polymers in aerospace applications - 1847350933 - ismithers rapra publishing

Expert overviews covering the science and technology of rubber and plastics

ISSN: 0889-3144

Volume 16, Number 12

Joel R. Fried

Polymers in Aerospace Applications

Report 192

16 –

12

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Item 1Macromolecules33, No.6, 21st March 2000, p.2171-83EFFECT OF THERMAL HISTORY ON THE RHEOLOGICAL BEHAVIOR OF THERMOPLASTIC POLYURETHANESPil Joong Yoon; Chang Dae HanAkron,University

The effect of thermal history on the rheological behaviour of ester- and ether-based commercial thermoplastic PUs (Estane 5701, 5707 and 5714 from B.F.Goodrich) was investigated. It was found that the injection moulding temp. used for specimen preparation had a marked effect on the variations of dynamic storage and loss moduli of specimens with time observed during isothermal annealing. Analysis of FTIR spectra indicated that variations in hydrogen bonding with time during isothermal annealing very much resembled variations of dynamic storage modulus with time during isothermal annealing. Isochronal dynamic temp. sweep experiments indicated that the thermoplastic PUs exhibited a hysteresis effect in the heating and cooling processes. It was concluded that the microphase separation transition or order-disorder transition in thermoplastic PUs could not be determined from the isochronal dynamic temp. sweep experiment. The plots of log dynamic storage modulus versus log loss modulus varied with temp. over the entire range of temps. (110-190C) investigated. 57 refs.

GOODRICH B.F.USA

Accession no.771897

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Previous Titles Still AvailableVolume 1Report 1 Conductive Polymers, W.J. Feast

Report 2 Medical, Surgical and Pharmaceutical Applications of Polymers, D.F. Williams

Report 3 Advanced Composites, D.K. Thomas, RAE, Farnborough.

Report 4 Liquid Crystal Polymers, M.K. Cox, ICI, Wilton.

Report 5 CAD/CAM in the Polymer Industry, N.W. Sandland and M.J. Sebborn, Cambridge Applied Technology.

Report 8 Engineering Thermoplastics, I.T. Barrie, Consultant.

Report 10 Reinforced Reaction Injection Moulding, P.D. Armitage, P.D. Coates and A.F. Johnson

Report 11 Communications Applications of Polymers, R. Spratling, British Telecom.

Report 12 Process Control in the Plastics Industry, R.F. Evans, Engelmann & Buckham Ancillaries.

Volume 2Report 13 Injection Moulding of Engineering Thermoplastics,

A.F. Whelan, London School of Polymer Technology.

Report 14 Polymers and Their Uses in the Sports and Leisure Industries, A.L. Cox and R.P. Brown, Rapra Technology Ltd.

Report 15 Polyurethane, Materials, Processing and Applications, G. Woods, Consultant.

Report 16 Polyetheretherketone, D.J. Kemmish, ICI, Wilton.

Report 17 Extrusion, G.M. Gale, Rapra Technology Ltd.

Report 18 Agricultural and Horticultural Applications of Polymers, J.C. Garnaud, International Committee for Plastics in Agriculture.

Report 19 Recycling and Disposal of Plastics Packaging, R.C. Fox, Plas/Tech Ltd.

Report 20 Pultrusion, L. Hollaway, University of Surrey.

Report 21 Materials Handling in the Polymer Industry, H. Hardy, Chronos Richardson Ltd.

Report 22 Electronics Applications of Polymers, M.T.Goosey, Plessey Research (Caswell) Ltd.

Report 23 Offshore Applications of Polymers, J.W.Brockbank, Avon Industrial Polymers Ltd.

Report 24 Recent Developments in Materials for Food Packaging, R.A. Roberts, Pira Packaging Division.

Volume 3Report 25 Foams and Blowing Agents, J.M. Methven, Cellcom

Technology Associates.

Report 26 Polymers and Structural Composites in Civil Engineering, L. Hollaway, University of Surrey.

Report 27 Injection Moulding of Rubber, M.A. Wheelans, Consultant.

Report 28 Adhesives for Structural and Engineering Applications, C. O’Reilly, Loctite (Ireland) Ltd.

Report 29 Polymers in Marine Applications, C.F.Britton, Corrosion Monitoring Consultancy.

Report 30 Non-destructive Testing of Polymers, W.N. Reynolds, National NDT Centre, Harwell.

Report 31 Silicone Rubbers, B.R. Trego and H.W.Winnan, Dow Corning Ltd.

Report 32 Fluoroelastomers - Properties and Applications, D. Cook and M. Lynn, 3M United Kingdom Plc and 3M Belgium SA.

Report 33 Polyamides, R.S. Williams and T. Daniels, T & N Technology Ltd. and BIP Chemicals Ltd.

Report 34 Extrusion of Rubber, J.G.A. Lovegrove, Nova Petrochemicals Inc.

Report 35 Polymers in Household Electrical Goods, D.Alvey, Hotpoint Ltd.

Report 36 Developments in Additives to Meet Health and Environmental Concerns, M.J. Forrest, Rapra Technology Ltd.

Volume 4Report 37 Polymers in Aerospace Applications, W.W. Wright,

University of Surrey.

Report 38 Epoxy Resins, K.A. Hodd

Report 39 Polymers in Chemically Resistant Applications, D. Cattell, Cattell Consultancy Services.

Report 40 Internal Mixing of Rubber, J.C. Lupton

Report 41 Failure of Plastics, S. Turner, Queen Mary College.

Report 42 Polycarbonates, R. Pakull, U. Grigo, D. Freitag, Bayer AG.

Report 43 Polymeric Materials from Renewable Resources, J.M. Methven, UMIST.

Report 44 Flammability and Flame Retardants in Plastics, J. Green, FMC Corp.

Report 45 Composites - Tooling and Component Processing, N.G. Brain, Tooltex.

Report 46 Quality Today in Polymer Processing, S.H. Coulson, J.A. Cousans, Exxon Chemical International Marketing.

Report 47 Chemical Analysis of Polymers, G. Lawson, Leicester Polytechnic.

Report 48 Plastics in Building, C.M.A. Johansson

Volume 5Report 49 Blends and Alloys of Engineering Thermoplastics, H.T.

van de Grampel, General Electric Plastics BV.

Report 50 Automotive Applications of Polymers II, A.N.A. Elliott, Consultant.

Report 51 Biomedical Applications of Polymers, C.G. Gebelein, Youngstown State University / Florida Atlantic University.

Report 52 Polymer Supported Chemical Reactions, P. Hodge, University of Manchester.

Report 53 Weathering of Polymers, S.M. Halliwell, Building Research Establishment.

Report 54 Health and Safety in the Rubber Industry, A.R. Nutt, Arnold Nutt & Co. and J. Wade.

Report 55 Computer Modelling of Polymer Processing, E. Andreassen, Å. Larsen and E.L. Hinrichsen, Senter for Industriforskning, Norway.

Report 56 Plastics in High Temperature Applications, J. Maxwell, Consultant.

Report 57 Joining of Plastics, K.W. Allen, City University.

Report 58 Physical Testing of Rubber, R.P. Brown, Rapra Technology Ltd.

Report 59 Polyimides - Materials, Processing and Applications, A.J. Kirby, Du Pont (U.K.) Ltd.

Report 60 Physical Testing of Thermoplastics, S.W. Hawley, Rapra Technology Ltd.

Volume 6Report 61 Food Contact Polymeric Materials, J.A. Sidwell,

Rapra Technology Ltd.

Report 62 Coextrusion, D. Djordjevic, Klöckner ER-WE-PA GmbH.

Report 63 Conductive Polymers II, R.H. Friend, University of Cambridge, Cavendish Laboratory.

Report 64 Designing with Plastics, P.R. Lewis, The Open University.

Report 65 Decorating and Coating of Plastics, P.J. Robinson, International Automotive Design.

Report 66 Reinforced Thermoplastics - Composition, Processing and Applications, P.G. Kelleher, New Jersey Polymer Extension Center at Stevens Institute of Technology.

Report 67 Plastics in Thermal and Acoustic Building Insulation, V.L. Kefford, MRM Engineering Consultancy.

Report 68 Cure Assessment by Physical and Chemical Techniques, B.G. Willoughby, Rapra Technology Ltd.

Report 69 Toxicity of Plastics and Rubber in Fire, P.J. Fardell, Building Research Establishment, Fire Research Station.

Report 70 Acrylonitrile-Butadiene-Styrene Polymers, M.E. Adams, D.J. Buckley, R.E. Colborn, W.P. England and D.N. Schissel, General Electric Corporate Research and Development Center.

Report 71 Rotational Moulding, R.J. Crawford, The Queen’s University of Belfast.

Report 72 Advances in Injection Moulding, C.A. Maier, Econology Ltd.

Volume 7Report 73 Reactive Processing of Polymers, M.W.R. Brown,

P.D. Coates and A.F. Johnson, IRC in Polymer Science and Technology, University of Bradford.

Report 74 Speciality Rubbers, J.A. Brydson.

Report 75 Plastics and the Environment, I. Boustead, Boustead Consulting Ltd.

Report 76 Polymeric Precursors for Ceramic Materials, R.C.P. Cubbon.

Report 77 Advances in Tyre Mechanics, R.A. Ridha, M. Theves, Goodyear Technical Center.

Report 78 PVC - Compounds, Processing and Applications, J.Leadbitter, J.A. Day, J.L. Ryan, Hydro Polymers Ltd.

Report 79 Rubber Compounding Ingredients - Need, Theory and Innovation, Part I: Vulcanising Systems, Antidegradants and Particulate Fillers for General Purpose Rubbers, C. Hepburn, University of Ulster.

Report 80 Anti-Corrosion Polymers: PEEK, PEKK and Other Polyaryls, G. Pritchard, Kingston University.

Report 81 Thermoplastic Elastomers - Properties and Applications, J.A. Brydson.

Report 82 Advances in Blow Moulding Process Optimization, Andres Garcia-Rejon,Industrial Materials Institute, National Research Council Canada.

Report 83 Molecular Weight Characterisation of Synthetic Polymers, S.R. Holding and E. Meehan, Rapra Technology Ltd. and Polymer Laboratories Ltd.

Report 84 Rheology and its Role in Plastics Processing, P. Prentice, The Nottingham Trent University.

Volume 8Report 85 Ring Opening Polymerisation, N. Spassky, Université

Pierre et Marie Curie.

Report 86 High Performance Engineering Plastics, D.J. Kemmish, Victrex Ltd.

Report 87 Rubber to Metal Bonding, B.G. Crowther, Rapra Technology Ltd.

Report 88 Plasticisers - Selection, Applications and Implications, A.S. Wilson.

Report 89 Polymer Membranes - Materials, Structures and Separation Performance, T. deV. Naylor, The Smart Chemical Company.

Report 90 Rubber Mixing, P.R. Wood.

Report 91 Recent Developments in Epoxy Resins, I. Hamerton, University of Surrey.

Report 92 Continuous Vulcanisation of Elastomer Profi les, A. Hill, Meteor Gummiwerke.

Report 93 Advances in Thermoforming, J.L. Throne, Sherwood Technologies Inc.

Report 94 Compressive Behaviour of Composites, C. Soutis, Imperial College of Science, Technology and Medicine.

Report 95 Thermal Analysis of Polymers, M. P. Sepe, Dickten & Masch Manufacturing Co.

Report 96 Polymeric Seals and Sealing Technology, J.A. Hickman, St Clair (Polymers) Ltd.

Volume 9Report 97 Rubber Compounding Ingredients - Need, Theory

and Innovation, Part II: Processing, Bonding, Fire Retardants, C. Hepburn, University of Ulster.

Report 98 Advances in Biodegradable Polymers, G.F. Moore & S.M. Saunders, Rapra Technology Ltd.

Report 99 Recycling of Rubber, H.J. Manuel and W. Dierkes, Vredestein Rubber Recycling B.V.

Report 100 Photoinitiated Polymerisation - Theory and Applications, J.P. Fouassier, Ecole Nationale Supérieure de Chimie, Mulhouse.

Report 101 Solvent-Free Adhesives, T.E. Rolando, H.B. Fuller Company.

Report 102 Plastics in Pressure Pipes, T. Stafford, Rapra Technology Ltd.

Report 103 Gas Assisted Moulding, T.C. Pearson, Gas Injection Ltd.

Report 104 Plastics Profi le Extrusion, R.J. Kent, Tangram Technology Ltd.

Report 105 Rubber Extrusion Theory and Development,B.G. Crowther.

Report 106 Properties and Applications of Elastomeric Polysulfi des, T.C.P. Lee, Oxford Brookes University.

Report 107 High Performance Polymer Fibres, P.R. Lewis, The Open University.

Report 108 Chemical Characterisation of Polyurethanes,M.J. Forrest, Rapra Technology Ltd.

Volume 10Report 109 Rubber Injection Moulding - A Practical Guide,

J.A. Lindsay.

Report 110 Long-Term and Accelerated Ageing Tests on Rubbers, R.P. Brown, M.J. Forrest and G. Soulagnet, Rapra Technology Ltd.

Report 111 Polymer Product Failure, P.R. Lewis, The Open University.

Report 112 Polystyrene - Synthesis, Production and Applications, J.R. Wünsch, BASF AG.

Report 113 Rubber-Modifi ed Thermoplastics, H. Keskkula, University of Texas at Austin.

Report 114 Developments in Polyacetylene - Nanopolyacetylene, V.M. Kobryanskii, Russian Academy of Sciences.

Report 115 Metallocene-Catalysed Polymerisation, W. Kaminsky, University of Hamburg.

Report 116 Compounding in Co-rotating Twin-Screw Extruders, Y. Wang, Tunghai University.

Report 117 Rapid Prototyping, Tooling and Manufacturing, R.J.M. Hague and P.E. Reeves, Edward Mackenzie Consulting.

Report 118 Liquid Crystal Polymers - Synthesis, Properties and Applications, D. Coates, CRL Ltd.

Report 119 Rubbers in Contact with Food, M.J. Forrest and J.A. Sidwell, Rapra Technology Ltd.

Report 120 Electronics Applications of Polymers II, M.T. Goosey, Shipley Ronal.

Volume 11

Report 121 Polyamides as Engineering Thermoplastic Materials, I.B. Page, BIP Ltd.

Report 122 Flexible Packaging - Adhesives, Coatings and Processes, T.E. Rolando, H.B. Fuller Company.

Report 123 Polymer Blends, L.A. Utracki, National Research Council Canada.

Report 124 Sorting of Waste Plastics for Recycling, R.D. Pascoe, University of Exeter.

Report 125 Structural Studies of Polymers by Solution NMR, H.N. Cheng, Hercules Incorporated.

Report 126 Composites for Automotive Applications, C.D. Rudd,University of Nottingham.

Report 127 Polymers in Medical Applications, B.J. Lambert and F.-W. Tang, Guidant Corp., and W.J. Rogers, Consultant.

Report 128 Solid State NMR of Polymers, P.A. Mirau, Lucent Technologies.

Report 129 Failure of Polymer Products Due to Photo-oxidation, D.C. Wright.

Report 130 Failure of Polymer Products Due to Chemical Attack, D.C. Wright.

Report 131 Failure of Polymer Products Due to Thermo-oxidation, D.C. Wright.

Report 132 Stabilisers for Polyolefi ns, C. Kröhnke and F. Werner, Clariant Huningue SA.

Volume 12Report 133 Advances in Automation for Plastics Injection

Moulding, J. Mallon, Yushin Inc.

Report 134 Infrared and Raman Spectroscopy of Polymers, J.L. Koenig, Case Western Reserve University.

Report 135 Polymers in Sport and Leisure, R.P. Brown.

Report 136 Radiation Curing, R.S. Davidson, DavRad Services.

Report 137 Silicone Elastomers, P. Jerschow, Wacker-Chemie GmbH.

Report 138 Health and Safety in the Rubber Industry, N. Chaiear, Khon Kaen University.

Report 139 Rubber Analysis - Polymers, Compounds and Products, M.J. Forrest, Rapra Technology Ltd.

Report 140 Tyre Compounding for Improved Performance, M.S. Evans, Kumho European Technical Centre.

Report 141 Particulate Fillers for Polymers, Professor R.N. Rothon, Rothon Consultants and Manchester Metropolitan University.

Report 142 Blowing Agents for Polyurethane Foams, S.N. Singh, Huntsman Polyurethanes.

Report 143 Adhesion and Bonding to Polyolefi ns, D.M. Brewis and I. Mathieson, Institute of Surface Science & Technology, Loughborough University.

Report 144 Rubber Curing Systems, R.N. Datta, Flexsys BV.

Volume 13Report 145 Multi-Material Injection Moulding, V. Goodship and

J.C. Love, The University of Warwick.

Report 146 In-Mould Decoration of Plastics, J.C. Love and V. Goodship, The University of Warwick.

Report 147 Rubber Product Failure, Roger P. Brown.

Report 148 Plastics Waste – Feedstock Recycling, Chemical Recycling and Incineration, A. Tukker, TNO.

Report 149 Analysis of Plastics, Martin J. Forrest, Rapra Technology Ltd.

Report 150 Mould Sticking, Fouling and Cleaning, D.E. Packham, Materials Research Centre, University of Bath.

Report 151 Rigid Plastics Packaging - Materials, Processes and Applications, F. Hannay, Nampak Group Research & Development.

Report 152 Natural and Wood Fibre Reinforcement in Polymers, A.K. Bledzki, V.E. Sperber and O. Faruk, University of Kassel.

Report 153 Polymers in Telecommunication Devices, G.H. Cross, University of Durham.

Report 154 Polymers in Building and Construction, S.M. Halliwell, BRE.

Report 155 Styrenic Copolymers, Andreas Chrisochoou and Daniel Dufour, Bayer AG.

Report 156 Life Cycle Assessment and Environmental Impact of Polymeric Products, T.J. O’Neill, Polymeron Consultancy Network.

Volume 14Report 157 Developments in Colorants for Plastics,

Ian N. Christensen.

Report 158 Geosynthetics, David I. Cook.

Report 159 Biopolymers, R.M. Johnson, L.Y. Mwaikambo and N. Tucker, Warwick Manufacturing Group.

Report 160 Emulsion Polymerisation and Applications of Latex, Christopher D. Anderson and Eric S. Daniels, Emulsion Polymers Institute.

Report 161 Emissions from Plastics, C. Henneuse-Boxus and T. Pacary, Certech.

Report 162 Analysis of Thermoset Materials, Precursors and Products, Martin J. Forrest, Rapra Technology Ltd.

Report 163 Polymer/Layered Silicate Nanocomposites, Masami Okamoto, Toyota Technological Institute.

Report 164 Cure Monitoring for Composites and Adhesives, David R. Mulligan, NPL.

Report 165 Polymer Enhancement of Technical Textiles, Roy W. Buckley.

Report 166 Developments in Thermoplastic Elastomers, K.E. Kear

Report 167 Polyolefi n Foams, N.J. Mills, Metallurgy and Materials, University of Birmingham.

Report 168 Plastic Flame Retardants: Technology and Current Developments, J. Innes and A. Innes, Flame Retardants Associates Inc.

Volume 15Report 169 Engineering and Structural Adhesives, David J. Dunn,

FLD Enterprises Inc.

Report 170 Polymers in Agriculture and Horticulture, Roger P. Brown.

Report 171 PVC Compounds and Processing, Stuart Patrick.

Report 172 Troubleshooting Injection Moulding, Vanessa Goodship, Warwick Manufacturing Group.

Report 173 Regulation of Food Packaging in Europe and the USA, Derek J. Knight and Lesley A. Creighton, Safepharm Laboratories Ltd.

Report 174 Pharmaceutical Applications of Polymers for Drug Delivery, David Jones, Queen's University, Belfast.

Report 175 Tyre Recycling, Valerie L. Shulman, European Tyre Recycling Association (ETRA).

Report 176 Polymer Processing with Supercritical Fluids, V. Goodship and E.O. Ogur.

Report 177 Bonding Elastomers: A Review of Adhesives & Processes, G. Polaski, J. Means, B. Stull, P. Warren, K. Allen, D. Mowrey and B. Carney.

Report 178 Mixing of Vulcanisable Rubbers and Thermoplastic Elastomers, P.R. Wood.

Report 179 Polymers in Asphalt, H.L. Robinson, Tarmac Ltd, UK.

Report 180 Biocides in Plastics, D. Nichols, Thor Overseas Limited.

Volume 16Report 181 New EU Regulation of Chemicals: REACH,

D.J. Knight, SafePharm Laboratories Ltd.

Report 182 Food Contact Rubbers 2 - Products, Migration and Regulation, M.J. Forrest.

Report 183 Adhesion to Fluoropolymers, D.M. Brewis and R.H. Dahm, IPTME, Loughborough University.

Report 184 Fluoroplastics, J.G. Drobny.

Report 185 Epoxy Composites: Impact Resistance and Flame Retardancy, Debdatta Ratna.

Report 186 Coatings and Inks for Food Contact Materials, Martin Forrest, Smithers Rapra.

Report 187 Nucleating Agents, Stuart Fairgrieve, SPF Polymer Consultants.

Report 188 Silicone Products for Food Contact Applications, Martin Forrest, Smithers Rapra.

Report 189 Degradation and Stabilisation of Polymers,Stuart Fairgrieve, SPF Polymer Consultants

Report 190 ElectrospinningJon Stanger, New Zealand Institute for Plant and Food ResearchNick Tucker, New Zealand Institute for Plant and Food ResearchMark Staiger, Univeristy of Canterbury, New Zeland

Report 191 Polyvinylalcohol: Materials, Processing and ApplicationsVannessa Goodship, Warwick Manufacturing Group, University of WarwickDaniel Jacobs, Warwick Manufacturing Group, University of Warwick

ISBN: 978-1-84735-093-0


Joel R. Fried


1

Contents

1. Introduction ...................................................................................................................................................3

2. Adhesives ......................................................................................................................................................3

3. Coatings ........................................................................................................................................................3

4. Fibres .............................................................................................................................................................3

4.1 Fibre Types ...........................................................................................................................................3

4.1.1 Carbon-Based Fibres ...............................................................................................................3

4.1.2 Inorganic Fibres ......................................................................................................................4

4.1.3 Polymeric Fibres .....................................................................................................................5

4.1.4 Hybrid Fibres ..........................................................................................................................6

4.2 Fibre Forms .........................................................................................................................................6

4.3 Interfacial Properties ............................................................................................................................6

4.3.1 Coupling Agents .....................................................................................................................6

4.3.2 Surface Treatment ...................................................................................................................7

5. Composites ....................................................................................................................................................7

5.1 Matrix Polymers ...................................................................................................................................7

5.1.1 Thermosetting Matrices .........................................................................................................8

5.1.2 TP Matrices ..........................................................................................................................10

5.2 Fabrication Methods ..........................................................................................................................12

5.3 Non-destructive Testing ......................................................................................................................12

6. Nanocomposites ..........................................................................................................................................13

6.1 Nano-Reinforcements ........................................................................................................................13

6.2 Processing ..........................................................................................................................................15

6.3 Properties of Nanocomposites ............................................................................................................15

7. Foams ..........................................................................................................................................................16

References ........................................................................................................................................................16

Abbreviations ...................................................................................................................................................16

Abstracts ..........................................................................................................................................................19

Index ..............................................................................................................................................................131


2

The views and opinions expressed by authors in Rapra Review Reports do not necessarily refl ect those of Smithers Rapra Technology or the editor. The series is published on the basis that no responsibility or liability of any nature shall attach to Smithers Rapra Technology arising out of or in connection with any utilisation in any form of any material contained therein.

Author contact details: Joel R. FriedDepartment of Chemical and Materials Engineering University of Cincinnati2600 Clifton Avenue, Cincinnati, Ohio 45221USA


3

1. Introduction

The last RAPRA Report on Polymers in Aerospace Applications (W.W. Wright, Report 37) was published in 1990. The present report strives to provide a contemporary review of this area with an emphasis on the literature appearing after 1990. It includes coverage of new materials and technologies (particularly nanocomposites).

The principal use for polymers in aerospace applications is as a matrix material and/or reinforcing � bre for composites. Other major applications include use in adhesives, anti-misting additives, coatings, elastomers, � bres, and foams.

2. Adhesives

Applications for adhesives include metal-to-metal bonding for aluminium and titanium parts, composite-to-metal bonding, and the bonding of elastomers to metal parts. Structural adhesives are manufactured in � lm and paste form (344). These are widely used in the manufacture, assembly, and repair of interior and exterior aircraft components. Examples include the reinforcement of honeycomb structures such as luggage lockers and � oor panels (190). Another use is the damping of engine and noise vibration (190). For example, epoxy-based syntactic paste has been used for engine vibration damping. A � ame-retardant epoxy paste has been used for high-strength reinforcement in honeycomb core parts as well as in fasteners in overhead baggage lockers (190). Adhesives with working temperatures in the range 315 °C to 400 °C have been reported for advanced thermal protection systems bondlines. Ultra-high temperature-resistant epoxy adhesives have been used to join together polybenzimidazole (PBI) sheets (199) under high-energy irradiation and low-pressure plasma treatment to provide service temperatures in the range –260 °C to +370 °C for potential aerospace and space applications (199).

3. Coatings

Coatings can provide protection against abrasion and corrosion as well as reduce icing, provide shielding against electromagnetic interference (EMI) or radio frequency interference (RFI), and to protect insulation. Modi� ed phosphate pigments contained in an epoxy/polyurethane carrier have been used for primers for metal and plastic substrates. These primers are resistant to hydraulic

� uids. Polysul� des and silicone resins have been used for anti-icing applications. Nylon-6,6 reinforced with nickel-coated carbon � bres (CF) have been used for EMI/RFI shielding. Thin � lms of poly(vinylidene � uoride), polyethylene, and polyimides (PI) have been used to cover layers of insulation in aircraft and space vehicles.

4. Fibres

The most widely used � bres for aerospace are glass, carbon, aramid, and boron (470). Other � bres used for high-performance composites include ultra-high molecular weight polyethylene (UHMWPE) and poly(p-phenylene-2,6-benzobisoxazole) (PBO) (217). A comparison of the modulus and strength of glass, carbon, and aramid � bres is given in Table 1. Principal differences between � bre groups include modulus as well as thermal and chemical stability. As shown by representative values in Table 1, the modulus can vary by more than one order of magnitude. Most � bres used in aerospace applications serve as reinforcements in composite materials; other uses are found for these fibres in cabin furnishing, parachutes, and other specialised applications. Properties and applications of carbon-based, inorganic, and polymeric � bres are reviewed in depth within the following sub-sections.

Table 1 Mechanical Properties of Typical Aerospace Fibres (472)

Fibre Modulus (GPa) Strength (MPa)

E-glass 72.4 3450S-glass 85.5 4600Carbon (PAN-based)

280–450 4140–5170

Aramid 830 4500PAN: Polyacrylonitrile

4.1 Fibre Types

4.1.1 Carbon-Based Fibres

Carbon � bres

Since the 1960s, CF have been the most widely used reinforcing � bres in advanced composites. They can be produced from PAN, Rayon, or pitch (e.g., petroleum


4

or coal tar). Early CF were produced from the pyrolysis of Rayon precursors. PAN precursors are now more common because they can be produced without the high-temperature graphitisation step required for Rayon-based CF. In general, CF is less impact-resistant that aramid or glass � bre (398). There is a continuing need to produce lower-cost CF ideally produced at low temperatures from cheap, abundant precursors such as anthracitic coal powder. Pitch-based CF have low-to-negative coef� cients of thermal expansion that are attractive for spacecraft applications (253). CF are stronger than glass or aramid � bres but are less impact-resistant and contact with metal can result in galvanic corrosion (253). It is estimated that 30% of CF consumption in 2009 will be for the aircraft and aerospace sector, with about 54% of the remaining production targeted for industrial use and 15% for sporting goods (245). Global demand for PAN-based CF is expected to grow at >10% per year (248). This is attributed to a resurgence of the aerospace market and speci� cally to production demands for new commercial aircraft such as the Boeing B787 and Airbus A380, as well as increased demand in other market sectors including use in the manufacture of windmill blades. Global production � gures for carbon � bres between 1999 and 2009 are shown in Figure 1.

Figure 1 Estimated global production of carbon � bre (245)

Another carbon-based � bre with interesting properties, especially for nanocomposite applications (see Section 6.1) is vapour-grown carbon � bre (VGCF) (310). VGCF has some similarities to multiwall carbon nanotubes (MWNT) but has larger outer (50–200 nm) and inner (30–90 nm) diameters, with lengths in the range 50 �m to 100 �m and aspect ratios between 100 to 500. VGCF has a typical tensile strength of 2.92 GPa and a tensile modulus of 240 GPa, and has very high thermal

conductivity (e.g., 1950 W/(m·K)). VGCF also has lower cost but defective microstructure can be a concern.

4.1.2 Inorganic Fibres

Inorganic � bres include primarily glass � bres but also � bres fabricated from more specialised material such as quartz and boron that � nd use in high-performance composite applications.

Glass Fibre

Compared with CF, glass � bre has higher density but offers superior impact resistance. Glass � bres come in several forms, including E-glass, S-glass, C-glass, and quartz. The commonest is E-glass (i.e., electrical grade), a calcium aluminoborosilicate glass. E-glass is a better electrical insulator than other glass � bres and represents 90% of all glass-� bre reinforcements (particularly � berglass). About 50% of the composition of E-glass is silica oxide. The remaining composition includes oxides of aluminium, boron, calcium, and other compounds, including limestone, � uorspar, boric acid, and clay (253). High-strength glass, a magnesium aluminosilicate glass, is known as S-glass in the USA (R-glass in Europe and T-glass in Japan). Compared with E-glass � bres, � bres made from S-glass have higher silica oxide content and are about 40–70% stronger (253) and 20% stiffer (398). Applications include aircraft panels, helicopter rotor blades, and � lament-wound rocket motor cases (470). Corrosion-resistant glass (C-glass or E-CR glass) provides greater resistance to acid environments than does E-glass (253).

Quartz Fibre

Compared with glass � bre, quartz � bre provides superior performance, including lower density, better mechanical properties (e.g., about twice the elongation-to-break and higher strength and stiffness), higher durability, better electromagnetic properties (favourable for fabrication of aircraft radomes), and a near zero coef� cient of thermal expansion (CTE) (309, 398). These superior properties come at a premium in cost. The use temperature of quartz � bre is as high as 1050 °C for continuous exposure and up to 1250 °C for short exposures (309).

Boron Fibre

Boron � bres were developed in the early 1960s and were the � rst high-performance reinforcements for advanced


5

composites. Boron � bres can be made by the vapour-deposition of boron vapours on tungsten or carbon � laments. They have very high strength and modulus, and offer excellent compressive properties and buckling resistance. Although boron � bres are expensive, their superior mechanical properties have led to applications as structural components on some high-performance military aircraft (470). Examples of aerospace applications include aircraft empennage skins, space shuttle truss members, and prefabricated aircraft repair patches (253, 309).

4.1.3 Polymeric Fibres

Most polymeric � bres used for composite applications are highly aromatic, rigid-chain polymers. These include aromatic polyamides, known as aramids. NomexTM and KevlarTM are aramids. These have high use-temperatures and provide high modulus and excellent ballistic properties. Specialty polymeric � bres include PBO and polybenzothiozole. Quite distinct from these high-performance polymers that have highly aromatic main chains is UHMWPE. UHMWPE is a highly crystalline aliphatic polymer that is extruded as a gel under high pressure at low temperatures to achieve highly extended single chains offering very high modulus in the tensile direction.

Aramid Fibre

Aramids include poly(p-phenylene terephthalamide) (KevlarTM)

HN

HN

O

C

O

C

Figure 2 Structure of Kevlar

and poly(m-phenylene isophthalamide) (NomexTM)

NH

O O

NH

Figure 3 Structure of Nomex

Nomex is prepared by the condensation polymerisation of 1,3-phenylene diamine and isophthallic acid (254). The most widely used aramid � bre for high-performance composites is Kevlar. Kevlar is prepared by the polycondensation of 1,4-phenylene diamine and terephthalic acid. Aramid fibres have lower compressive strength than CF or inorganic � bres. Other disadvantages include high water absorption and poor matrix adhesion in some cases. The high tensile strength (Table 1) of aramid � bres offers important opportunities for composite applications such as � lament-wound rocket motor cases, gas pressure vessels, and lightly loaded structures on aircraft (470). Aramid � bres provide exceptional impact resistance and tensile strength (253). Typical high-performance aramid � bres have moduli of about 138 GPa and tensile strength in the range of 3,447 MPa. The properties of aramid � bres can be modi� ed by surface oxidation or plasma etching that can improve off-axis strength of the composite (254). Bonding of the � bre to the matrix can be improved through chemical modi� cation, plasma treatment, or by the use of a coupling agent (254).

PBO

PBO � bres (Zylon®) [a.1] have higher strength than CF. PBO also offers excellent heat and � ame resistance (469) and has about twice the modulus and tensile strength of that of an aramid � bre. The decomposition temperature of PBO is about 100 °C higher than Kevlar (253, 309, 398). Comparison of the properties of aramid and PBO � bres is made in Table 2.

OO

N N

Figure 4 Structure of PBO

Polybenzothiazole (PBZT)

Another rigid-rod polymer similar in structure to PBO is PBZT [a.2]. Like PBO, PBZT has high modulus, high temperature resistance, and excellent resistance to organic solvents.

NS

N S

Figure 5 Structure of PBZT


6

UHMWPE

The attractive properties of these lightweight � bres made from UHMWPE include high impact resistance, extremely high speci� c strength, excellent chemical, ultraviolet (UV), and moisture resistance, outstanding impact resistance, abrasion resistance, low dielectric constant, and anti-ballistic properties (253). Conversely, UHMWPE � bres have low resistance to elongation under sustained load and a comparatively low use-temperature (398) with a melting point of 150 °C. UHMWPE fibre is produced by gel spinning of UHMWPE dissolved in a suitable solvent (254). Fibre drawing increases strength and modulus (254). Functional groups can be introduced on the surface of UHMWPE � bres by means of corona discharge and plasma treatment (254). The aerospace applications for UHMWPE � bre composites are limited, but their antiballistic properties are suitable for applications such as the bulletproof insert in forti� ed cockpit doors in Boeing single-aisle aircraft (253, 398).

Poly(aryl ether ether ketone) (PEEK)

PEEK, is a semicrystalline engineering thermoplastic (TP) with a heat distortion temperature (HDT) of 148 °C.

O

COO

Figure 6 Structure of PEEK

PEEK can be spun into high-modulus yarn for aerospace applications by drawing at 200 °C (1). These yarns can be used under long-term exposure to 250 °C and short-term exposure at 500 °C.

4.1.4 Hybrid Fibres

CF can be woven with aramid and glass � bres to produce hybrid cloths for composite application. Carbon/aramid and carbon/glass � bre hybrids have been used in some aircraft applications such as ribbed aircraft engine thrust reversers (254, 398).

4.2 Fibre Forms

Fibre reinforcements come in various forms, including continuous spools of tow (carbon) or roving (glass), woven fabrics, stitched multaxials, non-woven mats, and chopped � bre. Tows are bundles of continuous � bres. The number of individual � bres in a tow is designated by a number followed by ‘K’, indicating a multiplication by 1000. CF tows consist of thousands of � bre. Typical sizes of aerospace-grade tows range 1 K to 12 K (253). Tows may be used directly in � lament winding or pultrusion, or fabricated in a unidirectional tape.

4.3 Interfacial Properties

Good interfacial strength between the � ller and the matrix polymer is critical to achieving high modulus and particularly strength [a.3]. This is often achieved by using a coupling agent that shares the chemical characteristics of the � bre and the matrix, as discussed in Section 4.3.1. For high-temperature aerospace applications, special � bre treatments may be used in place of coupling agents that may degrade at elevated temperatures.

4.3.1 Coupling Agents

In general, the interfacial strength of composites can be improved by the use of low-molecular-weight organofunctional silanes or titanates. For example, the interfacial strength of a glass � bre-reinforced composite

Table 2 Mechanical Properties of PBO and Aramid Fibres (469)Fibre Denier Tensile Strength

(g/den)Elongation at Break (%)

Tensile Modulus (g/den)

PBO 500 44.1 4.0 1320PBO high modulus 490 42.1 2.6 1790Aramid 1450 23.1 3.5 610Aramid high modulus 1440 21.6 2.4 910den: Denier, a measure of the � bre weight reported in the number of grams per 9000 m.


7

can be improved by the use of silicon-containing coupling agents: these are the most common. Titanate coupling agents are also used in some cases. Examples of commonly used coupling agents are given in Table 3. The effect of two different silane coupling agents (Table 3) on the � exural properties of an unsaturated polyester composite is illustrated in Table 4. Comparison shows that vinyl silane and particularly methacrylate silane improve � exural strength under dry exposure and at 2-hour exposure in boiling water.

4.3.2 Surface Treatment

The interfacial properties of � bres can be improved without the use of traditional coupling agents. For example, the interfacial adhesion of UHMWPE � bre can be improved by plasma treatment in pure oxygen. The surface life of � bre-reinforced polyimide composites in a high-temperature oxidative environment can be extended by coating a polyimide precursor solution followed by curing at elevated temperature in a nitrogen environment (468).

5. Composites

Compared with metals, composites offer high strength and low weight. Other attractive properties for aerospace applications include good vibrational damping, low CTE, and good fatigue resistance. Conversely, the low thermal and thermo-oxidative stability of some polymeric composites can be a concern for many high-temperature aerospace applications. Although carbon fibre-reinforced plastics (CFRP) represent a small portion of the total composite market (i.e., compared with glass-reinforced plastics such as � breglass), the market growth of CFRP is signi� cantly greater than for other composite materials.

5.1 Matrix Polymers

Polymeric matrices for composites include traditional thermosets (e.g., epoxies) and TP resins (475), including some PI and aromatic ketone polymers (e.g., PEEK and poly(aryl ether ketone ketone) PEKK). TP are semicrystalline or amorphous. Some TP polymers such as

Table 3 Common Coupling Agents [a.3]Type Representative Structure

Epoxy silane

H2C C H CH 2O C H 2C H2C H 2 CH 2 Si( OC H 3)

O

Methacrylate

H2C C C O CH2CH2CH2 Si(OCH3)3

C H3 O

Primary amine silane NH2CH2C H2CH2 Si(OCH3)3

Vinyl silane H2C CH Si(OCH3)3

Titanate

3

H2C C C O TiOCH(CH3)2( )C H3 O

Table 4 Flexural Strength of a Glass-Reinforced Polyester [a.3]Flexural Strength (GPa)

Coupling Agent Dry Two-Hour BoilNone 0.38 0.23Vinyl silane 0.46 0.41Methacrylate silane 0.62 0.59


8

PI can be crosslinked though the use of end-functioning low-molecular weight resin. In general, thermosetting resins provide greater resistance to aggressive � uids such as acetone and hydraulic � uids, but lower-impact properties and the shelf-life of pre-cure resins is limited. Composites prepared from TP resins can be fabricated by a wide variety of methods and provide higher toughness and increased fatigue and wear resistance, but generally have poor solvent resistance.

The ability to withstand high temperatures can be a critical consideration in many aerospace applications. For example, skin temperatures of Mach 1 aircraft reach 110 °C, but temperatures can reach 300 °C (327) for Mach 3 military aircraft. Guided weapons, re-entry vessels, and space shuttle service can require even higher use-temperature. PI prepared from the condensation polymerisation of an aromatic tetracarboxylic acid and an aromatic diamine, were developed in the 1960s to provide such high service temperatures. PBI, polybenzoxazoles, and polyquinolines provide even higher temperature stability but at higher costs.

5.1.1 Thermosetting Matrices

The commonest thermosets for advanced composites include epoxies, phenolics, cyanate esters (CE), bismaleimides (BMI), and PI. Typical properties of epoxy, phenolic, BMI, and CE resins are compared in Table 5. Although most properties are similar among the four thermosets, the highest temperature stability (based upon thermogravimetric analysis (TGA) data) is achieved by the BMI and CE resins. Other polymers belonging to this category and reviewed in this section are benzoxazines and phthalonitrile resins.

Benzoxazines are formed from the reaction of phenol with an aldehyde and aromatic amine (253). Maleimide-

and norbornene-functionalised benzoxazines provide improved thermal properties, including char yields of >55% and high glass transition temperature (Tg) (250 °C) (277).

Bismalemides

BMI thermosetting resin has similar properties to those of epoxies but offers better temperature performance, especially hot/wet service temperatures up to 232 °C (462), and high performance-to-cost ratio. They have been used for high-temperature structural applications on military aircraft (290). Like epoxies, the brittleness of BMI resins is high, but toughened versions (see Table 5) are available (470). Toughening methods include copolymerisation with styrene and hydroxyl methacrylate (254). Crosslinked BMI thermosets such as 4,4-bismaleimide diphenyl methane/o-o´-diallyl alcohol of bisphenol A (Matrimid 5292, Ciba Geigy) provide excellent high-temperature performance (464). A study of the effect of storage ageing on BMI prepregs have suggested that ageing for >30 days may reduce the curing rate (16).

Cyanoacrylate Esters

CE provide excellent strength and toughness, low moisture absorption, and superior electrical properties with a hot/wet service temperature around 149 °C (253, 398, 462). CE resins provide low dielectric loss, good adhesive properties, high glass-transition temperature (i.e., 220 °C to 290 °C), high solubility in ketones, and low moisture absorption (198). CE are more easily processed than BMI. Brittleness of cured CE resin can be a concern, and CE is often toughened (198) by including TP polymers or rubber. Applications for CE include ablatives and radomes due to excellent

Table 5 Properties of High-Performance Thermosets (462)Property Epoxy Phenolic Toughened BMI Cyanate EsterDensity (kg/m3×10-3) 1.2-1.25 1.24 1.2-1.3 1.1-1.35Use temperature (°C) RT to 180 200–250 ~200 ~200Tensile modulus (MPa) ×10-3 3.1-3.8 3-5 3.4-4.1 3.1-3.4Dielectric constant (1 MHz) 3.8-4.5 4.3-5.4 3.4-3.7 2.7-3.2Cure temperature (°C) RT to 180 150-190 220-300 180-250Mould Shrinkage (mm/mm) 0.0006 0.002 0.007 0.004TGA onset (°C) 260-340 300-360 360-400 400-420RT: Room temperature


9

dielectric properties of CE. CE also can be blended with epoxies and BMI (462). Epoxy-modi� ed bisphenol-A dicyanate resin reinforced with high-modulus CF for potential applications in a space environment has shown good resistance to thermal cycling, UV-irradiation, and exposure to boiling water (198). CE can be used for the formation of interpenetrating networks by blending with TP and thermosets (462). CE composites are used in primary and secondary structures in military aircraft as well as in satellite applications (462). These can be processed by conventional methods including pre-preging, resin transfer moulding (RTM), � lament winding, and sheet moulding techniques (462).

Epoxy

Epoxy resins are the most commonly used matrix material for composites, but their use in high-performance applications is limited by low service temperature that is adversely affected by moisture content, loading, and by the use of toughening agents. For example, an upper temperature limit of about 177 °C for dry structural use and only 149 °C for wet exposure has been suggested (198). Heavy loading of epoxy composites can lower use temperature to 120 °C. In general, the upper use temperature for advanced epoxies is limited to 150 °C to 180 °C (462). Epoxy resins provide many attractive features, including good handling properties, processibility, and low cost (470). Epoxies are commonly used in structural applications. Disadvantages include brittleness and moisture absorption that can lower use temperature as mentioned above. Toughened epoxies have found applications in aircraft structural composites (290) but toughening can also signi� cantly lower use temperature as indicated. Resin � ow characteristics and mechanical properties of tetraglycidyldiaminodiphenylmethane (TGDM) based epoxy resins can be modi� ed by reactive blending with an acrylonitrile–butadiene–methacrylic acid rubber (456).

Oxidative degradation of epoxy resins is also an important concern. The mechanism of oxidative degradation of an aerospace epoxy resin based upon TGDM and triglycidylaminophenol and diaminodiphenylsulfone has been investigated by Fourier transform infrared analysis (237). Results show that very different mechanisms are operative at 120 °C (close to actual use temperatures) compared with 170 °C (representative of accelerated ageing) where general oxidative changes occur in all areas of the matrix. At the lower temperature, the major reaction is probably oxidation of a methylene group adjacent to the nitrogen atom of the TGDM unit, whereas 170 °C ageing resulted in broader, general changes throughout the matrix.

Phenolic Resins

Phenolics such as phenol–formaldehyde resin are low-cost, flame-resistant, and low-smoke resins. Applications include � ame-resistant aircraft interior panels as well as ablative and rocket nozzle applications (398). Phenolics provide good heat and � ame resistance, ablative characteristics, and low cost (462). Major shortcomings include brittleness, poor shelf-life, and the need for high-pressure curing.

Phthalonitrile Resins

Oligomeric phthalonitrile resins have several attractive properties for high-performance composite applications, including very low moisture absorption and good thermal stability (2). These resins have been used to prepare void-free composites. Phthalonitrile end-capped oligomers are prepared by reacting pyromellitic dianhydride, an aromatic diamine, and 4-(aminophenoxy) phthalonitrile (APPH). Networks can be formed by reacting the end-capped oligomers with 4,4´-diaminodiphenyl sulfone at elevated temperatures.

CN

CNOH2N

Figure 7 Structure for APPH

Polyimides

PI are produced by a two-stage process in which a poly(amic acid) is � rst produced. This is followed by a � nal imidisation step. This intermediate is very corrosive and requires special consideration in mould design. The high values of Tg of PI make processing dif� cult. Elimination of water from the polycondensation reaction results in void formation that needs to be carefully controlled. As a class, PI have good adhesion and heat and chemical resistance as well as superior mechanical properties. Fire retardancy can be improved by the addition of phosphorus substituents. Use of a polyimide oligomer can promote better � bre wettability. Crosslinking by the use a functionally terminated oligomer as in the case of PMR-15 (in situ polymerisation of monomer reactants and the designation ‘-15’ in PMR-15 indicated the molecular weight of the first formed oligomer (i.e., 1500)) can lead to high-temperature and void-free


10

composites. PI composite can be fabricated using quartz, glass, boron, and graphite � bres reinforcement and are favoured as engineering laminates in supersonic aircraft (327). The use temperature for PI is typically 200 °C to 280 °C (463), although working temperatures as high as 315 °C have been reported.

PI resins can be thermosetting and TP. For composite applications, thermosetting PI are the primary choice. Thermosetting polyimides can provide hot/wet use temperature 260 °C to 320 °C. These PI are formed by a polycondensation reaction, but the release of volatiles may cause problems in terms of void formation during cure. Cost is typically high for these resins.

PMR polyimides such as PMR-15 use a two-stage curing process. The � rst-stage consists of solvent evaporation and an imidisation reaction to form short-chain imide oligomers with the release of condensation water. The second stage involves a ring-opening addition-type crosslinking reaction at nadic end groups to form the � nal crosslinked polyimide matrix. The absence of volatile release in the second stage is an advantage in forming void-free composites. Disadvantages include the need for a multi-stage cure process and the toxicity of the monomer 4,4´-methylenedianiline (301, 314). Over the past 20 years, PMR-15 has been the most widely used PI in the aerospace industry due to its high Tg (~340 °C) and good thermo-oxidative stability. Oxidation of the neat resin is diffusion-controlled, resulting in the formation of a surface oxidation layer (11). Ageing of PMR-15 neat resin in air at 288 °C has shown a small increase in Tg (330 °C to 336 °C) attributed to an increase in crosslink density (7). Ageing for 1000 hours resulted in a visibly damaged surface layer of ~0.16 mm thickness. This layer results in a decrease in tensile strength by acting as a crack initiation site, promoting premature failure. Tandon and co-workers (228) developed a model for thermo-oxidative ageing with a diffusion-reaction model whereby temperature, oxygen concentration, and weight-loss effects are considered. Extensive studies of the effect of ageing on the nano-indentation strain rate sensitivity have shown that the average strain rate sensitivity in the oxidised surface

layer is much higher than that of the non-oxidised interior, indicating that the oxidised surface layer has limited ductility and, thereby, is more susceptible to fracture [a.4]. A second-generation material is PMR II (in situ polymerisation). LARC™-ITPI, based upon the polycondensation of 4,4´-isophthaloyldiphthalic anhydride (IDPA) and 1,3-phenylenediamine, is another high-temperature PI matrix for aerospace applications (473).

5.1.2 TP Matrices

Composites made using a TP matrix represent a small but fast-growing market (253, 255, 290, 475). TP can be amorphous or semicrystalline. Some of the most widely used TP for composite applications include PEEK, polyetherimide (PEI), and poly(p-phenylene sul� de) (PPS). Representative properties are shown in Table 6. Continuous � bre-reinforced TP composites (471) provide cost-effective manufacturing achieved by a high degree of automation. Applications include use in aircraft interiors, wing ribs and panels, buckhead � oor panels, and landing gear doors. Compared with thermosets, TP composites provide the advantage of signi� cantly higher impact strength. On the negative side, use temperatures and resistance to solvents such as methyl ether ketone and hydraulic � uids of TP composites are lower than obtained using thermosetting composites. Such � uids act as stress cracking agents that can lead to mechanical failure. The properties of non-halogen � re-resistant TP have been reviewed by Lyon and Emrick (40).

Polyarylates

Aromatic polyester carbonates (polyarylates) having the general structure:

OCCO

OCO

O OCH3

O

C OCO

CH3

O

Figure 8 Structure of Polyarylate

Table 6 Representative Properties of Thermoplastic Resins (474)Polymer Morphology Tg (ºC) Processing

Temperature (ºC)

Yield Strength (MPa)

Modulus (GPa)

PEEK semicrystalline 143 380–400 100 3.7PEI amorphous 210 315–360 103 3.6PPS semicrystalline 88 330–345 79 3.3


11

are available in clear/transparent and pigmented versions that meet heat and smoke requirements for aircraft interior applications (40).

Poly(ether ether ketone)

PEEK or poly(ether ether ketone) (Victrex®) is used for the matrix of TP prepregs containing carbon, glass, and aramid � bres. PEEK has been reported to be capable of withstanding continuous operating temperature up to 260 °C in low-stress operations and 120 °C in aerospace structural applications (191). PEEK has good resistance to hydrolysis, corrosion, chemical, and radiation exposure. It provides high thermal stability, low coef� cient of expansion, good abrasion resistance, low smoke and toxic gas emission, and excellent stiffness (191).

O O

O

C

Figure 9 Structure of PEEK

Poly(arylether ketone ketone)

Developed in the 1980s, PEKK is a semicrystalline TP with low � ammability, a Tg of 156 °C, and melting temperatures in the range 300 °C to 310 °C (378). PEKK is the preferred TP resin matrix at temperatures >90 °C (378). PEKK composites have been prepared from short and continuous (i.e., tape and fabric, respectively) glass and CF composites (378). PEKK has high hot/wet retentions (up to 130 °C) due to low resin moisture pick-up (378). All high-temperature glass � bre sizings are suitable with PEKK and its processing temperature (335-345 °C) (378). Choice of sizing, however, can signi� cantly affect performance.

Polyetherimide

The commercial PEI Ultem® has the general structure

O

O

N CH3

C O

O

O

N

CH3

O

Figure 10 Structure of PEI

PEI is an amorphous polymer, developed in the 1980s, that offers high heat resistance, strength, and modulus. The mechanical performance of PEI degrades with exposure to aggressive � uids such as Skydrol hydraulic � uid (255). The effect of moisture on the interlaminar resistance of woven fabric PEI composite has been reported (187). Properties of composite structures formed by reactive heating a phenylethynyl-terminated PEI (Reactive Ultem®) coating on PAN-based CF have been reported (189). A suggested application is the rigidisation of in� atable composite structures in space.

Polyimides

PI composites have been used at temperatures >300 °C for electronics and aerospace applications (466). High-temperature coupling agents for S-glass and quartz fabric-reinforced PI are required at these temperatures to maintain high flexural strength (466). Thermoplastic polyimides (TPI) include LARCTM-TPI based on benzophenone dicarboxylic dianhydride and 3,3´-diamino benzophenone (254), LARCTM-ITPI based upon IDPA and 1,3-phenylenediamine (473), NR-10 B2 prepared by reacting hexa� uoro isopropylidene dianhydride with a 95/5 molar ratio of p/m-phenylene diamine, and polyimide 2080 produced by the reaction of benzophenone dicarboxylic acid dianhydride with a mixture of 80/20-toluene diisocyanate and methylene 4,4´-diisocyanate (254).

O

O

O

N N

O

OO

Figure 11 Structure of LARC-ITPI

Matrimid® is a high Tg (approximately 313 °C) amorphous TPI made from diaminophenylindane and 3,3´-4,4´-benzophenone tetracarboxylic dianhydride (BTDA).

N N

O

O

O

C

O

O

Figure 12 Structure of Matrimid


12

Polyamideimides such as TorlonTM, prepared by reacting trimellitoyl acid chloride with a mixture of 70/30 4,4´-diamino diphenyl oxide and phenylene diamine, has some of the properties of polyamides such as toughness and ductility, and the high heat resistance of PI.

O

OO

N O NH

Figure 13 Structure of Polyamideimides

PPS

Current grades of PPS (e.g., Forton®) exhibit good resistance to temperatures up to 240 °C (melting point between 280 °C and 290 °C) and are resistant to oils, fuels, solvents, anti-icing agents, and to acids/bases in the pH range 2 to 12. Other attractive properties include excellent hardness, dimensional stability, and excellent � re resistance. Water absorption is near 0.04%, signi� cantly lower than for other TP (including PEI and PEEK) used in aerospace applications. PPS can be processed by various TP composite technologies, including pultrusion, compression moulding, thermoforming, automated tape laying/� bre placement, and bladder moulding. Use of PPS matrix has been reported for structural applications on the Airbus A340 and A380 (290).

S

Figure 14 Structure of PPS

Polysulfones

Polysulfones that have been used in aerospace applications for aircraft interiors, and TP composite applications include bisphenol A polysulfone (PSF, UDELTM) and polyphenylsulfone (PPSU, RadelTM).

O C O

O

O

S

CH3

CH3

Figure 15 Structure of PSF

O O

O

S

O

Figure 16 Structure of PPSU

5.2 Fabrication Methods

Fibre reinforcement and matrix resin may be combined in a single step by various processes such as wet lay-up, � lament winding, pultrusion, and RTM. For some applications, resin-impregnated � bres (prepregs) are used. Prepregs can be made by using solvent, holt-melt, or powder impregnation techniques. A � bre-to-matrix ratio is typically 60:40 or higher for advanced composite materials (398). Resistive heating has been proposed as a route for the rigidisation of in� atable composite structures in space (189). The properties of a CF-reinforced heat-crosslinkable PEI (Ultem®) have been reported. Forming processes for TP composites include thermoforming, press-forming, compression moulding, matched-die moulding, welding, and diaphragm forming (448). Compression moulding is a high-volume, high-pressure method suitable for complex, high-strength glass-mat reinforced TP.

Resin Transfer Moulding

In the RTM process, a resin including high-temperature PI is injected into a closed cavity mould � lled with � bre reinforcement (314). RTM offers low fabrication cost compared with other alternatives such as autoclaving. High-temperature composite parts prepared by RTM have been incorporated in many high-performance military aircraft including the F-22 Raptor (314) where a RTM-processed bismaleimide prepreg has been used (467). The mould may be evacuated to assist the moulding process (vacuum-assisted RTM) (253).

5.3 Non-destructive Testing

Ultrasound techniques were used to monitor the cure of � breglass in 1966. Combined with other non-destructive evaluation techniques such as thermography and radiography techniques, composite properties such as density, modulus, and strength can be determined (280).


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6. Nanocomposites

Several excellent review articles on the properties and processing of nanocomposites are available (3, 41, 180, 206, 250, 312, 331, 358, 450 [a.5]). In general, the distinguishing characteristic of nanocomposites compared with more traditional composite materials is the dimensions of the reinforcing � ller. Nancomposites contain inorganic reinforcements with high aspect ratio and dimensions of 1–100 nm. The small size results in properties often superior to traditional composites. Some of the attractive properties of nanocomposites important for aerospace application include improved electrical and mechanical properties, reduced oxygen and water permeability, increased thermal stability, better � ame resistance, improved resistance to wear, elevated heat-distortion temperature, potential for surface and interface modi� cation, and easier processibility. Applications include fire-retardant coatings, rocket propulsion insulation, rocket nozzle ablative materials, aerospace structural panels, ultra-light space structures, and space mirror substrates (310, 298). Other potential aerospace applications include devices such as light-emitting diodes, photovoltaic cells, and gas sensors [a.6].

One of the � rst nanocomposites was fabricated from Nylon-6 by researchers at Toyota in the late 1980s. Typical properties of nylon nanocomposites are given in Table 7. As shown, tensile modulus and strength are signi� cantly improved without sacri� cing impact strength. Particularly noteworthy is the improvement in heat-distortion temperature due to the reinforcement. The use of nanocomposite material has been increasing very rapidly since the 1980s. The US market for nanocomposites is expected to reach 11 billion pounds by the year 2020.

Table 7 Representative Properties of a Nylon-6 Nanocomposite [a.3]

Property Nylon-6 NancompositeCoef� cient of thermal expansion (×105)

13 6.3

Heat-distortion temperature (°C)

65 145

Tensile modulus (GPa) 1.1 2.1Tensile Strength (MPa) 69 107Impact strength (kJ/m2) 2.3 2.8Water absorption (%) 0.87 0.51

Property improvement can be signi� cant at small loading. For example, the modulus of polydimethylsiloxane reinforced by 1% clay can be increased by approximately 100%. For a polysulfone organoclay nanocomposite,

modulus and strength reach a maximum at about 3 wt% organoclay content with little sacri� ce in elongation at break (461). At higher loading, exfoliation decreases and mechanical properties decline.

Nanocomposites have been prepared from nearly all commodity and engineering-grade plastics, including thermosetting resins. Examples of TP include polysiloxanes, Nylon 11, poly(vinyl acetate)–acrylic copolymer, poly(ethylene oxide), PEI, PI, and some TP elastomers such as polyamide silicone copolymer (298). Thermosets include phenolic, cyanate ester, and epoxies. Nanocomposite can be made using various � llers having at least one dimension in the nanometer range (95). Fillers include nanoclays, nanotubes, nano� bres, or silica and various metal oxides. Nano� bres are electrospun whiskers with diameters in the range 10–100 nm and length-to-diameter ratios >1000.

6.1 Nano-Reinforcements

Fillers used for nanocomposites include organic-modi� ed montmorillonite (MMT) nanoclays, nanosilica, carbon nano� bre (CNF), carbon nanotubes (CNT), polyhedral oliogomeric silsesquioxane (POSS), and various nanoparticles such as silica and more exotic � llers such indium tin oxide (ITO) (298).

MMT

The commonest form of nano-reinforcement is organoclay, MMT. MMT is a naturally occurring 2:1 phylloslicate with the same structure as talc and mica, but a different layer charge. Modi� cation of the inorganic surface of MMT by organic treatment is used to increase dispersion in the polymer matrix. The crystal structure of MMT consists of 1 nm thin layers with a central octahedral sheet of alumina fused between two external silica tetrahedral sheets. These platelets have thicknesses of ~1 nm with aspect ratios (i.e., diameter:thickness) of 10:1 to 1000:1 and are arranged in stacks that can be separated (or exfoliated) during composite fabrication. Isomorphoic substitution within the layers (e.g., replacing Al3+ by Mg2+) can be used to modify the charge exchange capacity. The silicate sheets in MMT are separated by cations, typically sodium, as illustrated in Figure 17. These cations balance the overall charge. The sodium cation in the gallery can be exchanged with other cations such as lithium, potassium, and calcium. In water-swollen layered silicates, organic cations, such as an alkyl ammonium cation, can also be used to replace Na+. The speci� c alkyl selection can be used to improve miscibility with the nanocomposite matrix.


14

Some examples include dimethyl distearyl ammonium chloride and dimethyl stearyl benzyl ammonium chloride. Silicone rubber nanocomposites can be fabricated by ion-exchanging Na+/MMT with dimethyl ditallow ammonium bromide or hexadecyltrimethylammonium bromide. This type of organophilic modi� cation improves the polymer miscibility of MMT. The ion-exchange process also increases the gallery height in relation to the molecular size of the organic cation.

Figure 17 Structure of sodium montmorillonite. Reproduced with permission from Southern Clay

Product, Incorporated

Nanosilica

Nanosilicas such as Aerosil® are very pure amorphous silica produced by high-temperature hydrolysis of silicon tetrachloride in an oxy-hydrogen gas � ame to produce particles in the range 7–40 nm (298). Hydrophilic and hydrophobic grades of nanosilicas are commercially available. Alkoxysilyl functional groups can improve matrix–silica binding (197).

Polyhedral Oligomeric Silsesquioxanes

Polyhedral oligomeric silsesquioxanes (POSS is a trademark of Hybrid Plastics (www.hybridplastics.com)) can serve as multifunctional additives providing molecular-level reinforcement as well as serving as processing aids and flame retardants (298). Other advantages of POSS-filled nanocomposites include increased service temperature, low density, low thermal conductivity, thermo-oxidative resistance, and ageing resistance. The chemical composition of POSS (RSiO1.5), is intermediate between that of silica (SiO2) and silicones (R2SiO). The commonest POSS has eight silicon atoms, each carrying an organic group (Figure 18). The typical dimensions of POSS particles are 1–3 nm.

Figure 18 Representation of a typical POSS structure. Possible organic substituents, R, are indicated.

Reproduced with permission from D.R. Paul and L.M. Robeson, Polymer, 2008, 49, 15, 3187.

© 2008, Elsevier

Carbon Nano� bres

CNF are discontinuous graphic � laments produced in the gas phase by the pyrolysis of hydrocarbons. Typical diameters of CNF range 50 nm to 200 nm with lengths in the range 50 �m to 100 �m.

Carbon Nanotubes

CNT provide attractive combinations of high � exibility and strength combined with high stiffness and low density. Carbon nanotubes can be single-walled (SWNT) or MWNT. SWNT have diameters as small as 0.4 nm compared with MWNT that have diameters in the range 2–25 nm. The typical tensile strength of CNT is 100–600 GPa. This range is about two orders of magnitude higher than that of typical CF. Densities of CNT are about 1.3 g/cm3 compared with 1.8–1.9 g/cm3 for CF (310). Compressive strengths of CNT are about two orders of magnitude higher than that of any other � bre. CNT also have extremely high stiffness, with Young’s modulus in the range 1–5 TPa, compared with 750 GPa for CF. CNT can also carry large current densities (>100 MA/cm2 for MWNT). Experimental thermal conductivities are about 200 W/(m·K). A problem with the use of CNT is the need for chemical modi� cation for favourable interaction with polymeric matrices. Their use requires high dispersion. Techniques used to achieve good dispersion include in situ polymerisation of the matrix, shear mixing, the use of surfactants, and solution processing (310).

Graphite Nanoplatelets

An alternative to CNT is the use of graphite nanoplatelets, especially for conducting nanocomposite applications. Several forms of nanographite include


15

expanded graphite, exfoliated graphite, and graphene. Functionalised graphene sheets can be prepared by controlled thermal expansion of graphite oxide.

6.2 Processing

Methods to disperse nanoparticles include high-shear mixing for liquid resins and three-roll milling for liquid resins, Brabender-type mixing for high-viscosity resins, and twin-screw extrusion for solid polymers (298). The process of exfoliation of surface-treated nanoclays under high-shear mixing is illustrated in Figure 19. Exfoliation results in improved mechanical properties, barrier performance, and application processing. Exchange of natural Na+ counter-ions with long-chain quaternary ammonium cations results in improved dispersion into hydrophobic polymers (298).

Figure 19 Mechanism of organoclay dispersion and exfoliation during melt processing. Reproduced with permission from D.R. Paul and L.M. Robeson,

Polymer, 2008, 49, 15, 3187. © 2008, Elsevier

6.3 Properties of Nanocomposites

One of the most signi� cant effects of nano� llers on the properties of the matrix polymer is the signi� cant increase in modulus compared with the neat resin. The addition of nano-sized � llers (especially organoclays) can increase modulus and tensile strength at signi� cantly smaller � ller content compared with more traditional reinforcing agents such as glass � bre. Modelling of the mechanical properties of nanocomposite materials has been given (183, 227, 315, 424). The effect of wt% � ller on relative modulus (i.e., the ratio of composite modulus to matrix polymer modulus) is compared for MMT and glass � bre-� lled Nylon 6 in Figure 20. As shown, approximately 20 wt% of glass � bre is necessary to increase the modulus of Nylon 6 to the same level achieved by addition of 7 wt% of MMT.

Figure 20 Comparison of relative modulus (i.e., the ratio of the modulus of the nancomposite to that of the

matrix polymer) at different concentrations of glass � bre and MMT concentration in Nylon 6. Reproduced

with permission from T.D. Fornes and D.R. Paul, Polymer, 2003, 44, 17, 4993. © 2003, Elsevier

Advantages of nanocomposites include improved barrier to fuel and dimensional stability (i.e., lower CTE) (301). Higher oxygen barrier performance can increase thermo-oxidative stability (301). For example, the oxygen permeability coef� cients of polyimide nanocomposites have been reported to drop by two-thirds and the thermal expansion coefficient to drop by 20% (301). Water resistivity also can be improved by adding reactive inorganic � llers. Nanocomposite � lms of CNT and ITO in polysiloxane have the capability for thermal control in satellite applications (197). Such nanocomposites provide anti-static properties. POSS and CNT can signi� cantly reduce the heat release rate and, thereby, improve � ame retardancy (235). Whereas nano� llers have small effects on the Tg, the effect on the HDT is signi� cant due to the large reinforcement effect of the nano� ller, as illustrated in Figure 21. As shown, the storage modulus, qualitatively related to the tensile modulus, is increased in the glassy region as well as the rubbery plateau. The result is a signi� cant increase in the heat distortion temperature.

Figure 21 Dynamic mechanical storage modulus of Nylon 6 as a function of temperature and wt% MMT content. The horizontal line illustrates how HDT at an

applied stress of 1.82 MPa changes with MMT loading. Reproduced with permission from T.D. Fornes and D.R.

Paul, Polymer, 2003, 44, 17, 4993. © 2003, Elsevier


16

The effect of oxydianiline (ODA)-modi� ed clay on the tensile properties of a BTDA-ODA polyimide is illustrated in Figure 22. Values represent relative modulus, relative maximum stress at break, and relative elongation at break (compared with the neat polyimide). As shown, the modulus is increased by more than threefold at only 7 wt% ODA-modi� ed organoclay. This increase in stiffness is accompanied by smaller improvements in stress and elongation at break. A similar improvement in tensile modulus and stress with a maximum at 3 wt% MMT has been reported for polysulfone nanocomposites (461).

Figure 22 Relative tensile properties (property of nanocomposite to that of the matrix polymer) reported

for a polyimide (BTDA–ODA) nanocomposite prepared using ODA-modi� ed organoclay. Data taken

from H-L. Tyan, K-H. Wei and T-E. Hsieh, Journal of Polymer Science Part B: Polymer Physics Edition,

2000, 38, 22, 2873. © 2000, Elsevier

7. Foams

In use since 1971, polymethacrylimide (PMI) has been fabricated into foam cores offering high strength, stiffness, and fatigue life. Thermoformed PMI foam has been used in many aerospace applications (252) as an alternative to Nomex® and aluminium honeycomb structures. Applications include helicopter rotor blades and structural sandwich cores of fuselage panels, as well as stringer pro� les in pressure bulkheads.

References

a.1. V. Kholodovych and W.J. Welsh in Polymer Data Handbook, Ed., J.E. Mark, Oxford University Press Inc., New York, NY, USA, 2009, p.386.

a.2. V. Kholodovych and W.J. Welsh in Polymer Data Handbook, Ed., J.E. Mark, 2009, Oxford University Press Inc., New York, NY, USA, 2009, p.394.

a.3. J.R. Fried, Polymer Science & Technology, 2nd Edition, Prentice Hall Upper Saddle River, Prentice Hall, NJ, USA, 2003.

a.4. Y.C. Lu, G.P. Tandon, S. Putthanarat and G.A. Schoeppner, Journal of Materials Science, 2009, 44, 8, 2119.

a.5. R.A. Vaia and E.P. Giannelis, MRS Bulletin, 2001, 26, 5, 394.

a.6. D.Y. Godovsky in Biopolymers, PVA Hydrogels, Anionic Polymerisation, Nanocomposites, Advances in Polymer Science No. 153, Springer, Berlin, Germany, 2000, p.163.

Abbreviations for Polymers in Aerospace Applications

APPH 4-(Aminophenoxy) phthalonitrile

BMI Bismaleimides

BTDA 3,3´-4,4´-Benzophenone tetracarboxylic dianhydride

CE Cyanate esters

CF Carbon � bre(s)

CFRP Carbon � bre reinforced plastics

CNF Carbon nano� bre

CNT Carbon nanotubes

CTE Coef� cient of thermal expansion

EMI Electromagnetic interference

HDT Heat distortion temperature

IDPA 4,4´-Benzophenone isophthaloyldiphthalic anhydride

ITO Indium tin oxide


17

MMT Montmorillonite

MWNT Multiwall carbon nanotubes

ODA Oxydianiline

PAN Polyacrylonitrile

PBI Polybenzimidazole

PBO Poly(p-phenylene-2,6-benzobisoxazole)

PBZT Polybenzothiazole

PEEK Poly(aryl ether ether ketone)

PEI Polyetherimide

PEKK Poly(ether ketone ketone)

PI Polyimide(s)

PMI Polymethacrylimide

PMR In situ polymerisation of monomer reactants.

POSS Polyhedral oligomeric silsesquioxanes

PPS Poly(p-phenylene sul� de)

PPSU Polyphenylsulfone

PSF Polysulfone

RFI Radio frequency interference

RTM Resin transfer moulding

SWNT Single wall carbon nanotubes

Tg Glass transition temperature

TGA Thermogravimetric analysis

TGDM Tetraglycidyldiaminodiphenylmethane

TP Thermoplastic

TPI Thermoplastic polyimides

UHMWPE Ultra-high molecular weight polyethylene

UV Ultraviolet

VGCF Vapour-grown carbon � bre


18

References and Abstracts

© Copyright 2008 Smithers Rapra Technology 19

Abstracts from the Polymer Library Database

Item 1Journal of Applied Polymer Science 112, No.4, 15th May 2009, p.2497PROPERTIES OF HIGH MODULUS PEEK YARNS FOR AEROSPACE APPLICATIONSShekar R I; Kotresh T M; Rao P M D; Kumar KIndia, Defence Bioengineering and Electromedical Laboratory; Bangalore,Central Silk Technological Research Institute; Kanpur,Defence Materials Stores Research & Development Establishment

The effects of the interactions between the rheological properties, spinning process variables and drawing conditions were investigated in order to obtain high modulus PEEK yarns that could be tailored for aerospace applications. Wide angle X-ray diffraction results indicated that drawing carried out above the glass transition temperature affected unit cell parameters, density and mechanical properties. The degree of orientation, characterised in terms of sonic velocity, was as high as 3 km/s with a sonic modulus of 105 gpd. The crystallinity increased with increasing draw temperature. Useful properties were observed at an optimum draw temperature of 200 deg.C (which may be the region of maximum crystallisation rate) and were primarily attributed to the maximum crystallisation temperature and the heat setting effect. The thermal stability of PEEK yarn under dynamic conditions suggested that PEEK could be used for high temperature applications (up to 250 deg.C) for long periods of exposure and 500 deg.C for short term exposure. 29 refs.INDIA

Accession no.1043036

Item 2Macromolecular SymposiaNo.277, 2009, p.190DEVELOPMENT OF OLIGOMERIC PHTHALONITRILE RESINS FOR ADVANCED COMPOSITE APPLICATIONSSelvakumar P; Sarojadevi MAnna, University

Phthalonitrile terminated oligomers were prepared in two stages by reacting an excess amount of pyromellitic dianhydride with aromatic diamines in a N,N-dimethylacetamide/toluene solvent mixture to form an anhydride terminated oligomeric intermediate, which was terminated by reaction with 4-(aminophenoxy)phthalonitrile. The oligomers were converted to network polymers using 4,4’-diaminodiphenyl sulphone as curing agent at elevated temperatures. Polymerisation of the oligomeric phthalonitrile/diamine mixtures and prepolymers was followed by DSC and the complex viscosity of the prepolymers during polymerisation determined by means of isothermal rheometric analysis. The

thermal and thermooxidative properties of the polymers were investigated by TGA, which showed that the polymers possessed better thermal and thermooxidative stability than current commercially available high-temperature thermosetting resins. 32 refs. (POLYCHAR-16, World Forum on Advanced Materials, Lucknow, India, 17th -21st Feb.2008)INDIA


Item 3European Polymer Journal 45, No.4, 2009, p.967PERMEABILITY OF POLYMER/CLAY NANOCOMPOSITES: A REVIEWChoudalakis G; Gotsis A D Crete, Technical University

This is a review of the existing studies on the permeability of gas molecules in nanocomposite materials that consist of inorganic platelet-shaped fi llers in polymeric matrices. We describe the dominant mechanisms for the transport of small molecules in polymers and polymer nanocomposites, as well as the procedures for the measurement of the permeability and the diffusivity. The emphasis is given on the various models that have been proposed for the prediction of permeability in polymer-clay nanocomposites. The infl uence of the characteristics of the inorganic particles on the barrier properties of the composite membrane is discussed and tested using the model and the available experimental data. Some aspects on the methods of improving the barrier properties of the nanocomposite are examined and a few applications of these materials as gas barriers are presented. 67 refs. Copyright (c) 2009 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; GREECE; WESTERN EUROPE


Item 4SAMPE Fall Technical Conference: Multifunctional Materials: Working Smarter Together. Proceedings of a conference held Memphis, Tn., 8-11 Sept., 2008.Covina, Ca., SAMPE International Business Offi ce, 2008, Paper 44, pp.8TAILORING THERMAL PROPERTIES IN COMPOSITE MATERIALS AND ITS INTERFACES FOR THERMOMECHANICAL APPLICATIONSRoy A K; Sangwook Sihn; Ganguli S; Varshney VWright-Patterson Air Force Base; Dayton, University, Research Institute; Universal Technology Corp.(SAMPE)

Thermal transport phenomena in aerospace fi bre-reinforced composites, composite joints and the composite material


20 © Copyright 2008 Smithers Rapra Technology

interface are analysed. It is shown through fi nite element analysis and molecular dynamics simulations that interface impedance plays an important role in dictating thermal transport through the interface and that through materials modelling parameters can be identifi ed to guide processing for tailoring interface performance. 8 refs.USA


Item 5SAMPE Fall Technical Conference: Multifunctional Materials: Working Smarter Together. Proceedings of a conference held Memphis, Tn., 8-11 Sept., 2008.Covina, Ca., SAMPE International Business Offi ce 2008, Paper 12, pp.13 LIFE PREDICTION OF CARBON FIBER/PEKK THERMOPLASTIC COMPOSITE MATERIAL FOR STRUCTURES DESIGNDan-Jumbo E; Keller R; Westerman B; Kuraishi A; Tsai S W; Wang JBoeing Co.; Stanford, University(SAMPE)

The development of a life prediction technique for characterising the long-term behaviour of composites fabricated from standard modulus carbon fi bre and polyetherketoneketone using Miyano’s Accelerated Testing Methodology, which is based on viscoelastic theory. The accelerated testing is combined with the time temperature superposition principle to relate long-term deformation and strength to short-term accelerated tests over a series of elevated operating temperatures, including repair analysis. Creep master curves are generated from the data for static strength and deformation predictions applicable to a wide range of temperatures and times for design and repair applications. 3 refs.USA


Item 6KGK:Kautschuk Gummi Kunststoffe61, No.12, Dec.2008, p.642-646COMPARISON OF FLUORINATED LIQUID SILICONE RUBBER AND HEAT CURED FLUOROSILICONE ELASTOMERFranssen O; Bosshammer S; Riley G; Toub MMomentive Performance Materials GmbH

The development by Momentive Performance Materials of fully fl uorinated liquid silicone rubber(LSR) compounds with good fuel and oil resistance and processability equivalent to that of commercial standard LSRs is described. Data on the physical properties, fl uid resistance and processability of the new LSRs are presented. The new materials are currently available in the 40-70 Shore A range of durometer and they are expected to play a major role in providing cost-effective options for demanding applications in the automotive and aerospace industries. 12 refs.

EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 7Journal of Applied Polymer Science 111, No.1, 5th Jan.2009, p.228EFFECTS OF PRIOR AGING AT 288 DEG.C IN AIR AND IN ARGON ENVIRONMENTS ON CREEP RESPONSE OF PMR-15 NEAT RESINRuggles-Wrenn M B; Broeckert J LUS,Air Force Institute of Technology

The creep behaviour of PMR-15 polyimide thermoset polymer, aged in air and in argon at 299 deg.C for up to 1000 hours was evaluated. Prior isothermal ageing increased the elastic modulus and decreased the capacity to accumulate creep strain. A rise in Tg with ageing time was attributed to an increase in the crosslink density of the polyimide. 20 refs.USA


Item 8Covina, Ca., SAMPE International Business Offi ce, 2008, 158 papersSAMPE FALL TECHNICAL CONFERENCE 2008. PROCEEDINGS OF A CONFERENCE HELD MEMPHIS, TN., 8-11 SEPT., 2008

MULTIFUNCTIONAL MATERIALS: WORKING SMARTER TOGETHER. (SAMPE)

The Fall 2008 SAMPE Technical Conference consisted of over 150 papers, covering topics which focused on nanocomposites and multifunctional materials. Papers were presented under the following topics: aerospace structures and applications; carbon-carbon composites and foams; composite design and analysis; composite fatigue and fracture; composites for the automotive industry; composites from agricultural products; design for multifunctionality; electromagnetic multifunctional materials; environmental considerations; high temperature resins and composites; infrastructure applications; joints in composite structures; manufacturing and processing advances; multifunctional materials with integral NDE; analysis and characterisation of nanocomposites; applications of nanocomposites; CNT/CNF alignment of nanocomposites; electrical and thermal properties of nanocomposites; fire behaviour of nanocomposites; processing of nanocomposites; nano-industrial applications; nanostructured multifunctional materials; NDE and structural health monitoring; resins and adhesives; sandwich structures; testing of composites; thermomechanical multifunctional materials; and thermoplastic compositesUSA




Item 9Journal of Plastics TechnologyNo.5, 2008, pp.19NEW YARN MATERIALS FOR HIGH-PERFORMANCE FIBRE-REINFORCED COMPOSITES MADE OF STITCHED PREFORMSBeier U; Sandler J K W; Altstaedt V; Spanner H; Weimer C; Roser T; Buchs WBayreuth,University; Eurocopter Deutschland GmbH

The results are reported of a study of the use of innovative low melting temperature polyamide and soluble phenoxy stitching yarns to manufacture cost-reduced textile preforms for liquid composite moulding of high-performance composites for aerospace applications. Tests are carried out on stitched composite panels to assess panel quality, compression performance, apparent interlaminar shear strength and compression after impact behaviour. The innovative yarns, which are compared with conventional polyester stitching yarn, are shown to reduce fi bre undulations in the carbon fi bre-reinforced epoxy composites, allowing further pre-stabilisation of the dry preforms by thermobonding and optimised composite performance. 27 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 10Advanced Composite Materials17, No.3, 2008, p.301-317EVALUATION METHOD OF ADHESIVE FRACTURE TOUGHNESS BASED ON DOUBLE CANTILEVER BEAM (DCB) TESTS INCLUDING RESIDUAL THERMAL STRESSESYokozeki T; Ogasawara TTokyo,University; Japan,Aerospace Exploration Agency

The energy release rate associated with crack growth in adhesive double cantilever beam specimens, including the effects of residual stresses, was formulated using laminate beam theory, and the calculation of the correction for temperature effects based on specimen geometry and thermomechanical properties such as coeffi cient of thermal expansion, is described. The results are compared with those based on fi nite element analysis, and the residual stress effects on the evaluation of adhesive fracture toughness are discussed in terms of aerospace applications of fi bre-reinforced composite laminates. 13 refs.JAPAN


Item 11Journal of Materials Science43, No.20, Oct.2008, p.6714-6723INFLUENCE OF AGING TEMPERATURE, TIME, AND ENVIRONMENT ON THERMO-OXIDATIVE

BEHAVIOR OF PMR-15: NANOMECHANICAL CHARACTERIZATIONPutthanarat S; Tandon G P; Schoeppner G ADayton,University; US,Air Force Research Laboratory

The effects of ageing temperature, ageing time, and ageing environment on the thermo-oxidative behaviour of a commercial high-temperature polyimide resin with applications in the aerospace industry were investigated by optical microscopy and nanoindentation testing to characterise localised mechanical properties and the development and growth of the oxidative layer. The results are discussed in terms of the chemical changes taking place in the polymer during oxidation. 26 refs.USA


Item 12Journal of Materials Science43, No.20, Oct.2008, p.6682-6694COMPOSITE BOND INSPECTIONCrane R L; Dillingham GBrighton Technologies Group Inc.

A brief review on existing methods of adhesive bond strength determination is presented with emphasis on aerospace applications. The recent development of two new methods for the non-destructive inspection of bond strength, laser shock preened proof testing to determine joint properties in situ, which requires access to two surfaces and expensive instrumentation, and the tape peel test, which is an inexpensive method to determine adhesion potential of a composite surface prior to fi nal bond consolidation, are discussed in terms of their scope of application and limitations. 143 refs.USA


Item 13Journal of Materials Science43, No.20, Oct.2008, p.6604-6618VIBRATION DAMPING IN SANDWICH PANELSMaheri M R; Adams R D; Hugon JBristol,University; Alcatel; Kerman,University

The inherent damping mechanism in sandwich panels, including those with both aluminium and carbon fi bre-reinforced composite plastic skins with aluminium honeycomb cores was analysed using the basic laminate theory, a fi rst-order shear deformation theory and a discretisation method. Implementation of the method using a fi nite-element software package to predict the overall damping value of a sandwich honeycomb panel for each specifi c mode is described, and the results are discussed in comparison with experimental data for typical honeycomb structural panels used in aerospace applications. 17 refs.



EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; IRAN; UK; WESTERN EUROPE


Item 14Journal of Materials Science43, No.20, Oct.2008, p.6578-6585VERY STIFF FIBRES WOVEN INTO ENGINEERING’S FUTURE: A LONG-TERM PERSPECTIVEKelly ACambridge,University

Advances in the design, development and properties of fi bre-reinforced composite laminates and the growth in their use since the 1960s are reviewed with emphasis on the use of glass, carbon and synthetic (such as aramid) fi bres for reinforcement, especially for aerospace applications. Problems associated with composite design, testing for fatigue and damage, and environmental concerns such as recycling of composite structures, are also discussed. 2 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 15Polymer Engineering and Science48, No.11, 2008, p.2075-2089CHALLENGES OF SHAPE MEMORY POLYMERS: A REVIEW OF THE PROGRESS TOWARD OVERCOMING SMP’S LIMITATIONSRousseau I AGeneral Motors Corp.

Many applications ranging from biomedical to aerospace have been proposed for the use of shape memory polymers (SMPs). To optimize SMPs properties for appropriately targeting such wide-spreading application requirements, it becomes necessary to understand the structure/property relationships in SMPs. The literature was reviewed and the recent advances made in the development of SMPs were determined to establish guidelines for composition and structure considerations for designing SMPs with targeted chemical, physical, and shape memory (SM) properties. It was concluded that covalently crosslinked glassy thermosets appear to be better SMP candidates because of their intrinsically higher modulus, greater thermal and chemical stability, higher shape fi xity and recovery, and possibly their longer cycle life. However, material design allows for reaching comparable or better properties for all classes of SMPs. This emphasizes that optimisation of SMPs requires application-specifi c molecular, structural, and geometrical design. Current techniques for improving stress recovery and cycle time, which compared to shape memory alloys are the two main limitations of SMPs, are extensively discussed. Understanding the relationships between the composition and structure of an SMP and its SM properties as well as

its limitations enables one to better defi ne the development areas for high performance SMPs. 74 refs.USA


Item 16Polymer Composites 29, No.11, 2008, p.1269EFFECTS OF STORAGE AGING ON THE CURE KINETICS OF T700/BMI PREPREGS FOR ADVANCED COMPOSITESGUO Z

SHANGHAI,UNIVERSITY

The effects of room temperature ageing on the cure kinetics of a bismaleimide (BMI) matrix prepreg have been characterized by different time and storage conditions. The study has focused on the stability of BMI matrix carbon fi bre prepregs, when exposed to controlled environmental conditions before being used in composite manufacturing. The effects of ageing on reactivity, glass transition temperature, and process window have been investigated by differential scanning calorimeter through dynamic and isothermal tests. A theoretical kinetic model for epoxy matrix prepregs, developed in previous studies, has been applied to the cure of both aged and virgin BMI matrix. The model is able to satisfactorily describe the effect of processing variables such as temperature and degree of cure during the curing of the composite under different conditions (curing temperature and heating rate). The effects of diffusion-controlled phenomena on the cure kinetics, associated with changes in glass transition temperature as a function of the degree of cure, have been taken into account in the formulation of an nth-order kinetic model. 12 refs.CHINA


Item 17JEC CompositesNo.44, Oct.2008, p.72-74SERIAL PRODUCTION OF CFRP THERMOPLASTIC PROFILESSpelz Uxperion Aerospace GmbH

The serial production of CFRP thermoplastic profi les for aircraft applications, specifi cally the fi xation rails of the sidewall panels of the Airbus A330/340, by xperion Aerospace GmbH is described. The continuous compression moulding process used is outlined, together with the weight reduction resulting from substitution of aluminium, and the material and process chain, involving polyether-imide. The manufacture of the individual components of the fi xation rails is discussed and subsequent processing is considered.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE




Item 18Journal of Thermoplastic Composite Materials21, No.6, Nov.2008, p.543-555IMPACT OF ND-YAG LASER DRILLING ON THE FATIGUE CHARACTERISTICS OF APC-2A/AS4 THERMOPLASTIC COMPOSITE MATERIALYoung T MLimerick,University

The effect of neodymium-doped-yttrium aluminium garnet laser drilling on the static tensile strength and fatigue life of quasi-isotropic thermoplastic composites APC-2A/AS4 (PEEK thermoplastic composite material in unidirectional form) for aerospace applications was investigated. The holes had diameters of about 120 micrometers and were spaced about 500 micrometers apart. The drilled specimens were inspected using scanning electron microscopy. A maximum stress versus cycles to failure was represented by a power law function, which was used with a reduced coefficient of fatigue strength value to describe the fatigue life characteristics of the laser-drilled specimens. 13 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; IRELAND; WESTERN EUROPE


Item 19ADVANCED COMPOSITE CENTRE FOR INNOVATION AND SCIENCE. Proceedings of the Annual Conference, held University of Bristol, 9th July 2008.Bristol, Advanced Composites Centre for Innovation & Science, 2008, paper 2, pp.5, 30 cm, 012. Downloaded from : www.bris.ac.uk/composites (Accessed 23/7/08)AUXETIC MATERIALS AND STRUCTURESScarpa F(UK,Advanced Composites Centre for Innovation and Science; Bristol,University)

This is a PowerPoint presentation on auxetic materials and structures. It deals with foams, composite laminates and honeycomb structures. Some data on properties are included and some applications indicated.


Item 20Journal of Applied Polymer Science110, No.4, 15th Nov.2008, p.2525-2530FABRICATION AND CHARACTERIZATION OF A NOVEL POLYPROPYLENE/POLYVINYL ALCOHOL/ALUMINUM HYBRID LAYERED ASSEMBLY FOR HIGH-PERFORMANCE FIBROUS INSULATIONWu H; Fan J; Qin X; Mo S; Hinestroza J PHong Kong,Polytechnic University; Shanghai,Donghua University; Cornell University

A hybrid layered assembly based on aluminium-coated PVAL nanofi bre supported on a PP web was fabricated

by electrospinning and physical vapour deposition. Characterisation was carried out using SEM and TEM. IR spectral transmission and water vapour transmission through the materials with or without the nanofi bre of metal coating were determined. Potential applications in protective clothing, sleeping bags, building applications and aircraft are mentioned. 28 refs.CHINA; USA


Item 21Advanced Materials20, No.19, 2nd Oct.2008, p.3759-3763SENSOR PAINTSWolfbeis O SRegensburg,Universitat

Current and future trends in the development of sensor paints, such as pH-, pressure- and temperature-sensitive paints, which respond to a chemical or biochemical parameter with a change in their optical properties are reviewed. The use of various polymers such as ethyl cellulose, poly(dimethylsiloxane), fl uorinated polymethacrylates, polystyrene and poly(trimethylsilylpropyne) are discussed in terms of applications of sensor paints in marine research, high-throughput screening and combinatorial microbiology, medicine, and in the design of aircraft and road vehicles. 30 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 22SAMPE ‘08: Material and Process Innovations: Changing our World. Volume 53. Proceedings of a conference held Long Beach, Ca., 18-22 May, 2008.Covina, Ca., SAMPE International Business Offi ce, 2008, Paper 194, pp.9A NEW NON-METALLIC ACOUSTIC CORE WITH A BURIED SEPTUM FOR APPLICATION IN COMPOSITE ACOUSTIC PANELSWelch J M; Kitt B R; Gallman JSpirit AeroSystems(SAMPE)

A new, non-metallic Acousti-Cap honeycomb core with a permeable plastic septum cap for application in composite acoustic panels for nacelle applications is reported and application possibilities associated with the new core are briefl y discussed. A typical production method for fabricating the acoustic panel using the new core involving perforated sheet construction and cure, perforated sheet to acoustic core bonding and machining, is described and non-destructive testing of a large area acoustic repair to identify any anomalies incurred during bonding is briefl y reported.USA




Item 23SAMPE ‘08: Material and Process Innovations: Changing our World. Volume 53. Proceedings of a conference held Long Beach, Ca., 18-22 May, 2008.Covina, Ca., SAMPE International Business Offi ce, 2008, Paper 191, pp.14PROCESS AND SIMULATION CHAINS FOR ADVANCED TEXTILE STRUCTURAL COMPOSITESDrechsler KStuttgart,University(SAMPE)

Various textile preforms, including braided and stitched textile structures, for composites are described and their use in aerospace and automotive applications is discussed. Methods for simulating the manufacturing process and predicting the mechanical performance of textile-reinforced composites are also considered and some application examples are presented. 15 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 24SAMPE ‘08: Material and Process Innovations: Changing our World. Volume 53. Proceedings of a conference held Long Beach, Ca., 18-22 May, 2008.Covina, Ca., SAMPE International Business Offi ce, 2008, Paper 160, pp.13ATL DESIGN TOOL FOR TOW PATH OPTIMIZATIONWyatt J; Haj-Hariri H; Gruber MVirginia,University; Accudyne Inc.(SAMPE)

An algorithm for automated tape laying is presented and applied to industrial applications, including pad-up geometries in aircraft panels and aircraft cowling, to calculate optimal tow paths, constrained to prevent overlap and to minimise tow gaps. It calculates natural paths, optimises initial conditions for the natural paths, forces tows off natural paths to close remaining gaps and quantifi es various design metrics. These metrics include fi bre strain, compression wrinkle caused by bi-normally bending trajectories and folding wrinkle created by rapid substrate variations. 5 refs.USA


Item 25SAMPE ‘08: Material and Process Innovations: Changing our World. Volume 53. Proceedings of a conference held Long Beach, Ca., 18-22 May, 2008.Covina, Ca., SAMPE International Business Offi ce, 2008, Paper 228, pp.183-D WOVEN PI PREFORM JOINTS: AN ENABLING TECHNOLOGY FOR LARGE

COMPOSITE STRUCTURESchmidt R P; Lee S M; Cooke L MLockheed Martin Aeronautics Co.(SAMPE)

A report is presented on the development of a new class of three-dimensional woven Pi preform composite joints with highly interlocked three-dimensional weave architecture demonstrating a 250 to 300% increase in out of plane load-carrying capacity as compared to conventional two-dimensional composite joint designs. The enabling aspects of the new preforms are described and the advantages of the preforms, which include ease of joining, superior joint strength and process fl exibility, are detailed. Structural applications are demonstrated and validation of various aircraft structures (from risk reduction to full scale level) based on the preforms is covered. 12 refs.USA


Item 26Composites Part A39, No.9, 2008, p.1572-1581MECHANICAL PERFORMANCE OF CARBON FIBRE-REINFORCED COMPOSITES BASED ON PREFORMS STITCHED WITH INNOVATIVE LOW-MELTING TEMPERATURE AND MATRIX SOLUBLE THERMOPLASTIC YARNSBeier U; Wolff-Fabris F; Fischer F; Sandler J K W; Altstadt V; Hulder G; Schmachtenberg E; Spanner H; Weimer C; Roser T; Buchs WBayreuth,University; Erlangen-Nurnberg,University; Eurocopter Deutschland GmbH

In order to achieve a superior overall mechanical performance of composites based on stitched preforms for demanding aircraft applications, innovative thermoplastic stitching yarns are comparatively evaluated in carbon fi bre-reinforced epoxy composites. Low-melting temperature yarns based on polyamide and phenoxy in comparison to a standard polyester yarn allow prestabilisation of the dry preforms by thermobonding and lead to signifi cantly reduced laminate disturbances following liquid composite moulding; thereby minimising the degradation of the resulting composite strength properties. While the softening polyamide yarns allow partial rearrangement of the carbon fi bres during the resin injection process, the dissolution and subsequent phase-separation of the phenoxy can induce a further local toughening of the epoxy matrix. The improvements in overall composite performance when using stitching yarns are partly due to the particular yarn material but also depend on variations in linear yarn density. Last but not least, it is demonstrated that stitching seams close to a bolted joint have only little effect on the bolt bearing strength of the stitched composite whereas seams running directly through the hole and oriented in the load direction induce small degradation of the bolt bearing strength. 32 refs. Copyright (c) 2008 Elsevier Ltd.





Item 27High Performance Polymers20, No.4-5, Aug-Sept.2008, p.461-474THE PERFORMANCE OF NOVEL POLYETHERIMIDES IN A LOW EARTH ORBIT ENVIRONMENTStienstra M M; Dingemans T; Van Eesbeek M; Rohr TDelft,University of Technology; ESA/ESTEC

The performance of a new series of all-aromaticpolyetherimides prepared from either 3,3’,4,4’-biphenyltetracarboxylic dianhydride or 3,3’,4,4’-oxydiphthalic dianhydride and diamines consisting of 1,2 or 3 additional aryloxy units with either para, meta or ortho substitutions was investigated under simulated low Earth orbit conditions. The effect of polymer backbone structure on the thermooptical stability of the polyetherimides under simulated UV radiation and atomic oxygen exposure was examined and the performance of these new polymers compared with that of Kapton and Upilex to assess their suitability for space applications. 9 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; WESTERN EUROPE


Item 28International Journal of Adhesion and Adhesives29, No.1, 2009, p.77-90ENVIRONMENTAL EFFECTS ON THE AGEING OF EPOXY ADHESIVE JOINTSDoyle G; Pethrick R AStrathclyde,University

Adhesive bonded joints are exposed to a range of different environments in aerospace applications. This paper reports dielectric and mechanical analysis of aluminium-epoxy bonded adhesives joints exposed to de-ionized water, aqueous urea solution and salt water at 65 deg.C. The changes observed are the results of plasticisation and corrosion. In the case of the aqueous urea solution, passivation of the oxide by the urea reduced the rate of corrosion. Sea water contains mobile ions and a new feature is detected associated with fi liform corrosion. The non-polar media aviation fuel and hydraulic fl uid are able to plasticise the adhesive and there is a consequent reduction in the strength of the joint. Propylene glycol, although it is polar solvent, produces limited plasticisation and degradation of the joints. Dichloromethane was very aggressive and produced a rapid loss of strength of the joints. 23 refs. Copyright (c) 2008 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 29Future MaterialsSept.2008, p.8-9‘NANONET’ MOVES FLEXIBLE ELECTRONICS CLOSER TO REALITY

Researchers have overcome a major obstacle in producing transistors from networks of carbon nanotubes, a technology that could make it possible to print circuits on plastic sheets for applications including flexible displays and an electronic skin to cover an entire aircraft to monitor crack formation. The so-called “nanonet” technology - circuits made of numerous carbon nanotubes randomly overlapping in a fi shnet-like structure - has been plagued by a critical fl aw: the network is contaminated with metallic nanotubes that cause short circuits. The discovery solves this problem by cutting the nanonet into strips, preventing short circuits by breaking the path of metallic nanotubes.

I l l i n o i s U n ive r s i t y a t U r b a n a - C h a m p a i g n ; Purdue,UniversityUSA


Item 30Reinforced Plastics52, No.8, Sept.2008, p.34-39NEW RECIPES FOR SMC INNOVATIONMcConnell V P

SMC formulations continue to abound in answer to a diverse range of applications. Automotive applications form the largest market for SMC, and over the past fi ve years, automotive SMC recipes have continued to meet and enhance this segment’s performance requirements. Among those are toughness, low density, low profi le, conductivity, in-mould colouring and coating and powder priming. Greener, more environmentally friendly SMCs are defi nitely making news, and Ashland has been a pioneer in this regard. Its Envirez 1807 polyester resin made with a 75/17/8% content ratio of petroleum, soybean oil and ethanol has been used since 2002 in Class A exterior styling panels on all John Deere combines, as well as many of the OEM’s tractor models and hay balers. The National Composite Center is looking at reinforcing structural SMC with biomaterials such as natural fi bre and recyclate. Hexcel is making big news with its application of HexMC carbon fi bre SMC in the large window frames on Boeing’s new 787 Dreamliner commercial aircraft. With base resin and compound prices rising, along with costs for the energy to conduct processing, some moulders are extending their technology grasp by adding in-house compounding.WORLD




Item 31ANTEC 2008. Proceedings of the 66th SPE Annual Technical Conference held Milwaukee, Wi., 4th-8th May 2008.Brookfi eld, Ct., SPE, 2008, p.1977-1981IMPROVING THE THERMAL CONDUCTIVITY OF EPOXY HYBRID NANOCOMPOSITES FOR AEROSPACE APPLICATIONSMovva S; Guerra D; Zhi-qi Cai; Yunior Hioe; Lee L J; Castro JOhio,State University(SPE)

The poor thermal conductivity of polymer based composites has long been a deterrent to their increased use in high end aerospace applications. In this study, the thermal conductivity of Epoxy-Carbon fi bre composites is improved dramatically by a novel method of incorporating carbon nanoparticles into the system. A comprehensive study of the preparation and properties of the highly thermally conductive Epoxy-Carbon fibre-Carbon nanofi bre composites is presented. 7 refs.USA


Item 32ANTEC 2008. Proceedings of the 66th SPE Annual Technical Conference held Milwaukee, Wi., 4th-8th May 2008.Brookfi eld, Ct., SPE, 2008, p.1256-1259IMPROVING ADHESION PERFORMANCE BETWEEN LOW SURFACE TENSION COMPOSITE AND DISSIMILAR SUBSTRATESWolf R AEnercon Industries Corp.(SPE)

The growing demand for high performance plastic components for automobile, aerospace, medical and electronic applications has made the job of formulating paints, adhesives and coatings more challenging. Composite plastics having low surface energies but which deliver high-strength, low-weight performance are becoming more prevalent. Adhesion to the surfaces of these composites, as well as between dissimilar high performance materials, is being solved by atmospheric pretreatment technologies. This paper links specifi c atmospheric surface pretreatment improvements in adhesion to an array of composite and dissimilar materials. 2 refs.USA


Item 33Chemical WeeklyLIV, No.1, 19th Aug.2008, p.174NEW NANOMATERIAL MAKES PLASTIC STIFFER, LIGHTER AND STRONGER

It is briefl y reported that a Michigan State University research team has developed a nanomaterial that makes plastic stiffer, lighter and stronger. The material xGnP Exfoliated Graphite NanoPlatelets will be instrumental in the development of new and expanded applications in the aerospace, automotive and packaging industries. The nano-scale material, which is electrically and thermally conductive, has reduced flammability and barrier properties. The graphene nanoparticles are being manufactured by a new startup company, XG Sciences, which has an exclusive licence to manufacture the material. The researchers are already looking ahead to more uses for the product, such as recyclable, economical or lightweight units to store hydrogen for the next generation of fuel cell-powered autos. Attention is being directed to high-end applications where substantial changes can be made in the way electronics, fuel cells, batteries and solar cells perform as a result of using the material.

Michigan,State UniversityUSA


Item 34Advanced Materials20, No.11, 4th June 2008, p.2074-2079ACTUATING SINGLE WALL CARBON NANOTUBE-POLYMER COMPOSITES: INTRINSIC UNIMORPHSCheol Park; Jin Ho Kang; Harrison J S; Costen R C; Lowther S EUS,National Institute of Aerospace; US,NASA,Langley Research Center

An actuating single-walled carbon nanotube(SWNT)/polyimide (Langley Research Center-Electroactive polyimide) composite was developed that exhibited a large strain (about 2.6%) at a low driving voltage (less than 1 MV/m), while possessing excellent mechanical and thermal properties. The strain energy density was at least an order of magnitude greater than any state-of-the-art polymeric materials reported. The actuating characteristic mainly originated from the electrostrictive contribution, presumably due to interfacial polarisation. The composite intrinsically formed a unimorph during the fabrication process to actuate without the need for additional inactive layers. The tunable multifunctionality and structural reinforcement achieved in these composites could contribute to the design of intelligent and durable components for future aerospace vehicles as well as terrestrial applications. 27 refs.

USAAccession no.1024215

Item 35Revista de Plasticos Modernos95, No.624, June 2008, p.479-488Spanish



RESIN FILM INFUSION FOR AIRCRAFT APPLICATIONSLopez-Quintana S; Leal L; Casado J; Poveda J; Diez S; De Benito ACIDAUT; Aries Complex SA

A report is presented on the manufacture of aircraft using the resin fi lm infusion process. 26 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; SPAIN; WESTERN EUROPE


Item 36High-Performance Composites16, No.4, July 2008, p.72-75ASSESSING CONVENTIONAL AND ADVANCED NDI FOR COMPOSITE AIRCRAFTRoach D

The rapidly increasing use of composites as structural aircraft materials has brought with it the challenge of making sure damage inspection can keep pace. Accurate non-destructive inspection (NDI) methods are a necessity to ensure aircraft airworthiness and passenger safety. Over the last several years, a series of experiments have been designed and implemented to assess how well both conventional and advanced NDI techniques can detect voids, disbonds, delaminations and impact damage in honeycomb structure, solid laminates and adhesively bonded structures. The test programme, called Composite Flaw Detection Experiments, was undertaken at the Federal Aviation Admin. Airworthiness Assurance NDI Validation Center (AANC), operated and staffed by Sandia National Laboratories. Many of the AANC composites activities are conducted under the auspices of the Commercial Aircraft Composite Repair Committee (CACRC). This article discusses the CACRC’s Inspection Task Group’s Probability of Detection experiments, some of the results gathered thus far, and potential applications of new technology for effective NDI on composites-intensive aircraft as they enter commercial service.

US,Federal Aviation AdministrationUSA


Item 37Journal of Applied Polymer Science109, No.3, 5th Aug.2008 p.1625-1634“EX SITUÖ CONCEPT FOR TOUGHENING THE RTMABLE BMI MATRIX COMPOSITES, PART I: IMPROVING THE INTERLAMINAR FRACTURE TOUGHNESSQunfeng Cheng; Zhengping Fang; Xiao-Su Yi; Xuefeng An; Bangming Tang; Yahong XuZhejiang,University; Beijing,National Key Laboratory of Advanced Composites; Beijing,Research Institute of Aerospace Special Materials and Technology

Interlaminar fracture toughness of bismaleimide

composites, as used for aerospace applications, was achieved using an ex-situ resin transfer moulding process with a polyether ketone (PEK)thermoplastic. The process was briefl y described, and samples were evaluated against an untreated base sample using double cantilevered beam tests or end notch fl exure test to assess mode 1 or mode 2 fracture toughness respectively. Fractured samples were examined using scanning electron and optical microscopies, and it was shown plastic deformation and rupture of the PEK phase was responsible for fracture toughening. The toughening mechanism was discussed. 26 refs.CHINA


Item 38Advanced Composite Materials17, No.2, 2008, p.125-137MONITORING OF A CFRP-STIFFENED PANEL MANUFACTURED BY VARTM USING FIBER-OPTIC SENSORSTakeda S; Mizutani T; Nishi T; Uota N; Hirano Y; Iwahori Y; Nagao Y; Takeda NJapan,Aerospace Exploration Agency; Tokyo,University; KADO Corp.

The structural health monitoring of a carbon fibre-reinforced epoxy resin composite laminate panel fabricated via vacuum-assisted resin transfer moulding and containing embedded fi bre Bragg grating (FBG) sensors and optical fi bres was investigated by measurement of residual internal strains during curing and post-curing and during four-point fl exure by means of refl ection spectra of the FBG sensors. The results are discussed in comparison with those obtained using conventional strain gauges and fi nite element analysis, and in terms of potential aerospace applications. 5 refs.JAPAN


Item 39Engineer293, No.7753, 28th July-17th Aug.2008, p.32/34HIGH-FIBRE DIETPierce J

Carbon fi bre is seen as one of the engineering materials of the future, with use expected to increase by 37% over the next four years. Although carbon fi bre is already a success in its present form, attempts are being made to improve manufacturing both the material and parts made from it, to increase its range of applications. Festo produces electric handling solutions for carbon fi bre production and has been carrying out pioneering work with the Textile Composites Group at Manchester University’s School of Materials. The project aims to use Festo’s automation range to cut waste and improve the dimensional strength in carbon fi bre products. Rockwell Automation has recently worked with DuPont on its Kevlar line. During an update of DuPont’s



Maydown Kevlar production plant in Derry, Rockwell replaced the existing dated PLC units with Allen-Bradley ControlLogix PLCs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 40Polymers for Advanced Technologies19, No.6, June 2008, p.609-619NON-HALOGEN FIRE RESISTANT PLASTICS FOR AIRCRAFT INTERIORSLyon R E; Emrick TAtlantic City International Airport; US,Federal Aviation Administration; Massachusetts,University

Strategies for developing fi re-proof aircraft cabin materials are reviewed in the light of environmental legislation restricting the use of halogens in plastics. Fire tests for aircraft materials are indicated and fi re resistance mechanisms of plastics are outlined and described in terms of their effect on heat release rate in fl aming combustion. Finally, the results are reported of fi re tests carried out on non-halogen polymers, including polyphenylsulphone, polyester carbonate and bishydroxydeoxybenzoin-based polyarylate, polyphosphonate and poly(arylate-co-phosphonate), which are optically clear and potentially useful for aircraft cabin applications. 34 refs.USA


Item 41Polymer 49, No.15, 2008, p.3187POLYMER NANOTECHNOLOGY: NANOCOMPOSITESPaul D R; Robeson L MTexas,University at Austin; Lehigh University

In the large field of nanotechnology, polymer matrix based nanocomposites have become a prominent area of current research and development. Exfoliated clay-based nanocomposites have dominated the polymer literature but there are a large number of other signifi cant areas of current and emerging interest. This review will detail the technology involved with exfoliated clay-based nanocomposites and also include other important areas including barrier properties, fl ammability resistance, biomedical applications, electrical/electronic/optoelectronic applications and fuel cell interests. The important question of the “nano-effect’’ of nanoparticle or fi bre inclusion relative to their larger scale counterparts is addressed relative to crystallisation and glass transition behaviour. Of course, other polymer (and composite)-based properties derive benefi ts from nanoscale fi ller or fi bre addition and these are addressed. 284 refs. Copyright (c) 2008 Elsevier Ltd.USA


Item 42Polymer Testing27, No.5, 2008, p.645-652CURE STUDIES ON BIFUNCTIONAL EPOXY MATRICES USING A DOMESTIC MICROWAVE OVENRao S; Rao R M V G KIndia,National Aerospace Laboratories

Three types of bifunctional epoxy-amine matrix systems (two room temperature (RT) cure types and one elevated temperature (ET) cure type), used for aerospace composite applications, were cured in a domestic microwave oven. Microwave cure schedules equivalent to vendor-specifi ed thermal cure schedules were evolved for each resin system, using the glass transition temperature (T”g) as the index of cure completion. Both continuous and pulsed microwave heating modes were employed. The cure status and cure uniformity were assessed using differential scanning calorimetry (DSC) and thermal imaging techniques. The studies showed that pulsed microwave-heated samples exhibited greater degree and uniformity of cure (both in terms of temperature attained and the T”g shown across the samples), compared to the continuous microwave-heated samples for all the resin systems studied. 16 refs. Copyright (c) 2008 Elsevier Ltd.INDIA


Item 43Covina, Ca., SAMPE International Business Offi ce, 2008, 257 papersSAMPE ‘08: Proceedings of a conference held Long Beach, Ca., Volume 53.18-22 May 2008MATERIAL AND PROCESS INNOVATIONS: CHANGING OUR WORLD. (SAMPE)

Over 250 papers dealing with aspects of materials and process innovations were presented at the SAMPE ‘08 conference. Papers were presented under the following main headings: adhesives and bonding; advancements in non-destructive evaluation; aircraft applications technologies; biomaterials; civil engineering and infrastructure; design and analysis; durability, impact and damage; electrical properties of composites and nanocomposites; high temperature resins and coatings; alternative energy applications; automotive and fl ame retardant applications; metals and ceramics; natural materials; nanomaterials; pressure vessel technology; process development and manufacturing; resin infusion; resins and interfaces; sandwich cores; smart materials, including shape memory materials; structural health monitoring; testing and test methods; textile and preform technology; thermoplastics; and tooling, repair and composites affordability.USA




Item 44Journal of Reinforced Plastics and Composites27, No.8, 2008, p.835-850AN EXAMINATION OF FAILURE CRITERIA FOR NOTCHED ORTHOTROPIC CERAMIC MATRIX COMPOSITE LAMINATESYeh H-Y; Murphy K S; Yeh H-LCalifornia,State University; Taiwan,I-Shou University

The application of the Yeh-Stratton failure criterion to newly developed fi bre-reinforced orthotropic ceramic matrix composite laminates based on an aluminoborosilicate fabric impregnated with a silica-alumina matrix was investigated analytically in comparison with experimental test data for laminates containing a central crack under tensile loading and with linear elastic stress models. The results are discussed in comparison with those for graphite fi bre-reinforced epoxy resin composite laminates and in terms of aerospace applications. 19 refs.TAIWAN; USA


Item 45Journal of Materials Chemistry18, No.21, 7th June 2008, p.2475-2482POLYMER NANOENCAPSULATED MESOPOROUS VANADIA WITH UNUSUAL DUCTILITY AT CRYOGENIC TEMPERATURESLeventis N; Sotiriou-Leventis C; Mulik S; Dass A; Schnobrich J; Hobbs A; Fabrizio E F; Luo H; Churu G; Zhang Y; Lu HMissouri,University of Science and Technology; US,NASA,Glenn Research Center; Ohio Aerospace Institute; Oklahoma,State University

An aerogel-like composite material was prepared by casting a conformal diisocyanate-derived polymer coating on the bird-nest like skeletal framework of mesoporous vanadia and its physicochemical and mechanical properties investigated. The nanoencapsulated vanadia exhibited a highly unusual ductility at cryogenic temperatures and did not fail even under high strain compression. The high strength of the nanoencapsulated vanadia was attributed to interlocking of skeletal nanoworms and the high ductility to sintering-like melting and fusion of the polymer coating under compression. The composites are considered suitable for applications, such as armour, cryogenic fuel containers and landing gear for aerospace applications. 28 refs.USA


Item 46SAMPE Journal44, No.3, May-June 2008, p.44-51DEVELOPMENT OF CRYOGENIC COMPOSITE OVER-WRAPPED PRESSURE VESSELS (COPVS)DeLay T; Patterson J; Noorda J; Schneider J

NASA,Marshall Space Flight Center; HyPerComp Engineering Inc.; Mississippi,State University

The results of a feasibility study on the development of cryogenic composite over-wrapped pressure vessels for aerospace and other applications, involving the development and evaluation of materials, test methods and tank design, are reported. The mechanical properties and burst pressures of composite vessels fabricated using carbon fi bre-reinforced epoxy resin or urethane resin systems with aluminium liners of different thicknesses were investigated experimentally at cryogenic temperatures, and the results are discussed in terms of potential savings in weight compared to alternative existing designs. 3 refs.USA


Item 47SAMPE Journal44, No.3, May-June 2008, p.22-34MECHANICAL AND PHYSICAL EVALUATION OF NEW CARBON FIBRE/PEEK COMPOSITES FOR SPACE APPLICATIONSKilroy J P; O’Bradaigh C M; Semprimoschnig C O AComposites Testing Laboratory Ltd.; Eire Composites; European Space Agency

The thermomechanical properties of laminates fabricated using a commercially available carbon fi bre-reinforced poly(etheretherketone) composite pre-impregnated tape processed under pressure-formed autoclave conditions were investigated by tensile, compression, fl exure, in-plane shear and interlaminar shear testing over a wide range of temperatures, and fracture toughness, moisture uptake and DSC measurements. The results are compared with those for laminates fabricated using thermoplastic in-situ automated tape placement and are discussed in terms of the fabrication of large composite structures such as cryogenic fuel tanks for aerospace applications. 19 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; IRELAND; NETHERLANDS; WESTERN EUROPE


Item 48Composites Technology14, No.2, April 2008, p.28-32MICROSPHERES: FILLERS FILLED WITH POSSIBILITIESWood K

The most versatile of fillers available to composites manufacturers are microspheres (also called microballoons), which can provide a range of product enhancements and process improvements. This article provides detailed information about these tiny hollow spheres, under the section headings: chemical composition and construction, density and crush, part processability, component cost, and optimised functionality. Additional boxes include



information on material alternatives, as well as core, acoustic and anti-blast applications.AUSTRALIA; EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; MALAYSIA; SCANDINAVIA; SOUTH KOREA; SWEDEN; UK; USA; WESTERN EUROPE


Item 49Composite Solutions2, No.2, March-April 2008, p.25-27Italian; EnglishCOMPOSITES TO ACCOUNT FOR HALF OF AIRCRAFT WEIGHT

Recent advances in composites for aerospace applications are reported, focusing upon products from Hexcel, including Hexweb HRH-36 Flexcore honeycomb made from Kevlar paper and reinforced with a high temperature-resistant phenolic resin, HexMC, a new kind of cost-effective carbon fibre epoxy moulding concept and Hextool composite tooling material based on HexMC. Some examples of Hexcel’s products on display at the Farnborough Airshow are included.

HexcelAccession no.1020252

Item 50Journal of Materials Chemistry18, No.19, 21st may 2008, p.2262-2267FABRICATION OF CLOSED-CELL POLYIMIDE INVERSE OPAL PHOTONIC CRYSTALS WITH EXCELLENT MECHANICAL PROPERTIES AND THERMAL STABILITYXiao Chen; Lihua Wang; Yongqiang Wen; Yuqi Zhang; Jingxia Wang; Yanlin Song; Lei Jiang; Daoben ZhuBeijing,Institute of Chemistry; Chinese Academy of Sciences; Yan’an,University; Beijing,Graduate University

Closed-cell fl uorinated polyimide inverse opal photonic crystals (IOPC)s were fabricated using core-shell poly(styrene-methyl methacrylate-acrylic acid) colloidal spheres as the template and their heat stabilities, morphologies, photonic band gaps, contact angles, hardnesses and elastic moduli investigated. The mechanism of formation of the closed-cell structure was studied and properties of the closed-cell fl uorinated polyimide IOPCs compared with those of open-cell polyimide IOPCs prepared using PS colloidal spheres as a template. The closed-cell polyimide IOPCs were thermally and mechanically stably and were considered potentially suitable for use in thermal insulation, energy absorption and aerospace applications. 20 refs.CHINA


Item 51JEC CompositesNo.40, May 2008, p.62-64

RESIN FLOW MONITORING IN THE COMPOSITE INFUSION PROCESSCostantino S; Cara FHuntsman Advanced Materials; MAPE Engineering Switzerland SA

The resin infusion process is outlined and two examples of extreme infusion environments, namely high-temperature infusion for composite parts in the aerospace industry and ambient isothermal resin infusion for tooling applications, are described. The fi rst example shows that the resin fl ow front can be detected during high-temperature infusion even through caul plates and the second one demonstrates that active sensors are needed to detect isothermal infusion.SWITZERLAND; WESTERN EUROPE


Item 52Composites Part A39, No.5, 2008, p.705-711EVALUATION OF PREFORMS STITCHED WITH A LOW MELTING-TEMPERATURE THERMOPLASTIC YARN IN CARBON FIBRE-REINFORCED COMPOSITESBeier U; Fischer F; Sandler J K W; Altstadt V; Weimer C; Spanner H; Buchs WBayreuth,University; Eurocopter Deutschland GmbH

A comparative assessment of the infl uence of assembly seams based on two different thermoplastic yarn types on key in-plane and interlaminar properties of carbon fi bre-reinforced epoxy composite is presented. Non-crimped fabric (NCF) composites prepared with a thin low melting-temperature polyamide stitching yarn showed an overall mechanical performance similar to that of the non-stitched equivalent, independent of the stitch geometry. In contrast, comparable composites prepared with a thicker standard unwashed polyester yarn revealed a clear reduction in compression and apparent interlaminar shear strength, with the exact level of degradation depending on the stitch geometry. These deviations in mechanical performance are explained on the basis of a fundamental microstructural difference of the composites following resin transfer moulding. Using the thinner meltable but immiscible polyamide yarn in the stitched preforms instead of the standard polyester yarn appears to reduce localised fi bre undulations; an effect most likely inducing the observed enhancements in key composite properties relevant for aircraft applications. 22 refs. Copyright (c) 2008 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 53Journal of Testing and Evaluation36, No.1, Jan.2008, p.69-72PRESSURE EFFECTS ON OXYGEN CONCENTRATION FLAMMABILITY



THRESHOLDS OF POLYMERIC MATERIALS FOR AEROSPACE APPLICATIONSHirsch D; Williams J; Beeson HUS,NASA,Johnson Space Center

The results are reported of a study of the effects of pressure on the oxygen concentration fl ammability thresholds of a range of polymeric materials, including polyoxymethylene, PE, PTFE, aliphatic polyamide, PCTFE, PDMS, fl uoroelastomer, SBR, nitrile rubber, polychloroprene and EPDM, for aerospace applications. For the range of total pressures tested, the oxygen concentration and oxygen partial pressure fl ammability thresholds show a near linear dependence on total pressure and appear to increase with increasing oxygen concentration (and oxygen partial pressure) thresholds. 10 refs.USA


Item 54Journal of Composite Materials42, No.9, May 2008, p.865-888INVESTIGATION OF SCALING EFFECTS IN FIBER-METAL LAMINATESMcKown S; Cantwell W J; Jones NLiverpool,University

The mechanical properties of scaled specimens of fi bre-metal laminates consisting of an aluminium alloy and a self-reinforced thermoplastic composite based on polypropylene fibres in a polypropylene matrix were investigated by a series of quasi-static tensile and fl exural tests and low-velocity impact tests. Scaling effects in the laminates were studied by comparison of the test results to a scaling law that predicts response parameters based on a simple geometrical relationship of the input parameters, and the results are discussed in terms of engineering applications especially in aerospace components. 25 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 55Polymer Composites29, No.5, 2008, p.473-482MODELING AND ANALYSIS OF THICKNESS GRADIENT AND VARIATIONS IN VACUUM-ASSISTED RESIN TRANSFER MOLDING PROCESSLi J; Zhang C; Liang R; Wang B; Walsh SFlorida A & M University; US,Army Research Laboratory

As vacuum-assisted resin transfer moulding (VARTM) is being increasingly used in aerospace applications, the thickness gradient and variation issues are gaining more attention. Typically, thickness gradient and variations result from the infusion pressure gradient during the process and material variations. Pressure gradient is the driving force

for resin fl ow and the main source of thickness variation. After infusion, an amount of pressure gradient is frozen into the preform, which primarily contributes to the thickness variation. This study investigates the mechanism of the thickness variation dynamic change during the infusion and relaxing/curing processes. A numerical model was developed to track the thickness change of the bagging fi lm free surface. A time-dependent permeability model as a function of compaction pressure was incorporated into an existing resin transfer moulding (RTM) code for obtaining the initial conditions for relaxing/curing process. Control volume (CV) and volume of fl uid (VOF) methods were combined to solve the free surface problem. Experiments were conducted to verify the simulation results. The proposed model was illustrated with a relatively complex part. 17 refs.USA


Item 56Composites Technology14, No.2, Suppl., April 2008, p.92-95SPACE BASES

Composite materials are in service on the International Space Station (ISS) and the equipment sent to explore Mars, and they are in leading contention for a future base on the Moon. Composites’ main competitor in these applications, as elsewhere in the aerospace sector, is aluminium. Twelve composite-overwrapped pressure vessels are currently in orbit, mounted externally on the ISS and protected from micrometeoroids by thin aluminium bumpers. Elsewhere on the ISS, composites form about 40 storage, payload and system racks. The racks were built by Boeing from graphite/epoxy composites by hand layup of a framework of rectangular tubes and I-beam sections as well as skin panels. A relatively new type of composite, featuring a shape-memory polymer matrix, soon might be available to designers of in-space deployment systems for solar arrays, communication antennae and optical systems. One example is the Elastic Memory Composite Hinge created by Composite Technology Development. Carbon fi bre composite technology for unmanned planetary exploration vehicles is well developed. The composites used have to go from the ambient Earth temperature at which they were assembled, to the autoclave temperature of about 177 deg.C, to the extreme cold in space and on Mars.USA


Item 57Composites Technology14, No.2, Suppl., April 2008, p.77-83LAUNCH VEHICLES

One of the earliest applications of space system composites was in strap-on solid rocket motor (SRM) cases for space launch vehicles. Early SRM cases were made from fi breglass/



epoxy and later aramid/epoxy. However, improvements in fi bre properties since then have made carbon/epoxy the SRM material of choice. More recently, composites have been adopted for fi rst-stage boosters, payload adaptors and payload fairings. The design of launch vehicle structures is driven primarily by stiffness. ATK Launch Systems Group produces the GEM (graphite epoxy motor) family for Boeing’s Delta launch vehicles as well as Orion rocket motors for Orbital. Vibration loads are a signifi cant design issue for spacecraft. CSA Engineering’s expertise is viscoelastic materials, or VEMs, which are typically rubbery materials that can reduce vibration amplitudes and peak dynamic stresses. One successful application was a space truss structure experiment. For manned space vehicles with crew modules, composites could eventually fi nd use on NASA’s latest initiative, the Constellation, a Space Shuttle replacement that is expected to return astronauts to Earth’s Moon by 2020.WORLD


Item 58Composites Technology14, No.2, Suppl., April 2008, p.72-75INTERIORS

The continued push for aircraft weight reduction is driving composites growth in cabin applications. Today, composites are used for fl oor and ceiling panels, overhead stowage bins, partitions, window and door surrounds, cabin and galley walls, lavatory modules, food and drink trolleys, cargo hold liners and ventilation ducts. Inroads are also being made into seating components such as rails and pedestals, which are still primarily manufactured of aluminium.WORLD


Item 59Composites Technology14, No.2, Suppl., April 2008, p.52-57CONTROL SURFACES

Composites continue to earn their way into fl ight-critical aircraft components with help from innovative fabrication strategies. The incursion of autoclaved prepreg composites into fl ight control surface structures has a history that goes back several decades. Today, however, a variety of material and process innovations are enabling a dramatic upswing in metal-to-composite conversions. This article presents examples which are representative of many creative applications. These include: composite wings; resin transfer moulded wing spars; one-piece wingskins; vacuum-assisted resin-transfer moulded trailing edges; fi breglass-reinforced thermoplastic leading edges; tail structures; pultruded tail stringers; hand layered rib trusses; and resin transfer moulded prepreg wingtips.WORLD


Item 60Welding International22, No.2, Feb.2008, p.122-129ADHESIVES AND BONDING MATERIALS FOR COMPONENTS IN AVIATION TECHNOLOGYLukina N F; Anikhovskaya L I; Dement’eva L A; Petrova A P; Tyumeneva T YRussia,State Research Centre; All-Russia Scientifi c Research Institute of Aviation Materials

A report is presented on research conducted over many years at the Russian Scientifi c Research Institute of Aviation Materials with the aim of developing suitable adhesives and bonding agents for aviation technology. The materials include high-strength and high-elasticity fi lm and paste-like adhesives for constructional applications, adhesive composite materials based on the adhesive matrix and glass and carbon fi llers, aluminium-polymer composite materials based on aluminium alloys and adhesive prepregs, adhesives for special applications (including heat-resisting, adhesives for rubber engineering applications), self-bonding materials based on aluminium foil, and protective fi lm coatings. Data on the properties of these adhesives are tabulated. It is shown that the adhesives and bonding agents developed ensure effi cient operation of adhesively-bonded joints in the temperature range from -196 to 1600 deg C. 9 refs.RUSSIA


Item 61Polymer International57, No.5, May 2008, p.689-699DIELECTRIC STUDIES OF WATER ABSORPTION AND DESORPTION IN EPOXY RESINS: INFLUENCE OF CURE PROCESS ON BEHAVIOURMcConnell B K; Pethrick R AStrathclyde,University

The results are reported of a study of the mechanism of water uptake and desorption in dicyandiamide- and amine-cured epoxy resin adhesives (AF 163-2K and Epibond 1590) used in aerospace applications. Uptake and loss of moisture are monitored gravimetrically, using broad band dielectric, DMTA and thickness measurements performed as a function of time at various temperatures. Uptake and loss profi les for the adhesives are compared and resorption studies performed on Epibond 1590 adhesive. Differences between the adhesives are rationalised in terms of the different abilities of the matrix to interact with the water molecules. 26 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 62Silicone Elastomers 2008. Proceedings of the Second International Conference held Munich, Germany, 12th-13th March, 2008.



Shawbury, Smithers Rapra, 2008, Paper 3, pp.12REAL FLUOROSILICONES COMBINED WITH LSR. PROCESSING. NEW PRODUCT FAMILY FFSLFranssen O; Bosshammer SMomentive Performance Materials GmbH(Smithers Rapra Technology Ltd.)

The introduction of new fl uorinated silicone liquid rubbers having comparable fl uorine content to fl uorosilicone heat cured elastomers and Shore hardnesses ranging from 40 to 70 is reported and these new fl uorosilicone liquid rubbers are compared with fl uorosilicone heat cured elastomers in the areas of processability, physical properties and fuel and solvent resistance, particular emphasis being placed on requirements for automotive and aerospace applications. 11 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 63Plastics Engineering64, No.3, March 2008, p.10/13OUT OF THIN AIR, AEROGELS EMERGEToensmeier P A

An aerogel is a wispy, foam structure that is more than 99% air. Properties include outstanding insulation and acoustic dampening, hydrophobic or hydrophilic performance, absorption, additive and reinforcement benefi ts in polymers and low dielectric constant. Aerogels are extremely light and particle size is less than 100nm, so they can be used in parts that require transparency or purity. The leading end-use application by far is thermal insulation, which accounted for 57.6% of market value in 2006. One application in which aerogels provide a unique benefi t is "daylighting" - translucent window and roof systems that let fi ltered light into a room with no increase in heating or cooling costs. Aerogels are supplied in various forms. Aspen, whose specialty is insulation, fabricates them mainly in fi brous sheets and blankets, which are installed on products like gas and oil pipelines, used in defence and aerospace applications, or added to cold-weather gear. Other companies like Cabot produce granular products that can be mixed with resins or made into various products.USA


Item 64Machine Design80, No.6, 20th March 2008, p.44/49STRONGER AND LIGHTER Û COMPOSITES MAKE THEIR MARKZweben C

Most engineers likely know that the new Boeing 787 Dreamliner is made primarily of carbon fi bre-reinforced

epoxy composites. Considering that carbon fi bres were fi rst developed in the late 1960s, this is remarkable progress. Carbon-epoxy composites have outstanding properties so it is not surprising that they have become the baseline materials in aerospace and sporting goods. The properties of polymer-matrix composites, metal-matrix composites, carbon matrix composites and ceramic-matrix composites are compared. Industrial and commercial composite applications are discussed.USA


Item 65Progress in Polymer Science33, No.3, 2008, p.289-345PROCESSIBLE POLYAZOMETHINES AND POLYKETANILS: FROM AEROSPACE TO LIGHT-EMITTING DIODES AND OTHER ADVANCED APPLICATIONSIwan A; Sek DPolish Academy of Sciences

Conjugated polymers have attracted widespread interest during the last two decades, because of their useful electronic, optoelectronic, electrochemical and non-linear optical properties. In this paper we discuss synthetic routes (Section 2) and spectroscopic properties (Section 4) of the principal conjugated polymers with imine groups (C=N) in the main chain, such as polyazomethines (Schiff bases) and polyketanils (polyketimines). Special emphasis is put on the molecular and supramolecular engineering approach (Sections 3-7), which allows tuning of processability and special desired properties of these polymers. Selected examples of possible technological applications of conjugated polymers containing imine groups are presented, such as their use as optical pH sensors, detectors, catalyst carriers or light-emitting diodes (Section 4). Additionally, the polyazomethines and polyketanils are thermally stable, making them potential candidate materials for aerospace applications (Section 4.1). Polyazomethines with liquid crystal properties are also considered (Section 5). The paper is completed by discussion of non-covalent interactions between dopant (Lewis and Bronsted acids) and conjugated polymers (polyazomethines and polyketanils) (Sections 3.2 and 7). 185 refs. Copyright (c) 2008 Elsevier Ltd.EASTERN EUROPE; POLAND


Item 66PROTECTING THE SUBSTRATE AND THE ENVIRONMENT. Proceedings of the International Protective Coatings Conference, held Amsterdam, The Netherlands, 24th-25th October, 2007.(Hampton), PRA, 2007, Paper 2, pp.14 WATERBORNE EPOXY TECHNOLOGY AND TOP PERFORMANCE: NO LONGER A FAIRY TALE?



Vandenberghe D; Heine F; Clayes-Bouuaert P; Van Poppel K; Rans M; Frederix AHexion Specialty Chemicals(PRA)

The development of waterborne epoxy binder technologies as a means of attaining volatile organic compound compliance is described. The historic development of waterborne binder families, including the NEW GEN technology, is discussed. The importance of applying the appropriate ‘formulation know-how’ in order to achieve top performance in some key market segments, such as aerospace applications and transportation coatings and primers for the agriculture, construction and earth-moving equipment markets, is highlighted. The performance data presented should help waterborne systems fi nd applications in the most conservative and diffi cult market segments, such as marine coatings. 7 refs.BELGIUM; EU; EUROPEAN COMMUNITY; EUROPEAN ECONOMIC COMMUNITY; EUROPEAN UNION; WESTERN EUROPE; WESTERN EUROPE-GENERAL


Item 67COMPOSITES: ENABLING A NEW ERA IN CIVIL AVIATION. Proceedings of the American Society for Composites:Twenty-second Technical Conference, held University of Washington, Seattle, Wa., 17th-19th Sept.2007.Lancaster, Pa., DEStech Publications, 2007, Paper 164CHARACTERIZATION OF DISCONTINUOUS CARBON FIBER/EPOXY SYSTEMS FOR AEROSPACE APPLICATIONS: PART IFeraboli P; Peitso E; Deleo F; Cleveland T; Graves M; Stickler PWashington,University; Boeing Phantom Works; Boeing Commercial Airplanes(American Society for Composites)

The results are reported of a study of the effect of fi bre length on the mechanical properties of a high-performance SMC composed of discontinuous carbon fibre-epoxy panels obtained from high-grade prepreg for aerospace applications. The tensile, compression and flexural properties of the composites are discussed and comparisons are made with continuous carbon fi bre-reinforced epoxy panels. Fibre distribution in the composites and the effective random nature of the composites are characterised by means of image analysis and testing of tensile specimens cut at 0, 45 and 90 degrees from the longitudinal axis. 16 refs.USA


Item 68COMPOSITES: ENABLING A NEW ERA IN CIVIL AVIATION. Proceedings of the American Society for Composites:Twenty-second Technical Conference,

held University of Washington, Seattle, Wa., 17th-19th Sept.2007.Lancaster, Pa., DEStech Publications, 2007, Paper 90IMPACT DAMAGE MONITORING OF SANDWICH STRUCTURE BY DISTRIBUTED STRAIN MEASUREMENT WITH CM-ORDER SPATIAL RESOLUTIONMinakuchi S; Okabe Y; Takeda NTokyo,University(American Society for Composites)

The development of an impact damage detection system for composite sandwich structures, which uses the specifi c response of a pre-pump pulse Brillouin optical time domain analysis sensing system to non-uniform strain distribution along an optical fi bre, is reported. The system is applied to the detection of non-uniform strain distribution along a dent of the CFRP facesheet of a sandwich panel with an aluminium honeycomb core and is considered suitable for inspecting sandwich structures for aerospace applications. 14 refs.JAPAN


Item 69SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 116, pp.15UPDATES FOR TRANSITION POTENTIAL OF LIGHT WEIGHT COMPOSITE AIRCRAFT & SPACECRAFT THERMAL MANAGEMENT COMPONENTSWatts R; Maxwell G; Steenwyk M; Biels J; Chang S; Carroll TUS,Air Force Research Laboratory; GE Aviation; Touchstone; Triton Systems Inc.(SAMPE)

The U.S. Air Force Research Laboratory Materials and Manufacturing Directorate is continuing to provide revolutionary lightweight hybrid carbon composite processing technology applied to heat transfer applications for aircraft potential transition and more demanding mega watts direct energy cooling. Updates on two key thermal management component areas for payoff, i.e. carbon composite heat exchangers and avionic hybrid carbon enclosures, are provided. The ultimate goal is to develop ‘advanced composite material’ manufacturing options to double the effectiveness of the existing systems and provide new energy sources for the environmental management systems. The transition to space material applications is considered. 7 refs.USA




Item 70SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.COVINA, CA., SAMPE INTERNATIONAL BUSINESS OFFICE, 2007, PAPER 114, PP.12 FORMULATING CHALLENGES IN EPOXY BASED INFUSION SYSTEMS FOR AEROSPACE APPLICATIONSHoge JHuntsman Advanced Materials

(SAMPE)Formulating challenges related to the development of epoxy-based systems for use with the vacuum infusion process for applications in the aerospace industry are discussed. A challenging balance of processing and ultimate physical properties must be met to qualify these systems for aerospace specifi cations. Various diffi culties arise in formulating aerospace infusion systems to meet the complex requirements of the vacuum infusion process and aerospace structural parts. Several opposing property parameters exist such as processing temperature/viscosity vs. pot life, low viscosity vs. high Tg, low viscosity vs. high temperature toughness, and high modulus vs. high toughness. Data are presented and comparisons are made with experimental epoxy blends and curing agents by studying one-part and two-part epoxy systems. Advantages and disadvantages of one- and two-part infusion systems are discussed. The ultimate goal is to develop systems which meet all of the processing and performance requirements for complex aircraft parts. 3 refs.USA


Item 71SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 104, pp.7DAMAGE PREDICTION OF CARBON/EPOXY COMPOSITE PANELS SUBJECTED TO BALLISTIC IMPACTZhiqiang Wang; Gang Qian; Ming XieGE Global Research Centre; GE Infrastructure-Aviation(SAMPE)

Damage resistance capability of carbon fi bre composite panels subjected to ballistic impact was investigated for potential aerospace applications. Numerical simulations were carried out to predict impact gouging behaviour and perforation limit with different panel thickness. The simulations were conducted with the explicit fi nite element code LS-DYNA, where a special user material subroutine was implemented to capture the carbon/epoxy composite material behaviour. The numerical results were correlated

with panel impact test data with different thicknesses and impact velocities. Results showed that the panel gouge depth and perforation limit were predicted with reasonable accuracy. Such an analytical prediction provided the possibility of signifi cantly reducing experimental cost in the investigation of composite impact performance. 11 refs.USA


Item 72SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.COVINA, CA., SAMPE INTERNATIONAL BUSINESS OFFICE, 2007, PAPER 101, PP.15 ANALYTICAL PREDICTIONS OF FAILURE OF A BOLTED JOINT IN COMPOSITE PANEL DUE TO DIRECT IMPACTGagel J; Ming Xi; Vijayvargiya A; Reddy VGE Infrastructure-Aviation(SAMPE)

Composite materials are used for aerospace applications because of their lightweight and high strength properties, but attachment design on a composite structure remains a great challenge. A metallic bracket, rather than an integral composite fl ange, often has to be used to attach two structures. In this study, a numerical analysis using LS-DYNA software was performed to simulate a metallic bracket bolted to a composite panel and subjected to a ballistic impact from a metallic projectile. A parametric study of the ballistic impact simulation was conducted, which included various impact velocities and impact locations. The effects of fi nite element mesh density were also investigated. Predictions on bolted joint performance are presented. 5 refs.INDIA; USA


Item 73SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 96, pp.9ALTERNATIVE ALKYNE-BASED MATERIALS FOR HIGH TEMPERATURE MATERIALS APPLICATIONSMorgan A BDayton,University,Research Institute(SAMPE)

Alkyne-containing monomers are currently used in the manufacture of some polyimide-based composites where a high level of crosslinking and thermal stability is required



in the end-use application. A variety of alkyne-based materials are made effi ciently from brominated aromatic starting materials, which may be useful for this application. The materials discussed in this paper were originally designed as high carbon char-forming materials for rocket booster ablative and fl ame retardancy applications, but through the control of chemical structure it was found that the alkyne crosslinking reaction could be raised or lowered, and different levels of carbon char could be generated. The versatility of organic synthesis allows for the creation of multi-alkyne containing structures which are highly soluble in a variety of solvents and whose alkyne crosslinking temperature can be tailored. The synthesis of these materials is described and possible advantages and disadvantages of these materials for the manufacture of new aerospace materials are considered. 6 refs.USA


Item 74SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 67, pp.12THERMO-MECHANICAL BEHAVIOR OF ADAPTIVE POLYMER FOAMDi Prima M A; Lesniewski M; Gall K; McDowell D L; Sanderson T; Campbell DGeorgia,Institute of Technology; Raytheon Missile Systems Co.; Composite Technology Development Inc.(SAMPE)

Adaptive (shape memory) polymer foams have potential aerospace applications, but their thermomechanical behaviour under deformation conditions is not well understood. Epoxy resin adaptive foams with an average relative density near 20% were examined by deforming them under conditions of varying stress, strain and temperature. The Tg of the foam was measured to be 90 deg C, while compression and tensile tests were performed at temperatures between 25 and 125 deg C. Tensile strain to failure was measured to probe the foam’s maximum recovery limits in temperature and strain space. Compression tests were performed to examine material compressibility as a function of temperature. These foams were compacted up to 80% and still experienced full strain recovery over multiple cycles. Both tensile strain to failure and cyclic compression recovery tests revealed that deforming at 80 deg C minimised damage and maximised macroscopic strain recovery. Deformation temperatures above or below this optimal value led to lower failure strains in tension and the accumulation of permanent strains in cyclic compression. Micro-computed tomography(microCT) scans of the foam at various compressed states were used to understand foam deformation mechanisms. The microCT studies revealed the bending, buckling and collapse of cells

with increasing compression, consistent with published numerical simulations. 38 refs.USA


Item 75SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 66, pp.11ACTIVE MULTISTABLE STRUCTURES FOR MORPHING APPLICATIONSSchultz M RComposite Technology Development Inc.(SAMPE)

Multistable structural components, i.e. components that have more than one stable equilibrium shape, can be benefi cial in creating morphing structures because power is only required to transform the structure between shapes, not to hold the structure in the new shape. As such, the use of multistable structural components can lead to reduced power requirements, and can provide a series of set operating shapes. This paper examines the use of piezocomposite actuators to bring about shape change in multistable structures. Two types of structures are considered, i.e. simple multistable cross-ply composite plates and a type of multistable airfoil-like twisting device that is made by combining two pre-curved shells. These structures are both based on graphite-epoxy resin composites. Piezocomposite actuators were shown to be effective in actively transforming both types of multistable structures at frequencies up to 10 Hz. It is shown that, in general, the combination of multistable structures with piezocomposite actuators can produce interesting active morphing structures. 18 refs.USA


Item 76SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.COVINA, CA., SAMPE INTERNATIONAL BUSINESS OFFICE, 2007, PAPER 63, PP.6 CHARACTERIZATION OF SHEAR DEFORMATION AND STRAIN RECOVERY BEHAVIOR IN SHAPE MEMORY POLYMERSKhan F; Jeong-Hoi Koo; Monk D; Eisbrenner EMiami,University(SAMPE)

The large strain deformation behaviour of a styrene-based shape memory polymer(SMP), Verifl ex, was investigated in tensile and shear loading conditions with the aim



of characterising the mechanical properties. Particular attention was paid to the recovery behaviour, which was critical for the development of new SMP-based applications, and the effect of fi ller loading. Magnetite and iron spherical nanoparticles were used as fi llers. The magnetite-fi lled samples were prepared to allow the investigation of magnetic induction-based heating to serve as a trigger for the thermally-activated SMP. Very favourable response times were observed using this technique. The iron-fi lled samples were prepared to render the polymer electrically conductive. Testing of the materials was performed in tensile and shear test conditions at room and elevated temperatures. Following tensile and shear deformation to lock-in plastic strain, the SMP exhibited a rapid rise in the recovery force following the application of a thermal trigger. Full recovery of the plastic strain was observed. The data should provide information on matrix-fi ller interaction and permit constitutive modelling through an investigation of the elastic, inelastic, and recovery deformation response of the SMP. 6 refs.USA


Item 77SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 62, pp.13THERMAL PROPERTIES OF AN OPEN CELL EPOXY SHAPE MEMORY POLYMER FOAMSanderson T; Di Prima M A; Gall K; Lamb J; Arzberger SArizona,University; Georgia,Institute of Technology; Raytheon Missile Systems Co.; Composite Technology Development Inc.(SAMPE)

The thermal properties of an epoxy SMF (shape memory polymer foam) were measured and reported for a foam of 18% density, and it was found that the thermal diffusivity increased by an order of magnitude in going from fully expanded to fully compressed, while the thermal conductivity increased by almost as much. Under the same conditions, the specifi c heat increased by less than 50% on average, while the density increased by a factor of about 3.5. Overall, the properties were similar to those of a thermally-insulating material, as expected. A simple transient thermal analysis was then carried out for using this material with an electric resistance heating element as the skin of a morphing aircraft wing. At steady state, for a 9.5 mm thick SMF skin, the ratio of the maximum to minimum temperature within the material was found to be 21 for the compressed foam and 69 for the expanded foam, which was excessive for practical applications. A dense network of electric resistance heating elements embedded within the material would be required. The analytical results presented emphasised the need to develop

volumetric material heating systems if shape memory polymers were to be used extensively for morphing aircraft applications. 17 refs.USA


Item 78SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 52, pp.12STRENGTH AND CORROSION RESISTANCE PROPERTIES OF A NEW GENERATION OF HIGH PERFORMANCE R-GLASS REINFORCEMENTSYing Peng; Spoo K; Hartman DOwens-Corning Science & Technology Center(SAMPE)

A new high-performance R-glass fi bre (HiPer-Tex), which promises to be a cost-effective high-strength reinforcement in numerous application areas, is shown to exhibit superior corrosion resistance in a variety of common corrosive media. Applications that demand higher tensile strength or modulus, e.g. wind turbine blades, pressure vessels, ballistic panels, and numerous aerospace applications, are discussed. In applications such as these, meeting secondary requirements such as corrosion resistance is absolutely necessary. The data demonstrate that the long-term performance of HiPer-Tex R-glass fi bre in corrosive environments should meet or exceed the requirements of these and other applications. Comparison is made with Advantex boron-free E-glass fi bre. 10 refs.USA


Item 79Machine Design80, No.4, 21st Feb.2008, p.74/76WHERE RETICULATED POLYURETHANE FOAM’S A FITGliganic RCrest Foam Industries Inc.

Reticulated PU foam is strong enough to handle industrial applications ranging from sound and vibration absorption to spark proofi ng fuel tanks in aircraft and race cars. The fl exible foams feature an open-pore structure with pore sizes and densities engineered specifi cally to suppress explosions and mitigate noise. Foam under compression, as in gasketing applications, can be made with a void volume as high as 98%. The production process for PU used as a fi lter or gasket can be tweaked to optimise properties for a particular application. Typical pore sizes for reticulated PU foams used industrially range from 4 to 120 ppi. In addition to use as sealants or gaskets, reticulated PU foams can be



specifi ed as dielectric insulators. They can be embedded with conductive metal particles in cases where a gasket or seal must also serve as a conductive material, as when providing a ground connection.USA


Item 80Lancaster, Pa., DEStech Publications, 2007, 162 PapersProceedings of the American Society for Composites: Twenty-second Technical Conference, held University of Washington, Seattle, Wa., 17th-19th Sept.2007COMPOSITES: ENABLING A NEW ERA IN CIVIL AVIATION. Edited by: Feraboli P; Stickler P(American Society for Composites)

168 original research papers were presented in September 2007 at the 22nd technical conference of the American Society for Composites, held in conjunction with the Materials Science Department at the University of Washington in Seattle. Research papers are presented by authors from Japan, the USA and Europe, offering technical insights into the design and applications of traditional composite materials, nanocomposites, natural composites, and emerging hybrids. A special session is devoted to trends in composite education and training, featuring input from Boeing company personnel. Papers are organised under the following headings: T. K. O’Brien Honorary Symposium; education; laminate behaviour and analysis; crashworthiness; characterisation and processing; hybrid laminates; applications in aeronautics and wind turbines ; thermoplastics; damage tolerance; bonded joints and repairs; nanocomposites; foam; multifunctional; health monitoring; bioapplications; natural composites; and new material forms.USA


Item 81Covina, Ca., SAMPE International Business Offi ce, 2007, 146 papers.Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st.Nov.2007SAMPE FALL TECHNICAL CONFERENCE 2007: FROM ART TO SCIENCE: ADVANCING MATERIALS AND PROCESS ENGINEERING. (SAMPE)

The Fall 2007 SAMPE Technical Conference consisted of over 140 papers focusing on four emerging tracks in the fi eld of materials today: nanotechnology (characterisation, devices and applications, electrical properties, synthesis and processing); propulsion (high temperature technologies, composite materials, high temperature resins, textile performing, and impact and dynamic behaviour); computational materials science and morphing (morphing and adaptive structures, novel resins and reinforcements).

Other topics covered include fire protection, liquid moulding, adhesive bonding, composite repair, high performance fibres, resin and process development, new metallic materials, aerospace coatings, spacecraft materials, and testing methods.USA


Item 82Rubber Fibres Plastics International3, No.1, Jan.2008, p.34-40FULLY FLUORINATED LSR - A NEW PRODUCT FAMILYFranssen O; Bosshammer S; Riley G; Toub MMomentive Performance Materials GmbH; Momentive Performance Materials Inc.

The introduction of a fl uorinated liquid silicone rubber with a comparable fl uorine content to fl uorosilicone high consistency elastomer is reported and a comparison is made of the processability, physical properties, fuel resistance and solvent resistance of these silicone rubbers. Emphasis is placed on requirements for automotive and aerospace applications and the development of a new self-bleeding grade (FFSL 7286/40) is reported. 11 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; USA; WESTERN EUROPE


Item 83Journal of Materials Science43, No.1, Jan.2008, p.413-416PHYSICAL PROPERTIES OF A REACTIVE GRAPHITE NANOFIBER-REINFORCED EPOXYJana S; Zhong W-HWashington State,University

The dielectric constants, electrical and thermal properties of composites of epoxy resin with small proportions of reactive graphitic nanofi bres were investigated after curing by surface conductivity, complex dielectric permittivity (via broadband dielectric spectroscopy) and thermal conductivity measurements. The effects of different proportions of reactive graphitic nanofi bres on the properties of the epoxy resin matrix are discussed in terms of potential applications such as aerospace and wind energy. 16 refs.USA


Item 84Nippon Gomu Kyokaishi80, No.5, May 2007, p.184-190JapaneseCHARACTERISTIC FEATURE AND APPLICATIONS OF CONDUCTING POLYMERSKuramoto NYamagata,University



The characteristics and applications of conducting polymers, such as polyaniline, polypyrrole and polythiophene derivatives, are described. Emphasis appears to be on polyaniline. 24 refs.JAPAN


Item 85High Performance and Speciality Elastomers 2007. Proceedings of the 4th International Conference, held Frankfurt, Germany, 5th-6th Dec.2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 20, pp.5MODIFICATION OF ELASTOMER FRICTION BY ION BOMBARDMENTBielinski D M; Pieczynska D; Jagielski JStomil; Lodz,Technical University; Warsaw,Institute of Electronic Materials Technology(Smithers Rapra Technology Ltd.)

Various elastomers for sealing applications in aerospace and automotive applications were subjected to ion beam bombardment with helium or argon ion beams and the effect of ion beam bombardment on the friction coeffi cient, surface geometry, wear resistance and microhardness of the surface treated rubbers investigated. Rubbers studied were nitrile rubber, polychloroprene, silicone rubber, thermoplastic PU elastomer and thermoplastic polyether-amide elastomer (Pebax 5533 SN 01). Comparisons were made with rubbers treated by solution sulphonation and chlorination. 11 refs.EASTERN EUROPE; POLAND


Item 86High Performance and Speciality Elastomers 2007. Proceedings of the 4th International Conference, held Frankfurt, Germany, 5th-6th Dec.2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 10, pp.12INNOVATIONS IN FLUORINATED LIQUID SILICONE RUBBERFranssen O; Bosshammer SMomentive Performance Materials GmbH(Smithers Rapra Technology Ltd.)

A new line of novel fl uorinated liquid silicone rubbers having a comparable fl uorine content to fl uorosilicone heat cured elastomers is reported and compared with fluorosilicone heat cured elastomer in the areas of processability, physical properties, fuel resistance and solvent resistance, with emphasis on requirements for automotive and aerospace applications. The new materials are currently available in the 40 to 70 Shore A range of durometer. 11 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 87SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 11, pp.18SURFACE TREATMENT AND APPLICATION PROCESSES FOR EPOXY BONDING TO BISMALEIMIDE COMPOSITESRider A N; Wang C H; Chang P; Brack NAustralia,Defence Science & Technology Org.(SAMPE)

The results are reported of an investigation into a range of candidate structural adhesives for use in the repair of high temperature carbon/bismaleimide composites. Adhesives evaluated include an epoxy resin with good high temperature strength, a fi lm adhesive in paste form with fl exibility in curing below 177 degrees C and a new generation bismaleimide fi lm adhesive for high temperature composite applications. The effect of factors, such as adhesive solvent levels, surface treatment and adherend moisture levels, on voiding levels are examined, methods of reducing voiding levels are considered and processes to provide reliable adhesion are evaluated. 8 refs.AUSTRALIA


Item 88SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 10, pp.14STRUCTURAL REPAIR TECHNIQUES FOR HIGHLY-LOADED CARBON/BMI COMPOSITESWang C H; Rider A N; Chang P; Charon A; Baker AAustralia,Defence Science & Technology Org.(SAMPE)

The results are reported of an experimental and analytical investigation carried out to evaluate the performance of mechanically fastened and adhesively bonded repairs to carbon/bismaleimide composites for aircraft applications at an elevated temperature of 177 degrees C when repairs are cured close to the operating temperature. Types of repairs under consideration are fastened patch repair, bonded patch repair, bonded scarf joint, multi-row bolted repair and bonded doubler-scarf repair. 16 refs.AUSTRALIA


Item 89SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th



Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 7, pp.7SILYLATED POLYURETHANE ADHESIVES: NEXT GENERATION JET FUEL & HYDRAULIC FLUID RESISTANT PSA’SGriswold R; Frye RMomentive Performance Materials(SAMPE)

Typical physical properties, adhesive properties and solvent resistance of novel pressure-sensitive adhesives based on silylated PUs, which offer unique resistance to jet fuel and hydraulic fl uids in aerospace labelling applications, are described. These adhesives are isocyanate-free and extend temperature and shear resistance, bridging the gap between conventional organic adhesives and silicone pressure-sensitive adhesives. 5 refs.USA


Item 90SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 2, pp.18LASER PRETREATMENT OF SURFACES FOR ADHESIVE BONDINGWalters C T; Smith J AWalters C.,Associates; Dayton,University,Research Institute(SAMPE)

An investigation was carried out into the possible use of short pulse Nd:YAG laser devices for pretreating metal and composite surfaces for aerospace applications prior to adhesive bonding, A series of mechanical tests (wedge and lap shear strength tests) were performed on panels bonded after laser pretreatment of their surfaces and the results compared with those pretreated by conventional grit blasting and solvent wipe. Substrates tested were aluminium alloys and carbon fi bre/epoxy composites. The data obtained revealed that, generally, the laser pretreated adherends performed as well as the solvent-wiped and grit-blasted control adherends. 11 refs.USA


Item 91SAMPE Fall Technical Conference: From Art to Science: Advancing Materials and Process Engineering. Proceedings of a conference held Cincinnati, Oh., 29th Oct.-1st Nov.2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 1, pp.15IMPROVEMENTS IN SOL-GEL SURFACE

PREPARATION METHODS FOR METAL BONDING APPLICATIONSBlohowiak K Y; Grob J; Grace W B; Cejka N; Berg DBoeing Co.(SAMPE)

Improvements in the use of sol-gel methods, based on the Boegel -EPH system, which is currently formulated as a four-part kit, for preparing metal surfaces for bonding with 121 and 177 degrees C-cure epoxy adhesives are discussed. These improvements include the use of four new expanded abrasion sandpaper materials and techniques and use of a two-component sol-gel kit. Tests which measure adhesive durability and strength and are sensitivity to surface changes (crack extension, wedge and peel tests) are employed to compare the sandpapers and performance and durability tests are carried out on bonded aluminium specimens to validate the equivalent performance of the two- and four-part sol-gel kits after ageing. 9 refs.USA


Item 92Journal of Polymer Engineering27, No.8, 2007, p.565-582ANALYSIS OF CURE REACTION KINETICS OF ARAMID/TOUGHENED-EPOXY PREPREG SYSTEM AIMING AT PROCESSING OF COMPOSITE MATERIAL FOR STRUCTURAL APPLICATIONSSoahib A; Zhe M; Irfan YLyon,Universite Claude Bernard; Lyon,Ecole Centrale; Pakistan,Institute of Space Technology

The cure reaction kinetics and rheological properties of a prepreg system based on an aramid fabric as reinforcement impregnated with a toughened bisphenol-A/epichlorohydrin-derived epoxy resin using an aliphatic amine curing agent were investigated by dynamic DSC, rheometry and dynamic and isothermal DMA techniques. The results are discussed in terms of optimisation of the curing process for fabrication of structural components with aerospace applications. 27 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; PAKISTAN; WESTERN EUROPE


Item 93Composites Technology13, No.6, Suppl., Dec.2007, p.6/45COMPOSITES FLY HIGH AROUND THE WORLD

This comprehensive article provides an overview of the composites industry. Fibre reinforcements, matrix resins, nanotechnology, part design criteria, fabrication methods, tooling considerations and applications are discussed.



WORLD


Item 94High-Performance Composites15, No.6, Nov.2007, p.26-30CARBON FIBER STOPPING POWERWood K

Low weight, thermal shock resistance and extreme strength drive growth of carbon-reinforced friction products and materials in brake applications. Driven by growth in the aerospace sector as well as the inherent performance characteristics of the material, carbon-reinforced composites, such as carbon/carbon, are expected to offer the best opportunity for growth in the North American friction market, according to BCC Research. C/C is a composite made from a carbon fi bre reinforcement impregnated with a carbon matrix by a lengthy and expensive process that involves exposure to extreme heat (pyrolysis). The result is an extremely lightweight composite characterised by a very low coeffi cient of thermal expansion and excellent resistance to the extremely high temperatures generated in braking applications. Production costs associated with the manufacture of C/C friction products are very high. Over the past fi ve years, major producers of friction products and materials have designed and patented a number of process variations, including advancements in antioxidant systems, process automation, fi bre orientation, densifi cation methods and process fl ow, all in an effort to reduce manufacturing time and costs while maintaining thermal and strength properties.USA


Item 95Plastics EngineeringNo.11, Nov.2007, p.50-54NANOCOMPOSITES FAST TRACK TO COMMERCIALISATIONRamasubramanian H Frost & Sullivan Ltd.

An overview is presented of Frost & Sullivan’s recent global study on nanocomposites, which are currently entering an important phase in their product life cycle, moving from innovation to growth. The focus of the overview is on technical challenges, commercialisation challenges and issues, health and safety aspects and the markets for nanoclays and nanotubes.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 96SAMPE Journal43, No.6, Nov.-Dec.2007, p.53-60HIGH PERFORMANCE 3-D BRAIDED FIBER

PREFORMS: DESIGN AND MANUFACTURING ADVANCEMENTS FOR COMPLEX COMPOSITE STRUCTURESMungalov D; Duke P; Bogdanovich A3TEX Inc.

Recent advances in the design and manufacture of three-dimensional braided products fabricated on three-dimensional rotary braiding machines are reported, focusing upon large cross-section integral carbon fi bre Hat-stiffeners primarily intended for aircraft applications and carbon or glass fi bre truss-like integral structures for potential aerospace, marine and civil engineering applications. Fabrication approaches used for consolidating the three-dimensional braided composites are detailed and some of the basic characteristics of the composites are described. 10 refs.USA


Item 97SAMPE Journal43, No.6, Nov.-Dec.2007, p.17-20A REVIEW OF ALIGNED DISCONTINUOUS CARBON FIBER SYSTEMS FOR COMPOSITES FORMINGNg S J; Meilunas R JNAVAIR

An overview is presented of past and recent developments in new material systems based on aligned, discontinuous carbon fi bre forms for advanced composite aerospace and other commercial applications. Candidate material systems considered include LDF thermoplastic composite technology, Stretch Broken Carbon Fiber, Discotex and Schappe Technique, all of which enable lower touch labour cost manufacturing and fabrication of complex geometric composite parts. 17 refs.USA


Item 98Polymers Paint Colour Journal197, No.4518, Nov.2007, p.6FROZEN FISH PAINT COULD HOLD KEY TO AIRCRAFT SAFETY

The development of antifreeze coatings based on anti-freeze proteins found in plants, fish and insects and synthesised at the Fraunhofer Institute for Manufacturing Technology in Bremen, Germany, is reported. Potential applications of the coatings include the prevention of ice formation on the wings of aircraft, a process that increases drag and can cause dangerous turbulence during take off and landing. 0 refs.




Item 99Reinforced Plastics51, No.11, Dec.2007, p.20-25STITCH IN ITS TIME: FABRICS SEW UP DIVERSE COMPOSITES MARKETSMcConnell V P

From traditional unidirectional wovens to stitched multiaxials and unique hybrids, reinforcement fabrics deliver the increased strength, stiffness, weight and cost properties now demanded in composite applications. Both woven and nonwoven fabrics vary in thickness, areal weight and may be coated with sizing or binder. SAERTEX utilises specially-formulated SAEFIX bonding agent as an option on its standard fabrics to promote self-adhesion. SAEFIX eliminates spraying up an adhesive, such as might be used in boat hull manufacture, but still allows rearrangement of the fabric during lay-up, contains no solvents and reduces the overall amount of adhesive necessary. Of the multiple markets utilising composites, renewable energy systems comprise a strong niche taking advantage of non-crimp fabrics. Both SAERTEX and Vectorply list wind energy among their key market segments, as does glass producer Owens Corning. Hexcel is applying advanced materials technology to high-performance yachts. In May, the company tested its three-ply, symmetric, double bias carbon fi bre woven fabric, HexForce, relative to the in-plane shear requirements of thick, load-bearing marine structure such as hull girders, bulkheads and booms. The security/safety market for personal, vehicle and building armour represents another growth area for reinforced fabric. 3TEX has received a 2m US dollars appropriation from the US Department of Defense for further development of its trademarked 3WEAVE composite armour technologies in combat vehicles. 3TEX uses patented textile preforming processes to weave its three-dimensional fabric with fi bre orientations in the X, Y and Z directions.WORLD


Item 100Eureka27, No.12, Dec.2007, p.14TAKING THE HITS WITHOUT FLINCHINGShelley T

At Reading University in the UK, scientists have discovered that reinforcing plastic with helical fi bre tubes, wound at an angle of just 15 degrees, produces composite materials that can absorb very large amounts of impact energy before they break, regardless of whether impact is fast or slow. Applications are envisaged in security, defence, aerospace, and motor vehicles. Full details are provided in this article.

Reading,UniversityEUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 101Eureka27, No.11, Nov.2007, p.28WEAVING ARAMID WITH CARBON MAKES FOR BETTER COMPOSITES

The manufacture by researchers at the University of East London of a composite which combines aramid and carbon fi bres in the weave is briefl y described. The failure mechanism when the fabric is loaded in different directions is considered. Applications are expected in the automotive and aerospace industries.

East London,UniversityEUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 102172nd ACS Rubber Division Meeting - Fall 2007. Proceedings of a conference held Cleveland, Oh., 16th-18th Oct.2007.Akron, Oh., ACS Rubber Division, 2007, Paper 46, pp.19COMPARISON OF FLUORINATED LIQUID SILICONE RUBBER AND HEAT CURED FLUOROSILICONE ELASTOMERRiley G; Toub M; Franssen P; Bosshammer SMomentive Performance Materials Inc.(ACS,Rubber Div.)

A fully fl uorinated liquid silicone rubber having excellent fuel and oil resistance and processability equivalent to commercial standard liquid silicone rubbers is compared with fl uorosilicone heat cured elastomers in the areas of processability, physical properties and fuel and solvent resistance with emphasis on requirements for automotive and aerospace applications. 12 refs.USA


Item 103High Performance Polymers19, No.5-6, Oct.-Dec.2007, p.665-683USE OF DIELS-ALDER CYCLOPOLYMERIZATIONS IN THE PHOTOCURING OF POLYMERSMeador M A; Meador M A; Tyson D S; Ilhan FUS,NASA,Glenn Research Center; Ohio Aerospace Institute; Abhu Dhabi,University

The synthesis of polyimides and polyesters via photocuring by Diels-Alder cyclopolymerisation of o-methylphenylketone-derived o-quinodimethanes and trapping by a bis(dienophile) such as bismaleimide or bisacrylate, is described. The products were characterised by proton and carbon-13 NMR, FTIR, TMA, DSC, TGA and GPC, and the effects of molecular structure on properties are discussed in terms of potential aerospace applications. 6 refs.



UNITED ARAB EMIRATES; USA


Item 104Journal of Materials Science42, No.22, Nov.2007, p.9170-9175INFLUENCE OF NOVEL ADDITIVE ON BMI RESIN AND BMI RESIN MATRIX COMPOSITEZhang B Y; Li M; Chen X BBeijing,Institute of Aeronautical Materials

In order to achieve high performance in a bismaleimide(BMI) matrix composite manufactured by the vacuum bag cure only technique, a novel additive WD-01 (a toluene solution of alkylammonium salt of acrylate-acrylamide copolymer) was selected to modify BMI-B resin based on modifi ed polyetherketone-toughened 4,4’-bismaleimidodiphenyl methane/O,O’-diallylbisphenol A system, and the properties of WD-01-modifi ed BMI resin(BMI-WD) and resin matrix/carbon fi bre composite were investigated. Results indicated that the cure shrinkage rate of BMI-B resin was reduced from original 4.0% to 1.8% and the surface morphology of neat resin casting were changed signifi cantly by incorporating 1 wt % WD-01, with no change of chemical cure behaviour of BMI resin being observed. Vacuum-consolidated BMI-WD/T700 laminates had autoclave cure quality with good mechanical properties. A high-performance vacuum-bag curable prepreg with promising characteristics is thus being developed, which is expected to fi nd use in advanced composite structures, e.g. for aerospace applications. 9 refs.

Yantai Science and Technology Corp.CHINA


Item 105Composite Structures82, No.4, 2008, p.629-635EFFECT OF TEMPERATURE AND HUMIDITY ON TRANSIENT HYGROTHERMAL STRESSES DURING MOISTURE DESORPTION IN LAMINATED COMPOSITE PLATESBenkhedda A; Tounsi A; Adda Bedia E ASidi-Bel-Abbes,University; Blida,Universite Saad Dahleb

Polymer matrix composites are relevant materials for future supersonic aircraft due to their high specifi c properties. However, in such aeronautical applications, the material is exposed to severe environmental conditions. The present paper aims at assessing an approximate model to evaluate hygrothermoelastic stress in composite laminated plates during moisture desorption taking into account the change of mechanical characteristics induced by the variation of temperature and moisture. The developed method permits us to calculate such stresses during desorption phase without the computation of the moisture concentration, through laminated plates. It observed through this

study that the variation of elasticity modulus due to the temperature causes a stress relaxation. These stresses have to be taken into account for the design of composite structures submitted to a moist environment. Through the presented study, we hope to contribute to the understanding of hygrothermal behaviour of composite laminated plates. 22 refs. Copyright (c) 2007 Elsevier Ltd.ALGERIA


Item 106Polymers in Defence and Aerospace Applications. Proceedings of an international conference held Toulouse, France, 18th-19th September 2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 19, pp.10POLYMERS FOR EXO-ATMOSPHERIC SUPERSONIC VEHICLES: A TOUGH LIFEBroughton D; Narbron DAWE PLC(Smithers Rapra Technology Ltd.)

The range of materials, including adhesives, potting compounds and rigid and fl exible foams, which AWE has built up expertise with for exo-atmospheric supersonic vehicle applications, is described and some specific examples of problems/issues relating to material supply and PU adhesive manufacture, which have had to be solved, are presented.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 107Polymers in Defence and Aerospace Applications. Proceedings of an international conference held Toulouse, France, 18th-19th September 2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 14, pp.22DEVELOPMENT OF WIDER PERFORMANCE RANGE RUBBER SEAL MATERIALS AND THE UTILITY OF FEA MODELINGKeller R WFreudenberg-NOK General Partnership(Smithers Rapra Technology Ltd.)

The development of new materials (fl uoroelastomer and EPDM materials) for aerospace sealing applications is described and examples are presented of the use of testing at actual application conditions (temperature, pressure and fl uid exposure) to more thoroughly determine whether the new materials will perform in the intended O-ring applications. Examples are also presented where application testing and fi nite element analysis were used to avoid potential problems and where testing was not used and problems were observed. Tables are included showing the original properties of the materials (hardness, tensile strength, elongation and specifi c gravity) and changes in



properties, including compression set, upon air ageing and after fl uid immersion. 6 refs.USA


Item 108Polymers in Defence and Aerospace Applications. Proceedings of an international conference held Toulouse, France, 18th-19th September 2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 10, pp.14DEVELOPMENT OF NEW CONDUCTIVE AND MICROWAVE-LOSSY MATERIALS INVOLVING CONDUCTING POLYMER COATINGSAvloni J; Henn AEeonyx Corp.; Marktek Inc.(Smithers Rapra Technology Ltd.)

The basic properties of EeonTex textiles coated with conductive polymers, such as polypyrrole, polyaniline and polyethylenedioxythiophene, are described and end-use applications of the coated fabrics in defence and aerospace applications are indicated. The properties and applications of Eeonfoams, which consist of polymeric foams coated with conducting polymers, are also described. 5 refs.USA


Item 109Polymers in Defence and Aerospace Applications. Proceedings of an international conference held Toulouse, France, 18th-19th September 2007.Shawbury, Smithers Rapra Technology Ltd., 2007, Paper 3, pp.6POLYMER NANOCOMPOSITES WITH CARBON NANOTUBES IN AEROSPACE AND DEFENCENjuguna J; Pielichowski KCranfi eld,University; Cracow,University of Technology(Smithers Rapra Technology Ltd.)

The use of carbon nanotubes and nanocomposites based thereon for the manufacture of structures for aerospace and defence applications is discussed, focusing upon methods of production, effects of the preparation method on the structure and phase distribution of polymer nanocomposites and structure-property relationships. Examples of a number of potential applications of nanocomposites in aerospace and defence applications, including sensors and thermal management systems, are given. 9 refs.EASTERN EUROPE; POLAND


Item 110International Journal of Crashworthiness12, No.4, 2007, p.411-428A REVIEW OF COMPOSITE STRUCTURES

SUBJECTED TO DYNAMIC LOADINGHampson P R; Moatamedi MSalford,University

An overview of recent developments in theoretical, experimental and numerical methods for low, high, and hyper-velocity impact of composite structures reported in the literature is presented, with emphasis on experimental apparatus and techniques such as drop-weight testing and the implementation of failure criteria in fi nite element modelling methods which predict material behaviour. Applications within the marine, automotive and aerospace industries are discussed and potential future research topics such as the study of oblique impacts are identifi ed. 158 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 111SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 120, pp.14ENGINEERED SANDWICH CORES FOR VEHICULAR BRIDGE DECKSKos E; Stoll FWebCore Technologies Inc.(SAMPE)

Technical results obtained from recent applications of innovatively-engineered composite cores for bridges and ground matting systems are presented. The sandwich core designs are based on patented fi bre reinforced cores used in infusion moulding process. Examples include a vehicular bridge deck recently installed in Summit County, Ohio, and an airfi eld mat development programme in which deployable panels placed on soft soil are subjected to highly concentrated wheel loads. Laboratory and fi eld test data are presented. 1 ref.USA


Item 112SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 227, pp.9MULTI-CHANNEL STRUCTURAL HEALTH MONITORING NETWORK, POWERED & INTERROGATED USING ELECTROMAGNETIC FIELDSArms S W; Hamel M J; Townsend C PMicroStrain Inc.(SAMPE)

A report is presented on the EmbedSense network of



versatile, embedded wireless sensing nodes that are powered and interrogated by external electromagnetic fi elds. The embedded nodes support a wide range of sensors, and include a factory programmable radio-frequency identifi cation code. It is shown that power for these systems may be provided through one or more inductive ‘coupling points’ where access is less restricted, but sensors may be extended on or within the smart structure to allow data to be sampled from remote, hard-to-access areas. Monitoring applications in smart medical implants, composite civil structures and composite aerospace structures are described. 5 refs.USA


Item 113SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 220, pp.14ROHACELL FOAM FOR SPACE APPLICATIONSHogue P; Rooney M; Webb A; Huebert D; Marinelli B; Daugherty A; Price D JJohns Hopkins University; US,Naval Air Weapons Center; Raytheon Space and Airborne Systems(SAMPE)

Rohacell foams, closed cell polymethacrylimide(PMI) materials manufactured by Degussa, are used in terrestrial lightweight construction such as aircraft seating, helicopter rotor blade core, antenna radome construction and as part of the PHENIX multiplicity detector at Brookhaven National Laboratory. The requirements for their use in space-based applications are, however, much more stringent. The present study indicates that stiffness remains reasonably fl at over the temperature range -160 deg C to +120 deg C. However, the foam swells on the order of 1.8E-3 cm per cm under room temperature vacuum and exhibits very slow relaxation in a vacuum at 25 deg C. While the PMI foam evaluated meets NASA outgassing requirements when water is subtracted from the total mass loss, the rate of water diffusion at 23 deg C is only 6.3E-11 cm2/s. At 100 deg C, this value is 1.6E-7 cm2/s giving activation energy for diffusion of 93.3 kJ/mol. Hydrogen bonding to nitrogen and adjacent carbonyl groups is a possible explanation for the unusually strong bond with water. TGA and thermal expansion results are also presented. 18 refs.

DegussaUSA


Item 114Future MaterialsSept.2007, p.16NANOTUBE COMPOSITE SENSING SKINMichigan,University

A coating which could be painted or sprayed on structures to sense their stability over time has been developed by researchers at the University of Michigan’s College of Engineering. The coating material is an opaque, black material made of layers of polymers with networks of carbon nanotubes running therethrough, each layer being capable of measuring different things, such as the pH level of a structure, which changes with corrosion, or registering cracks by cracking under the same conditions as the structure. The perimeter of the carbon nanotube skin is lined with electrodes connected to a microprocessor or computer, which creates a two-dimensional visual map of the electrical resistance in the nanotube skin, revealing corrosion or fracturing too small for human eyes to detect. Potential applications include bridges, buildings and airplanes.USA


Item 115Polymer Preprints. Volume 46. Number 2. August 2005. Papers presented at the ACS meeting held Washington, D.C., August 2005.Washington, D.C., ACS,Div.of Polymer Chemistry, 2005, p.802-803SINGLE WALL CARBON NANOTUBE COPOLYPEPTIDE BIONANOCOMPOSITES FOR POTENTIAL AEROSPACE APPLICATIONSLovel 1 C; Worthington E; Deming T J; Stucky G D; Jinho Kang; Wise K E; Harrison J S; Fitz-Gerald J M; Cheol ParkVirginia,University; California,University; US,National Institute of Aerospace; NASA Langley Research Center(ACS,Div.of Polymer Chemistry)

Bionanocomposites were prepared from a random copolypeptide of leucine and phenylalanine and single walled carbon nanotubes. These materials were evaluated for their mechanical, dielectric and electrical conductive properties, and it was shown that the addition of carbon nanotubes into this biopolymer allowed the potential of using it as a sensor to investigate shear forces in aerospace vehicles. Nanotube addition improves both dielectric constant and electrical conductivity of the peptide copolymer composites, as well as improving mechanical durability. 4 refs.USA


Item 116Iranian Polymer Journal16, No.6, June 2007, p.375-387THERMAL DEGRADATION PROCESS OF RESOL TYPE PHENOLIC MATRIX/KAOLINITE LAYERED SILICATE NANOCOMPOSITEBahramian A R; Kokabi M; Behesty M H; Famili M H N



Tarbiat Modarres,University; Iran,Polymer & Petrochemical Institute

The preparation of nanocomposites of a resol-type phenolic resin and kaolinite layered silicate clay reinforced with asbestos cloth and their characterisation by XRF, XRD, FTIR and SEM, is described. Thermal degradation of the nanocomposites during pyrolysis was investigated using TGA and cone calorimetry, and the effects of layered silicate on thermal stability are discussed in terms of potential aerospace applications as an ablative insulation material. 22 refs.IRAN


Item 117Cellular Polymers26, No.4, 2007, p.229-244LOW-DENSITY PHENOLIC SYNTACTIC FOAMS: PROCESSING AND PROPERTIESJohn B; Nair C P R; Ninan K NVikram Sarabhai Space Centre

The mechanical properties of low density phenolic resin syntactic foams with different volume fractions of glass microballoons were investigated by tensile, fl exural and compression testing, SEM examination of fracture surfaces, and DMA. The results are discussed in comparison with those for syntactic foams based on an addition cure phenolic resin, propargyl ether novolac resin, in terms of potential aerospace applications. 27 refs.INDIA


Item 118Polymer Composites28, No.5, 2007, p.588-592CONDUCTING POLYANILINE COMPOSITES AS MICROWAVE ABSORBERSJohn H; Thomas R M; Jacob J; Mathew K; Joseph RCochin,University of Science & Technology

Conducting polymers are excellent microwave absorbers and they show technological advantage when compared with inorganic electromagnetic absorbing materials, being light weight, easily processable, and the ability of changing the electromagnetic properties with nature and amount of dopants, synthesis conditions, etc. In this paper we report the synthesis, dielectric properties, and expected application of conducting composites based on polyaniline (PAN). Cyclohexanone soluble conducting PAN composites of microwave conductivity 12.5 S/m was synthesised by the in situ polymerisation of aniline in the presence of emulsion grade polyvinyl chloride. The dielectric properties of the composites, especially the dielectric loss, conductivity, dielectric heating coeffi cient, absorption coeffi cient, and penetration depth, were studied using a HP8510 vector network analyzer. The microwave

absorption of the composites were studied at different frequency bands i.e, S, C, and X bands (2-12 GHz). The absorption coeffi cient was found to be higher than 200 m-1 and it can be used for making microwave absorbers in space applications. 35 refs.INDIA


Item 119Materials World15, No.10, Oct.2007, p.26-27CAN WE FIX IT?Jones FSheffi eld,University

With the introduction of advanced composite materials into many structural applications, such as the Airbus 380 and Boeing 787, it has become necessary to fi nd a way to autonomically heal mechanically induced damage. Early work on self-healing used embedded glass capillaries containing a liquid repair resin that would fracture in the path of a propagating crack. The released resin would polymerise and heal the damage. This approach has been developed further to employ continuous hollow glass fi bres to encapsulate potential resin systems. At the University of Sheffi eld, the need to accredit materials for the aerospace industry has driven the development of a structural health monitoring system for composite materials. It comprises a damage detection system that induces the healing effect and a matrix system that employs standard resins that are easily modifi ed for healing.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE


Item 120SAMPE ‘07: M&P - COAST TO COAST AND AROUND THE WORLD. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 36, pp.9CHARACTERIZATION OF “ULTRA” LOW OUTGASSING SILICONE MATERIALS FOR AEROSPACE APPLICATIONSRiegler B; Burkitt B; Thomaier RNuSil Technology LLC(SAMPE)

Newly developed ultra low outgassing silicone adhesives with total mass loss and collected volatile condensable material one-tenth the previous specifi cations and intended for aerospace applications are characterised by physical, outgas and optical testing and compared with standard materials meeting basic outgassing requirements. 11 refs.ASTM

USA




Item 121SAMPE ‘07: M&P - COAST TO COAST AND AROUND THE WORLD. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 26, pp.15EPOXY PREPREGS BASED ON FLAX FIBERS, THEIR APPLICATIONS AND PROPERTIESVan Raemdonck J; Van Acker J; Defoirdt N; McKee HIPA Composites; Ghent,University; Bast Fibers LLC(SAMPE)

Flax fibre epoxy prepregs were fabricated by in-line technology and their water absorption behaviour, resistance to biological attack, tensile properties, elastic modulus, flexural strength and dimensional stability investigated. Hybrid carbon-fl ax epoxy composite tubing was also manufactured and used in the production of racing bicycles and aircraft wings.BELGIUM; EU; EUROPEAN COMMUNITY; EUROPEAN ECONOMIC COMMUNITY; EUROPEAN UNION; USA; WESTERN EUROPE; WESTERN EUROPE-GENERAL


Item 122SAMPE ‘07: M&P - COAST TO COAST AND AROUND THE WORLD. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 17, pp.7ALIGNED DISCONTINUOUS CARBON FIBER FOR COMPOSITES FORMINGNg S J; Meilunas R JNAVAIR(SAMPE)

An overview is presented of past and recent developments in new material systems based on aligned, discontinuous carbon fi bre forms, which offer additional deformation mechanisms associated with fi bre axis stretching, thereby alleviating in-plane and interply shearing requirements that constitute the principal process limitations of continuous fi bre systems. The material systems considered are LDF thermoplastic composite technology, stretch broken carbon fi bre, Discotex and the Schappe Technique, which is based on the use of long fi bres producing yarns which are more bulky, of higher tenacity and which can be produced in a number of blends. All four of the technologies enable lower touch labour cost manufacturing and fabrication of complex geometric composite parts for potential aerospace and other applications. 17 refs.USA


Item 123SAMPE ‘07: M&P - COAST TO COAST AND AROUND THE WORLD. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.

Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 11, pp.12HIGH STRENGTH AND DURABILITY NACELLE FILM ADHESIVE, HYSOL EA9658McKillen J M; Miao T Y; Cornwell R E; Marsicano J MHenkel Corp.(SAMPE)

The development of a state-of-the-art, high temperature and durable epoxy-based fi lm adhesive, called Hysol EA9658, for use in aerospace nacelle bonding applications, is reported. The impact-cure kinetics, bulk thermal performance, adhesive performance (tensile lap shear, peel properties and flatwise tension performance), environmental fl uid resistance, heat ageing performance and primer properties of this adhesive, which is a 177 degrees C cure system possessing unusually high toughness and peel strength and controlled flow, are described. It is suitable for demanding applications where continuous exposure (6,000+ hours) to temperatures up to 177 degrees C is required. 6 refs.USA


Item 124SAMPE ‘07: M&P - COAST TO COAST AND AROUND THE WORLD. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 7, pp.12DEVELOPMENT OF A NEW HIGH PERFORMANCE ADHESIVE FILM FOR AEROSPACE BONDING APPLICATIONSSang J J; Kohli D KCytec Engineered Materials(SAMPE)

The development, processing and applications of a new structural adhesive fi lm, called FM 320, designed for bonding of metallic and composite monolithic and sandwich structures for aerospace applications, are described. The adhesive fi lm, which is dual curing (121/177 degrees C) and uses new toughening technology, exhibits very high toughness at low temperatures and high shear strength up to 121 degrees C and provides a minimum of 30 days outtime at 23 degrees C. Metal bonding performance and thermal characteristics of the adhesive fi lm are evaluated and the effects of primer thickness, different cure cycles and humidity exposure on adhesive performance evaluated. 6 refs.USA


Item 125SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce,



2007, Paper 85, pp.13HYBRID POLYMERS FOR HIGH TEMPERATURE AEROSPACE APPLICATIONSKeller T M; Kolel-Veetil M KUS,Naval Research Laboratory(SAMPE)

The results are reported of a study of the processability and thermooxidative properties of high temperature materials prepared from poly(carborane-siloxane-acetylene)s, blends thereof with poly(siloxane-acetylene)s and hydrosilation reaction involving vinyl-containing carboranylenesiloxane. The aim of the study was to develop unique high temperature thermosets, coatings for polymeric and carbon fi bres and ceramic compositions upon heat treatment. Data are included on thermal cure behaviours obtained by DSC, oxidative stability of coated carbon fi bres upon heating to 1000 degrees C in air and weight retention of networks obtained from the reaction of vinyl-containing carboranylenesiloxane with various crosslinkers obtained by TGA upon heating to 1000 degrees C in nitrogen and air. 19 refs.USA


Item 126SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce, 2007, Paper 53, pp.10A NEW THERMOPLASTIC FLUOROPOLYMER COMPOSITE MATERIAL FOR NONFLAMMABLE TANKS AND STRUCTURESDeLong D; Greason JXCOR Aerospace(SAMPE)

Advances which have been made in the manufacture of a fl uoropolymer composite material (Nonburnite) suitable for lightweight, oxygen compatible, linerless liquid oxygen tanks for propulsion, fuel cell and life support applications are described. The composite material is resistant to microcracking and has a low coeffi cient of thermal expansion and inherent resistance to combustion. When used in a skin-foam-skin composite, the composite material also serves as thermal insulation. Fabrication and test experience with a newly released Tefl on PFA TE-224 dispersion formula, which replaces Tefl on PFA 335, is also described. 1 ref.USA


Item 127SAMPE ‘07: M&P - Coast to Coast and Around the World. Volume 52. Proceedings of a conference held Baltimore, Md., 3rd-7th June, 2007.Covina, Ca., SAMPE International Business Offi ce,

2007, Paper 52, pp.11CRYOGENIC DAMAGE TOLERANCE EFFECT ON COMPOSITE MATERIALSNoorda J; Patterson J; Fronk T; Swenson D; DeLay THyPerComp Engineering Inc.; Utah,State University; US,NASA,Marshall Space Flight Center(SAMPE)

The results are reported of cryogenic Izod impact testing of neat epoxy resins and toughened resin systems typically employed in aerospace and commercial applications and the effects of low and high energy impacts at cryogenic temperatures (specifi cally liquid nitrogen) on composites made from aramid and/or carbon fi bres and two of the resins. The composites were also subjected to tensile testing after impact. The data obtained will be used to design pressure vessels with improved toughness at cryogenic temperatures. 5 refs.USA


Item 128Materials and Manufacturing Processes22, No.5-6, 2007, p.768-772MANUFACTURING INFLUENCE ON THE DELAMINATION FRACTURE BEHAVIOR OF THE T800H/3900-2 CARBON FIBER REINFORCED POLYMER COMPOSITESZhang J; Fox B LDeakin,University

The delamination fracture behaviour of carbon fi bre-reinforced epoxy resin composite laminates for aerospace applications, cured under different processing conditions, were investigated by mode I interlaminar fracture toughness tests, double cantilever beam tests, indentation-debonding tests, SEM examination of fracture surfaces, and AFM of debonded fi bres. The effects of different fracture mechanisms during delamination on delamination resistance during crack growth are discussed. 15 refs.AUSTRALIA


Item 129Materials and Manufacturing Processes22, No.5-6, 2007, p.741-749ADVANCES IN POLYMER-FILLER COMPOSITES: MACRO TO NANORay S; Easteal A JAuckland,University

An overview of polymer-clay nanocomposites (PCNs) based on layered silicates with or without modifi cation by cationic surfactants, is presented in terms of their preparation by in-situ intercalative polymerisation, solution or melt intercalation, the characterisation of their intercalated or exfoliated structures by techniques such as SAXS and TEM, and their mechanical, barrier,



fl ame retardant and other properties. Current and potential future applications of PCNs in automobiles, construction, aerospace, electrical, electronics, food packaging, coatings and pigments are discussed. 55 refs.NEW ZEALAND


Item 130Future MaterialsAug.2007, p.3KEVLAR BLASTS OFF WITH NASA

DuPont has signed a Space Act Agreement with NASA for development of urethane foam insulation reinforced with Kevlar fi bre, which is intended for applications including the new launch vehicle being designed to replace the space shuttle. Scientists will specifi cally seek to develop a process to incorporate Kevlar fi bre into the cells walls of the foam, to enhance the performance of the thermal protection systems used in the Ares I crew launch vehicle.

DuPont; NASAUSA


Item 131Shawbury, Smithers Rapra Technology Ltd., 2006, 21 papers, pp.73Proceedings of an international conference held 18th-19th September 2007, Toulouse, France(Smithers Rapra Technology Ltd.)POLYMERS IN DEFENCE AND AEROSPACE APPLICATIONS.

This conference covers a broad range of subjects relating to the use of polymers in defence and aerospace applications, presented by some of the world’s leading authorities and organisations. A signifi cant number of papers are devoted to the use of composites and nanocomposites. Other presentations relate to novel polymer systems, elastomers and rubbers, and polymer processes and applications.WORLD


Item 132JEC CompositesNo.34, July-Aug.2007, p.62-63ALTERNATIVE CFRP SURFACE TREATMENTS: FOR ADHESIVE BONDING REPLACE MANUAL GRINDINGWachinger G; Kolb M; Klug M; Scholler JEADS; EADS Military Air Systems

The use of corona and atmospheric plasma treatment as alternatives to the surface treatment of carbon fi bre-reinforced polymer surfaces by manual grinding and grit blasting to remove traces of peel ply release agent prior to adhesive bonding in aerospace applications were

investigated by XPS, peel tests and visual examination of fracture surfaces. The advantages of atmospheric plasma treatment are discussed in terms of durability of surface activation, performance and the potential for automation of the process. 8 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE


Item 133Materials Science & Engineering R56, No.1-6, 2007, p.28-64INFECTIOUS DISEASE: CONNECTING INNATE IMMUNITY TO BIOCIDAL POLYMERSGabriel G J; Som A; Madkour A E; Eren T; Tew G NMassachusetts,University

Infectious disease is a critically important global healthcare issue. In the U.S. alone there are 2 million new cases of hospital-acquired infections annually leading to 90,000 deaths and 5 billion dollars of added healthcare costs. Couple these numbers with the appearance of new antibiotic resistant bacterial strains and the increasing occurrences of community-type outbreaks, and clearly this is an important problem. Our review attempts to bridge the research areas of natural host defence peptides (HDPs), a component of the innate immune system, and biocidal cationic polymers. Recently discovered peptidomimetics and other synthetic mimics of HDPs, that can be short oligomers as well as polymeric macromolecules, provide a unique link between these two areas. An emerging class of these mimics are the facially amphiphilic polymers that aim to emulate the physicochemical properties of HDPs but take advantage of the synthetic ease of polymers. These mimics have been designed with antimicrobial activity and, importantly, selectivity that rivals natural HDPs. In addition to providing some perspective on HDPs, selective mimics, and biocidal polymers, focus is given to the arsenal of biophysical techniques available to study their mode of action and interactions with phospholipid membranes. The issue of lipid type is highlighted and the important role of negative curvature lipids is illustrated. Finally, materials applications (for instance, in the development of permanently antibacterial surfaces) are discussed as this is an important part of controlling the spread of infectious disease. 231 refs. Copyright (c) 2007 Elsevier B.V.USA


Item 134TECH 30: Global Conference VI. Proceedings of the Pressure Sensitive Tape Council, held Orlando, Fl., 16th-18th May 2007.Northbrook, Il., Pressure Sensitive Tape Council, 2007, p.99-106COMPARATIVE PROPERTIES OF SILYLATED POLYURETHANE, SILICONE AND NON-SILICONE PRESSURE SENSITIVE ADHESIVES



Griswold R MMomentive Performance Materials(Pressure Sensitive Tape Council)

The adhesive properties and chemical resistance of new pressure-sensitive adhesives based on silylated PUs are discussed and compared with those of conventional high-performance acrylic and silicone adhesives. The new adhesives offer excellent adhesive properties for applications requiring long-term exposure to chemicals and their properties can be altered for repositionability and permeability for a range of applications, including medical, pharmaceutical, automotive and aerospace applications. 2 refs.USA


Item 135Polymer Science Series C49, No.2, April-June 2007, p.182-187FLUOROSILOXANE SEALANTS FOR AVIATION INDUSTRYDonskoi A A; Baritko N VAll-Russian Institute of Aviation Materials

The properties of commercially available sealants based on fluorosiloxane oligomers containing the gamma-trifl uoropropyl group and their applications in the aviation industry are reviewed. The mechanical, thermal and physical properties of the sealants and their resistance to oils, fuels and other solvents are discussed with regard to their uses in surface and interjoint sealing and in comparison with those for fl uorocarbon rubbers. 52 refs.RUSSIA


Item 136Polymer Science Series C49, No.2, April-June 2007, p.166-170STABILITY OF SHEAR MODULUS OF GLASS-REINFORCED PLASTICS BASED ON ADHESIVE PREPREG IN A HUMID MEDIUMStartsev O V; Krotov A S; Ponomareva N V; Anikhovskaya L I; Batizat D V; Dement’eva L AAltai,State University; NTF Tekhpolikom; All-Russian Institute of Aviation Materials

Strength properties and moisture absorption of glass fi bre- and carbon fi bre-reinforced epoxy resin based on solvent-free adhesive prepregs were investigated in a humid atmosphere by ultimate moisture saturation, diffusion coeffi cient, shear modulus and swelling measurements. The effects of a cyclic action of moisture and temperature on shear modulus along the sheet plane were studied and the results are discussed in terms of the sealing of honeycomb structures in aerospace applications. 3 refs.RUSSIA


Item 137Future MaterialsJuly 2007, p.20FR FIBRE FOR COLOURFUL INTERIORS

GE Plastics, in partnership with Fiber Innovation Technology, has commercialised a new fi bre technology based on GE’s high-performance, fl ame-retardant Ultem polyetherimide resin. The new fibre is an excellent candidate material for textiles and nonwovens used in aircraft interiors and other applications requiring compliance with strict, flame, smoke and toxicity regulations. Currently, FIT can produce up to 10 million pounds/year of 6-denier per fi lament yarns and staple fi bres from GE’s Ultem 9011 resin using a state-of-the-art melt-spinning conversion line especially designed to handle high-temperature resins. Fibres based on Ultem resins are easily dyed using a broad range of colours and offer fl ame retardance without the use of halogens.

GE Plastics; Fiber Innovation Technology Inc.USA


Item 138Composites Manufacturing (USA)23, No.6, June 2007, p.60/62NEW MOLDING PROCESS SHOWS PROMISE FOR RANGE OF APPLICATIONSCouch HUS,National Composite Center

Quickstep Technologies’ Quickstep composite moulding technology, with applications in the aerospace, automotive, marine and construction industries, is described. The fl uid-based technology is shown to permit the curing, partial curing and joining of composite materials. Using balanced pressure and liquid heating and cooling, the process works by rapidly applying heat to a laminate trapped between a free fl oating rigid (or semi-rigid) mould that fl oats in a heat transfer fl uid(HTF). The mould and laminate are separated from the circulating HTF by a fl exible membrane or bladder. The temperature and pressure of the HTF behind the mould and fl exible membrane stay the same. Balanced pressure, combined with vibration within the HTF and vacuum on the laminate, removes air and compacts and heats the laminate to cure the part. The composite cure reaction can be stopped at any point, allowing the manufacturer to restart the curing cycle of uncured sections to join and bond them to other structures.

Quickstep Technologies Pty.Ltd.AUSTRALIA; USA


Item 139ANTEC 2007. Proceedings of the 65th SPE Annual conference held Cincinnati, Oh., 6th-11th May 2007.Brookfi eld, Ct., SPE, 2007, p.1606-1611NEW TRANSPARENT COPOLYCARBONATE



COMPOSITIONS WITH LOW OSU HEAT RELEASE VALUESDi J; Davis G; Jackson K; El KAssmi A; Mullen B; Schultz L; Sinha M; Sybert P D; Zhang JGE Plastics; GE Global Research(SPE)

New polyester carbonate copolymers afford the fi rst resins with low colour, high transmission and low haze combined with low OSU Heat Release values. In addition, the fabricated articles can be hard coated to provide improved levels of scratch resistance. These compositions can be varied to maximise the various mechanical properties depending on the needs of the application. The excellent clarity combined with OSU 65/65 compliance allow for applications such as interior transportation windows/dust covers, partitions, mirrors and lighting lenses. The excellent colourability also allows for the fabrication of interior opaque components for the transportation industry. 9 refs.USA

Accession no.999508

Item 140ANTEC 2007. Proceedings of the 65th SPE Annual conference held Cincinnati, Oh., 6th-11th May 2007.Brookfi eld, Ct., SPE, 2007, p.1547-1550NANOMECHANICAL AND NANOTACK PROPERTIES OF POLYMER COMPOSITESMorgan S E; Jones P J; Tucker S J; Wiggins J SSouthern Mississippi,University(SPE)

Joining and adhesive properties of polymeric composites are of critical importance for emerging applications in the aeronautical, aerospace and marine industries. Traditional macroscopic adhesion testing techniques evaluate macroscopic properties of materials, with limited information on the molecular level processes that control actual performance. Nanomechanical and nanotack evaluations utilising advanced nanoprobe techniques of polymer/fi bre composites reveal differences in performance at the molecular level. 8 refs.USA

Accession no.999497

Item 141Polymer48, No.14, 2007, p.4184-4195COMPRESSIVE PROPERTIES OF EXTRUDED POLYTETRAFLUOROETHYLENEJordan J L; Siviour C R; Foley J R; Brown E NUS,Air Force Research Laboratory; Oxford,University; Los Alamos National Laboratory

Polymers are becoming increasingly used in aerospace structural applications, where they experience complex, non-static loads. Correspondingly, the mechanical

properties at high strain rates are of increasing importance in these applications. This paper presents an investigation of the properties of Dupont 9B polytetrafl uoroethylene (PTFE) across strain rates from 10-3 to 105 s-1. The samples were tested using an Instron mechanical testing machine for static loading, traditional split Hopkinson pressure bars (SHPBs) for high strain rates, and a miniaturized SHPB for ultra-high strain rates. Additionally, the material was tested using dynamic mechanical analysis to determine the effects of time-temperature superposition on the strain rate behaviour of the samples. The results of the experiments are analyzed using the Zerilli-Armstrong model for polymers, which shows good agreement with other PTFE studies. 53 refs. Copyright (c) 2007 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; USA; WESTERN EUROPE

Accession no.999120

Item 142Composites Part A38, No.7, 2007, p.1655-1663MECHANICAL PERFORMANCE OF CARBON FIBRE-REINFORCED COMPOSITES BASED ON STITCHED PREFORMSBeier U; Fischer F; Sandler J K W; Altstadt V; Weimer C; Buchs WBayreuth,University; Eurocopter Deutschland GmbH

A comparative assessment of the influence of pure assembly seams based on a thin (11 tex) polyester yarn in a zigzag geometry on the resulting mechanical performance of a non-crimped fabric (NCF) carbon fi bre-reinforced epoxy composite manufactured by vacuum-assisted resin transfer moulding is presented. This study was aimed at generating a solid foundation regarding the overall performance level of stitched NCF composites and at identifying critical property changes. The comprehensive evaluation of the mechanical composite properties includes static as well as dynamic tests of the in-plane properties as well as a characterisation of the interlaminar properties such as apparent interlaminar shear strength (ILSS) and compression after impact (CAI). It is demonstrated that mechanical properties such as the tensile and compression stiffness and CAI strength are not degraded by the chosen stitching parameters, whereas the tensile and compression strength, ILSS as well as the tensile fatigue behaviour are reduced as a result of pronounced localised fi bre ondulations. A direct comparison to properties of a commonly used 5H satin woven fabric composite verifi es that the overall performance of these particular stitched NCF composites must be enhanced with regard to the identifi ed key criteria to meet the level required for aircraft applications and in order to maintain the performance advantage of NCF composites as compared to standard woven fabrics in general. Promising approaches include the use of different yarn materials based on soluble thermoplastics and/or modifi ed stitching parameters. 22 refs. Copyright (c) 2007 Elsevier Ltd.




Accession no.999076

Item 143Composites Technology13, No.3, June 2007, p.32-37THERMOSETTING STRUCTURAL ADHESIVESBlack S

When compared to mechanical fasteners and welding, structural adhesives distribute stresses over wider areas, act as sealants and also reduce noise and vibration. A structural adhesive must have strength enough to transfer or share loads between highly stressed components. Three basic thermosetting resin chemistries dominate the structural adhesives market: epoxy, PU and acrylic. In transportation, marine and industrial applications, all three types are in common use, while in the aerospace sector, epoxy dominates, due mainly to very high strength and temperature resistance and compatibility with the sector’s predominately epoxy-based laminates. Acrylics excel at bonding unprepared metals and composites; epoxies give the highest strength and highest temperature resistance and are a good choice for prepared metals and composites in high-stress environments; and urethanes offer good resilience and fl exibility for a range of materials. Case studies are presented that best illustrate the unique benefi ts of select products.WORLD

Accession no.998952

Item 144Proceedings of the American Society for Composites. Twenty-fi rst Technical Conference. Proceedings of a conference held Dearborn, Mi., 17th-20th Sept.2006.Lancaster, Pa., DEStech Publications, 2006, Paper 73GAS PERMEABILITY OF COMPOSITE LAMINATES FOR CRYOGENIC STORAGE SYSTEMSVan Pelt J; Sankar B V; Ifju P GFlorida,University(American Society for Composites; Michigan-Dearborn,University)

The effect of micro-cracking on the gas permeability of composite laminates for cryogenic storage tanks for aerospace applications was investigated using a procedure developed according to ASTM D1434-82 standards. Loads induced by launch and landing of vehicles were simulated by subjecting the composites to a given load and tank refuelling simulated by cryo-cycling of the laminates. The effects of the duration of the test, type of gas used and magnitude of upstream pressure on gas permeability were evaluated and the relationship between gas permeability and cryo-cycling examined. An uncertainty analysis was also carried out and a new geometry of specimen developed to achieve a seamless integration between test equipment

and specimen. Finite element modelling demonstrated that the new geometry would allow for accurate permeability measurements. 4 refs.

ASTMUSA

Accession no.998204

Item 145Proceedings of the American Society for Composites. Twenty-fi rst Technical Conference. Proceedings of a conference held Dearborn, Mi., 17th-20th Sept.2006.Lancaster, Pa., DEStech Publications, 2006, Paper 69PREDICTION OF GAS PERMEABILITY IN CROSS-PLY LAMINATES USING FINITE ELEMENTSJianlong Xu; Sankar B VFlorida,University(American Society for Composites; Michigan-Dearborn,University)

The permeation model based on Darcy’s law is used to predict gas permeability in cross-ply laminates for such applications as cryogenic propellant tanks under biaxial loading. The problem is decoupled into two parts, namely determination of crack density and interlaminar cross-sectional area. Crack densities are taken from experimental measurements and two different models are used to compute interlaminar cross-sectional area. The variation of permeability as a function of average stress for three different lay-ups is computed using a specially written MATLAB program and the results discussed. 14 refs.USA

Accession no.998200

Item 146Macromolecular Research15, No.4, June 2007, pp.357-362PREPARATION AND CHARACTERIZATION OF POLYIMIDE/CARBON-NANOTUBE COMPOSITESKim B S; Bae S H; Park Y H; Kim J HSung Kyun Kwan University

Polyimide/carbon nanotube (CNT) composite films, potential useful in high-performance microelectronics and aerospace applications, were prepared by mixing a solution of a polyisoimide solution with a suspension of CNTs in NMP, followed by casting, evaporation and thermal imidisation. The CNTs were modifi ed by treatment with nitric acid to improve their thermal and electrical properties, and to provide good dispersion of the CNTs in the polymer matrix. The modifi ed CNTs were well dispersed in the polyimide matrix, with a uniform diameter of about 50 nm. The thermal stability of the fi lms containing the CNTs was improved as a result of enhanced interfacial interactions between the polymer and CNTs and good dispersion of the modifi ed CNTs. The thermal expansion coeffi cient of the composite fi lms was slightly



decreased, whereas the dielectric constants increased linearly with increasing CNT content. 15 refs.SOUTH KOREA

Accession no.997846

Item 147ANTEC 2007. Proceedings of the 65th SPE Annual conference held Cincinnati, Oh., 6th-11th May 2007.Brookfi eld, Ct., SPE, 2007, p.1849-1853A CONSTITUTIVE MODEL FOR CREEP LIFETIME OF PBO BRAIDED CORDSterling W JUS,NASA,Goddard Space Flight Center; NASA,Wallops Flight Facility(SPE)

A constitutive model to describe the creep lifetime of PBO braided cord has been developed and fi t to laboratory data. The model follows an approach proposed for p-aramid cord in similar applications, and has an Arrhenius-type representation that arises from consideration of the failure phenomenon mechanism. The data were obtained using a hydraulic-type universal testing machine, and were analyzed according to Weibull statistics using commercially-available software. The application of concern to the author is NASA’s Ultra- Long Duration Balloon and other gossamer spacecraft, but the motivations for the related p-aramid works suggest broader interest. 30 refs.USA

Accession no.997522

Item 148SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 83, pp.11APPLICATIONS & PROCESSING TECHNIQUES FOR CETEX THERMOPLASTICS IN AEROSPACEBernard D; Kok W; Lenferink RTen Cate Advanced Composites(SAMPE)

The use and processing of CETEX thermoplastic materials in structural and interior aerospace applications are discussed. For aircraft applications, two resin systems are primarily used. CETEX PEI is an amorphous polyetherimide resin offering outstanding toughness and high heat resistance. It is qualifi ed at Airbus and Boeing for both structural and interior applications. CETEX PPS is a semicrystalline polyphenylene sulphide resin offering outstanding toughness and excellent chemical and solvent resistance. It is qualifi ed at Airbus and Boeing for multiple structural applications. Both materials are inherently fl ame resistant with low smoke emission and

easily meet 35/35 OSU. CETEX products are typically supplied in 12ft by 4ft pre-consolidated laminates and sandwich panels using the customer’s designated ply count, orientation and reinforcement, including hybrid laminates. By utilising pre-consolidated sheets and avoiding hand lamination, the customer can signifi cantly reduce the cycle time required to produce a fi nished part by, for example, heated press, autoclave, creep/stretch forming and vacuum forming. Lightning strike material can be incorporated and the laminates can be pigmented and/or textured. Thermoplastics have the unique capability of allowing parts to be welded or fused and folded, which facilitates lower part count structures.

Airbus; BoeingEUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; USA; WESTERN EUROPE

Accession no.997376

Item 149SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 82, pp.10TRIBOLOGICAL PROPERTIES OF XYTREX POLYMERS OF 3P CORPORATIONJiaxiang RenPerformance Plastics Products(SAMPE)

Xytrex polymers from Performance Plastics Products (3P) represent a family of high performance thermoplastics and their composites, using thermoplastics such as PEEK, polyphenylene sulphide and polyimide. Some of the polymers are compounded with property-enhancing reinforcing fillers and lubricants. The tribological properties of several Xytrex materials were studied. The results showed that by adding lubricants, such as PTFE and graphite, the wear factor and coeffi cient of friction of the composites improved. With the same fi llers, the wear resistance performance of various polymer-based composites differed. Potential applications in aerospace, automotive, electronic components, pump, valve and compressor components, and other industries are considered. 8 refs.USA

Accession no.997375

Item 150SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 73, pp.16MEMBRANE BASED VARTM PROCESSING: MODELLING AND CHARACTERIZATIONAmouroux S C; Henau J F; Heider D; Gillespie J W



Delaware,University(SAMPE)

The use of a nanoporous PTFE membrane as a means of improving the quality and repeatability of the vacuum assisted resin transfer moulding process for affordable high-performance composites for aerospace applications was investigated. By ensuring a uniform compaction pressure and a continuous venting over the entire part surface, the membrane provided a unique multifunctional solution to reduce thickness gradients and volatile-induced porosity and eliminate dry-spots. Previous experiments showed empirically that the choice of resin drove the choice of membrane. However, the fundamental mechanisms of the membrane and interactions with the resin needed further study. A fi rst generation model based on capillary effects and convective fl ow was developed. The comparison between predictions and experimental results, however, showed discrepancies. A critical assessment of the experimental set-up and the sensitivity of the model predictions to several input parameters is presented. Improvements in the experimental method and the model are identifi ed. 16 refs.USA

Accession no.997366

Item 151SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 65, pp.6DEVELOPMENT OF ELECTRONICALLY CONDUCTIVE PTFE COMPOSITE BY ADDING CARBON NANOFILLERSJiaxiang RenPerformance Plastics Products(SAMPE)

An electronically conductive PTFE composite has been developed at Performance Plastics Products(3P) by adding nanofi llers. Traditionally, a high concentration of carbon black or carbon fi bre is blended with PTFE to make a realistic electronically conductive PTFE composite. Mechanical properties of the composite, however, suffer signifi cantly and the viscosity of the mixture is too high to be produced by some PTFE production processes. In this study, it is demonstrated that, by breaking bundles of the nanofi llers and dispersing them homogeneously in the PTFE matrix, an electronically conductive PTFE composite with a lower nanofi ller concentration can be manufactured using the production facility at 3P. The nanofi llers used are vapour grown carbon nanofi bres and carbon nanotubes. The mechanical strength of the composite is shown to be comparable with that of the unfi lled PTFE. Potential applications of the electrically conductive PTFE composite in batteries, fuel cells, and automotive and aerospace applications are discussed. 7 refs.

USA

Accession no.997358

Item 152SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 52, pp.14SURFACE MODIFICATION OF EXFOLIATED GRAPHITE NANO-REINFORCEMENTSAllred R E; Gosau J M; Barlow J PAdherent Technologies Inc.(SAMPE)

Methods are discussed for modifying the surface chemistry and energy of nano-reinforcements of graphite and carbon, such as fl akes, worms and tubes, to allow improved wetting and provide a means for chemical bonding at the interface with polymers such as epoxy resin. Two approaches for surface modifi cation are presented, i.e. oxidative plasma treatments to populate the graphite surface with carboxyl and hydroxyl groups, and bonding of epoxy oligomers to the nano-reinforcements using reactive coupling agents. Both of these approaches are shown to be successful with exfoliated graphite nano-fl akes. These unique nano-reinforcements are expected to fi nd many applications in structural composites for military and commercial aircraft, aerospace, chemical processing, and medical structures. 20 refs.USA

Accession no.997345

Item 153SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 51, pp.5EMI SHIELDING POLYMERS BASED ON CARBON NANOTUBE HYBRIDSTiano T; Phely-Bobin T; Lynch A; Carey C; Hess D; Marchand J; Czerw RFoster-Miller Inc.; ARC Technologies Inc.; NanoTech Labs Inc.(SAMPE)

The development by Foster-Miller and ARC Technologies of a series of highly conductive polymer-based materials for use in lightweight EMI shielding applications, from aerospace to portable electronics, is described. The use of carbon nanotubes in different geometries, particularly as buckypaper, is shown to offer the advantages of good shielding effectiveness in a lightweight durable polymer, such as a two-part polysulphide. It is demonstrated that very high performance structures can be obtained which can be applied to surfaces in a similar manner to that in



which adhesive tape is put down. The reconfi guration of this structure for the preparation of microwave-absorbing materials is also discussed. 4 refs.USA

Accession no.997344

Item 154SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 47, pp.9POLYMER NANOCOMPOSITES FOR LINERLESS COMPOSITE TANKSArzberger S C; Tomlinson M; Cronin J; Ryan K; Mallick K; Munshi NComposite Technology Development Inc.(SAMPE)

The development of suitable materials for lightweight, linerless composite tanks for aerospace applications is discussed. Analytical models are used to identify the best morphology of the nano-reinforcement and to optimise the reinforcement volume fraction to achieve the desired performance. The material development and characterisation of polymer nanocomposites to meet these requirements are considered. These novel materials were shown to offer microcrack resistance over a broad temperature range. Substantial mechanical and thermal property improvements were demonstrated with Composite Technology Development(CTD)-developed polymer nanocomposites prepared from highly anisotropic nano-reinforcements (vapour grown carbon nanofi bres) at loading levels below 3 vol % in CTD’s high-performance, microcrack-resistant epoxy matrix resins. 8 refs.USA

Accession no.997340

Item 155SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 11, pp.10PERMEABILITY CHARACTERISTICS OF SILICONE RUBBERHaibing Zhang; Cloud AArlon Silicone Technologies(SAMPE)

Some applications which require silicone performance in extreme environments also require low gas permeability. These applications cover a range of aerospace components such as infl atables, ducting and diaphragms. A technical review is presented of the gas permeability characteristics of silicone rubber, including analysis of the gas penetration mechanism through the elastomer. The chemical structure

of silicone rubber affects permeability, as do other governing factors such as temperature and gas type. In particular, phenyl vinyl methyl silicone(PVMQ) has the lowest Tg (-120 deg C) of all elastomers, but its gas permeability is very high. The development by Arlon of a proprietary technology to reduce the gas permeability of PVMQ is described. The approach produces large gains in gas permeability reduction without sacrifi cing excellent low temperature elastomeric fl exibility. 14 refs.

Dow CorningUSA

Accession no.997305

Item 156SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 10, pp.11DEVELOPMENT OF A NEXT-GENERATION NON-CHROMATED ZERO VOC WATER BASED PRIMER FOR ADHESIVE BONDING APPLICATIONSShah K; Kohli DCytec Engineered Materials(SAMPE)

The development by Cytec Engineered Materials of a water-based non-chromate primer, based on an amine-cured epoxy resin, for adhesive bonding applications is discussed. The primer, designated BR 6700, is formulated to meet both the US Environmental Protection Agency regulations and the corrosion and bonding requirements of metallic substrates in the aerospace industry. The primer provides good corrosion protection, durability and mechanical performance in combination with 121 deg C and 177 deg C curing adhesives. The performance of the new BR 6700 primer is comparable with the industry standard primers, BR 127 and waterborne BR 6747-1. 2 refs.

US,Environmental Protection AgencyUSA

Accession no.997304

Item 157SAMPE Fall Technical Conference: Global Advances in Materials and Process Engineering. Vol. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 2, pp.13HIGH-TEMPERATURE ADHESIVE DEVELOPMENTGray R A; Magato J R; Vannucci R; Dillingham GMaverick Corp.; Brighton Technologies Group Inc.(SAMPE)

The recent development of AFR-PE-4 polyimide composites for large jet engine structures has increased



the need for a high-temperature adhesive system to bond these components to other structures. This study focuses on the development of a high-temperature adhesive that will allow the market to take full advantage of AFR-PE-4 composite systems in aggressive aircraft engine environments. This technology will have a high impact on both space and military launch vehicles, in addition to dual-use applications in automotive and the chemical industry. Maverick Corp. evaluated two candidate polyimide resin chemistries with the goal of developing the ‘next-generation’ high-temperature adhesive technology for AFR-PE-4 composite components. The overall goal of the study was to formulate addition-cured polyimide resins and to study the effect of chemical structure on high temperature properties, adhesion, and joint durability. 2 refs.USA

Accession no.997296

Item 158Journal of ASTM International3, No.8, Sept.2006, pp.15MECHANICAL IMPACT TESTING: DATA REVIEW AND ANALYSISEngel C D; Herald S D; Davis S EQualis Corp.; Marshall Space Flight Center

A review and evaluation of mechanical impact test data collected by NASA since the 1970s for six non-metallic materials in high-pressure liquid oxygen(LOX) and gaseous oxygen and in ambient LOX environments are presented. The impact mechanism is a proven ignition mechanism, which must be considered and understood in the design of an oxygen system for aerospace applications. The non-metallic materials considered are nylon-66, Lexan FR 700-701, neoprene, silicone polymer, Tefl on PTFE and Viton. Results of tests conducted to determine the statistical nature of the test procedure, to help establish sample size guidelines for material characterisation, are discussed. It is shown that the current practice of reporting reaction frequency data at dropped energy rather than energy the sample receives does not offer a means of comparing data between facilities. 14 refs. (ASTM Symposium on Flammability and Sensitivity of Materials in Oxygen-Enriched Atmospheres, Washington, DC, USA, Oct.2006)USA

Accession no.997232

Item 159Journal of ASTM International3, No.9, Oct.2006, pp.15PROACTIVE MITIGATION OF PCTFE-RELATED IGNITION HAZARDS IN OXYGEN SYSTEMS. I. DEVELOPMENT OF A VOLUNTARY CONSENSUS STANDARD SPECIFICATION TO CONTROL PROPERTY VARIATION IN

FINISHED PCTFE PARTSWaller J M; Julien H L; Newton B E; Beeson H DUS,NASA,Johnson Space Center; Wendell Hull & Associates Inc.

Reports of dimensional instability in PCTFE semi-fi nished articles and fi nished parts have raised concerns that leaks or part failure could occur during service, leading to catastrophic component or system failure, especially in high-pressure gaseous oxygen systems where fl ow friction, fl ow resonance or kindling chain ignition mechanisms are operative. These concerns culminated in the release of an internal NASA Kennedy Space Center Problem Advisory and a Government-Industry Data Exchange Program Problem Advisory on PCTFE. Release of the advisories coincided with a task group study examining the factors contributing to property variation in PCTFE. More specifically, the effect of resin grade, process route, annealing method and machining on dimensional stability, molec.wt. and crystallinity was determined. To gain better control of dimensional stability, for example, a Biot-Fourier method was developed that allowed calculation of the time needed for PCTFE parts of known geometry to reach thermal equilibrium during annealing. A voluntary consensus material specifi cation was then implemented to control properties in fi nished PCTFE parts used in aerospace applications. 25 refs. (ASTM Symposium on Flammability and Sensitivity of Materials in Oxygen-Enriched Atmospheres, Washington, DC, USA, Oct.2006)

US,NASA,Kennedy Space Center; DaikinUSA

Accession no.997226

Item 160Proceedings of the American Society for Composites. Twenty-fi rst Technical Conference. Proceedings of a conference held Dearborn, Mi., 17th-20th Sept.2006.Lancaster, Pa., DEStech Publications, 2006, Paper 10NONDESTRUCTIVE METHODS SUPPORTING NASA COMPOSITE OVERWRAPPED PRESSURE VESSEL ASSESSMENTSSaulsberry R; Greene N; Beeson H; Thesken J C; Phoenix S L; Revilock D; Grant J; Thorton S; Yolken T; Madaras E; Cramer E; Newman JUS,NASA,Johnson Space Center; Cornell University; US,NASA,Glenn Research Center; US,NASA,Marshall Space Flight Center; Texas Research Institute; US,NASA,Langley Research Center; Laser Technology Inc.(American Society for Composites; Michigan-Dearborn,University)

A comprehensive report is presented on the application of non-destructive testing techniques to the pre-test screening of Kevlar and other carbon composite over-wrapped pressure vessels for aerospace applications. Techniques, which have been employed or are under evaluation include ultrasonic testing, eddy-current testing, fl ash thermography



and shearography. 6 refs.USA

Accession no.996951

Item 161Proceedings of the American Society for Composites. Twenty-fi rst Technical Conference. Proceedings of a conference held Dearborn, Mi., 17th-20th Sept.2006.Lancaster, Pa., DEStech Publications, 2006, Paper 4DETERMINATION OF DAMAGE PROGRESSION IN NOTCHED NON-TRADITIONAL LAMINATES UNDER TENSILE LOADTreasurer P; Johnson W S; Houghton P; Hoffman D J; Razi HWoodruff G.W.,School of Mechanical Engineering; Atlanta,School of Material Science and Engineering; Boeing Commercial Airplanes(American Society for Composites; Michigan-Dearborn,University)

Non-traditional carbon fi bre/toughened epoxy prepreg laminates with slightly off-axis longitudinal plies were evaluated for damage suppression and compared with laminates with traditional 0 degree longitudinal plies. Open hole tension and fi lled hole tension tests were carried out on quasi-isotropic (25/50/25) and hard (60/30/10) lay-ups with longitudinal fi bre orientations and in-situ die-penetrant enhanced X-ray radiography was utilised to determine damage mode and progression. The effects of notch constraint, lay-up and off-axis longitudinal plies on overall laminate response were evaluated and the advantages of the non-traditional laminates over the traditional laminates for structural applications, such as aerospace applications, considered. 7 refs.USA

Accession no.996945

Item 162Adhesives and Sealants Industry14, No.5, May 2007, p.19-20ADVANCED COMPOSITES FOR TERRESTRIAL APPLICATIONS PROVE USEFUL IN SPACE INDUSTRYJohnson S; Sher SYLA Inc.

The benefi ts of advanced composite materials based on precision adhesives combined with compatible prepreg resins, such as YLA’s RS-3 (modifi ed polycyanate resin), SF-5 (polycyanate syntactic fi lm) and RS-4A (polycyanate fi lm adhesive), for aerospace applications are outlined and some examples of aerospace parts, which utilise these composites, are given.USA

Accession no.996130

Item 163Composites Science and Technology67, No.11-12, 2007, p.2592-2605MODELING OF PERMEATION AND DAMAGE IN GRAPHITE/EPOXY LAMINATES FOR CRYOGENIC TANKS IN THE PRESENCE OF DELAMINATIONS AND STITCH CRACKSNair A; Roy SAlabama,University

Composites are extensively used for various aerospace applications and one of its important potential uses is as cryogenic fuel tank material for crew launch vehicles. Composites offer high specifi c strength and stiffness, and therefore are preferred over many other materials. However under structural mechanical loads and/or thermal loads, transverse micro-cracks develop in the polymer matrix. These cracks along with interlaminar delaminations produced at the crack tips, lead to permeation of cryogenic fuel permeation through the laminates. In this study, mathematical models have been proposed to determine the delaminated crack opening displacement (DCOD) for each ply of a damaged laminate and the permeability associated with it. In addition, a stitch crack model has been proposed to address experimental observations. The through-thickness DCOD distribution for a damaged composite under the action of thermal and/or mechanical load is predicted using a five-layer model which is developed based on fi rst order shear deformation theory. The DCOD predicted by this mathematical model, with and without stitch cracks, shows good agreement with two dimensional fi nite element analysis. The DCOD values predicted for IM7/5250-4 laminate of lay-up [0/45/-45/90]”S were used to predict permeability using Darcy’s law for fl uid fl ow through porous media. The analysis results were benchmarked using test data from Air Force Research Laboratory. A parametric study for permeability conducted with varying stitch crack lengths shows that the permeability of the composite is sensitive to this form of damage in individual plies. 27 refs. Copyright (c) 2007 Elsevier Ltd.USA

Accession no.995898

Item 164Elastomers for Engineering: Future Trends. Proceedings of a conference held London, 23rd. Nov.2006.London, IOM Communications Ltd., 2006, p.97-101FUTURE REQUIREMENTS FOR ELASTOMERS IN AEROSPACE ENGINEERINGTaylor MAirbus(UK,Institute of Materials,Minerals & Mining)

This paper discusses the requirements of sealants used in airframe structures. A modern civil jet plane is assembled using several hundred kilograms of sealant, much of which performs critical functions for the aircraft. In such applications, sealants routinely operate under fatigue and



static loads in hostile environments and in temperatures ranging from -55 deg.C to 250 deg.C. The sealants may be in contact with fuel, water or aerospace chemical fl uids, and must be durable for the lifetime of the airframe, which may exceed 20 years. Key considerations when selecting an aerospace sealant are health, safety and environmental issues, the need to reduce density and weight reduction, and the need to be able to adhere to a variety of substrates. The suitability of polysulphide sealants to meet these requirements is examined.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.995417

Item 165JEC CompositesNo.32, May 2007, p.56-57LARGE-SCALE COMPOSITE COMPONENTS MADE OUT-OF-AUTOCLAVECornforth JGKN Aerospace

Advantages of out-of-autoclave (OOA) processing are discussed with reference to the production of large scale composite components. OAA processing of composites uses a different resin formulation that permits the component to be successfully cured under vacuum pressure only, whereas carbon-epoxy composites for aerospace applications are usually cured under a pressure close to seven bars. One advantage is that the tooling used to cure the component doesn’t need to be so substantial, which means that composite tooling can become viable. Energy consumption is reduced, since with OOA, the heat is applied locally, directly from the tool itself, with the external surfaces of the component well insulated. In addition, OOA can support a cellular-based lean operation, where all of the processing on that component is done in one location and parts no longer need to be moved around the factory. GKN Aerospace has developed a fi bre-optic thermometer based on the Bragg Grating principle of operation, which avoids the need to add multiple disposable thermocouples to the edges of the pre-cured laminate stack to monitor temperature during cure, thereby saving time and money. The company has already manufactured parts up to 2.5 m long and weighing 80 kg. It is claimed that the advantages outlined make out-of-autoclave processing a target technology for a factory of the future.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.995380

Item 166Journal of Polymer Science: Polymer Chemistry Edition45, No.9, 1st May 2007, p.1641-1652PENDENT POLYIMIDES USING MELLITIC ACID DIANHYDRIDE. II. STRUCTURE-PROPERTY RELATIONSHIPS FOR

ZIRCONIUM-CONTAINING PENDENT POLYMERSIllingsworth M L; Dai H; Wang W; Chow D; Siochi E J; Yang K; Leiston-Belanger J M; Jankauskas JRochester,Institute of Technology; US,NASA,Langley Research Center

The synthesis of polyimide films with zirconium-containing pendant groups derived from pyromellitic dianhydride and 4,4’-oxydiphthalic anhydride as dianhydrides and 4,4’-oxydianiline, 3,4’-oxydianiline and 1,3-diaminophenoxybenzene as diamines is described. The products were characterised by FTIR, proton NMR, GPC, TGA, DSC, fl exibility, solvent resistance and cracking resistance of multilayer fi lms, and the structure-property relationships are discussed in terms of potential aerospace applications. 80 refs.USA

Accession no.994785

Item 167Journal of Advanced Materials39, No.2, April 2007, p.3-12A REVIEW Û FEATURES AND BENEFITS OF SHAPE MEMORY POLYMERS (SMPS)Dietsch B; Tong TCornerstone Research Group Inc.

The development of shape memory polymers (SMPs), a type of æsmart’ or intelligent materials that function by changing their modulus in response to an external stimulus such as heat, light or chemical exposure, is reviewed. The mechanism of the shape memory effect is described and potential applications of SMPs, such as actuators, in clothing manufacture, deployable space applications, morphing aircraft and in medical treatment, are discussed. 44 refs.USA

Accession no.994765

Item 168Covina, Ca., SAMPE International Business Offi ce, 2006, 85 papersVOL. 38. Proceedings of a conference held Dallas, Tx., 6th-9th November 2006.SAMPE FALL TECHNICAL CONFERENCE: GLOBAL ADVANCES IN MATERIALS AND PROCESS ENGINEERING. (SAMPE)

Papers are divided into the following main sessions: adhesives, joining and bonding, aircraft materials recycling, coatings and sealants, composites repair, testing and inspection technologies, design and analysis, fi bre reinforcement, textile and preform, fi re safe materials, high temperature materials, innovative material forms, nanocomposites, nanomaterials for space applications, natural fi bres, new advances in resin infusion processing,



new materials applications and challenges for aircraft, and thermoplastic composites.USA

Accession no.994688

Item 169Reinforced Plastics51, No.5, May 2007, p.13TRIPLE-PLY TAPE DEVELOPED

It is briefly reported that Polystrand has introduced a lightweight and balanced reinforcement tape for applications needing a higher strength-to-weight ratio. The continuous 25 inch wide tape provides 70% high-performance glass fi bres by weight in a thermoplastic matrix. Polystrand Tri-Ply tape is made in a proprietary process that impregnates continuous fi bres with a PP thermoplastic resin. The reinforcement weighs only 29.4 ounces per square yard, a 20% reduction in weight compared to a three-layer product made with standard tapes.

Polystrand Inc.USA

Accession no.994543

Item 170High Performance PlasticsMarch 2007, p.5FIRE RETARDANT PP FOR TRANSPORT APPLICATIONS

Brief details are presented in this small article about a European Union project, co-ordinated by Polymer Laboratories in Germany, which seeks to resolve the diffi culty of producing PP-based fl ame retardants fi lled with magnesium hydroxide particles, for use in cars, planes and ships. The project is called “FLARETPOL”.

Polymer LaboratoriesEU; EUROPE-GENERAL; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.994074

Item 171Composites Part A38, No.6, 2007, p.1525-1532A SELF-HEALING CARBON FIBRE REINFORCED POLYMER FOR AEROSPACE APPLICATIONSWilliams G; Trask R; Bond IBristol,University

Self-healing is receiving increasing interest worldwide as a technology to autonomously address the effects of damage in composite materials. This paper describes the results of four point bend fl exural testing (ASTM-D6272-02) of T300/914 carbon fi bre reinforced epoxy with resin fi lled embedded hollow glass fi bres (HGF) which provided

a self-healing functionality. The study investigated the effect of the embedded HGF on the host CFRP mechanical properties and also the healing effi ciency of the laminates after they were subjected to quasi-static impact. Specimens were tested in the undamaged, damaged and healed conditions using a commercial two-part epoxy healing agent (Cytec Cycom 823). Microscopic characterisation of the embedded HGF was also undertaken to characterise the effect on the host laminate fi bre architecture. 26 refs. Copyright (c) 2007 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.993176

Item 172Journal of Composite Materials41, No.5, 2007, p.613-632THE IMPACT PROPERTIES OF HIGH-TEMPERATURE FIBER-METAL LAMINATESCortes P; Cantwell W JLiverpool,University

The impact properties of laminates of a metal alloy and either carbon fi bre-reinforced PEEK or glass fi bre-reinforced polyetherimide composites were investigated under high and low velocity impact loading conditions with the aim of developing a lightweight hybrid material for high-temperature aerospace applications. Low velocity impact tests were performed using an instrumented impact tower and high velocity impact tests were conducted using a nitrogen gas gun. Fracture mechanisms were identifi ed by optical microscopy and a comparison made of the impact properties of the carbon fi bre-reinforced PEEK versus glass fi bre-reinforced polyetherimide composites. 18 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.991679

Item 173Journal of Applied Polymer Science104, No.2, 15th April 2007, p.0138-1042PREPARATION AND PROPERTIES OF A NOVEL POLYTRIAZOLE RESINWan L; Luo Y; Xue L; Tian J; Hu Y; Qi H; Shen X; Huang F; Du L; Chen XEast China,University of Science & Technology; Shanghai,Bureau of Astronautics; Shanghai,Key Laboratory for Ultrafi ne Materials; Beijing,Institute of Aeronautical Materials

Details are given of the synthesis and characterisation of a novel polytriazole resin. Solubility in acetone was determined. The Tg and thermal degradation temperature of the cured resin were investigated. Tensile and fl exural properties are discussed. Potential applications in aviation and aerospace materials are mentioned. 15 refs.



CHINA

Accession no.991488

Item 174High Performance Polymers19, No.1, Feb.2007, p.78-96POLYKETANILS: PREPARATION OF PI-CONJUGATED POLYMER BASES FROM P-DIBENZOYLBENZENE WITH VARIOUS DIAMINES. PROTONATION WITH DL-CAMPHOR-10-SULPHONIC ACIDIwan A; Kasperczyk J; Kaczmarczyk B; Janeczek H; Jurusik J; Mazurak Z; Sek DPolish Academy of Sciences

New luminescent materials, aromatic polyketanils(PKs) containing p-phenylene and biphenylene linkages in the backbone and electron-donating side-group substitutions, were synthesised via melt polycondensation (180 deg.C, 24 h). Their structures were confirmed by elemental and spectral FTIR, 13C and “1H-NMR, and UV-visible analysis. All the PKs were solution-processable and thermally stable, making them potential candidate materials for applications in microelectronics and aerospace. These ketanil polymers showed high thermal stability and well-defi ned Tg. The temperature at which the polymers lost 10% of their weight ranged from 420 to 520 deg.C. Depending on the polymer structure, PKs showed Tg values in the range of 133 to 244 deg.C. The polymers emitted either blue radiation or green radiation depending on the mutual presence of conjugated and saturated chain segments. The HOMO/LUMO energy gap of the polymers was in the range of 2.74-2.19 eV. The photoluminescence properties of the PKs after protonation with DL-camphor-10-sulphonic acid(CSA) were tested. The structure formation of (PKs)1 (CSA)2 complexes is discussed on the basis of 1H-NMR spectroscopy. 32 refs.EASTERN EUROPE; POLAND

Accession no.990788

Item 175High Performance Polymers19, No.1, Feb.2007, p.33-47SYNTHESIS AND CHARACTERIZATION OF CYANATE EPOXY COMPOSITESJayakumari L S; Thulasiraman V; Sarojadevi MAnna,University

Anthraquinone dicyanate was prepared by treating CNBr with 1,4-dihydroxy anthraquinone in the presence of triethylamine at -5 to 5 deg.C. The dicyanate was characterised by FTIR spectroscopy. The prepared dicyanate was blended with commercial epoxy resin in different ratios and cured at 120 deg.C for 1 h, 180 deg.C for 1 h and post-cured at 220 deg.C for 1 h using diaminodiphenylmethane as the curing agent. Castings of neat resin and blends were prepared and characterised by FTIR analysis. The composite laminates were also

fabricated from the same composition. The mechanical properties such as TS, flexural strength and fracture toughness were measured as per ASTM D 3039, D 790 and D 5528, respectively. The TS increased with increasing cyanate content (3, 6, and 9%) from 52.1 to 80.1 MPa. The values of fracture toughness also increased from 0.7671 kJ.m2 for the neat epoxy resin to 0.9168 kJ.m2 for the 9% cyanate ester epoxy-modifi ed system. The thermal properties were also studied. The 10% weight loss temperature of pure epoxy was 358 deg.C and it increased to 381 deg.C with incorporation of cyanate ester resin. The incorporation of cyanate ester up to a 9% loading level did not affect the Tg to a very great extent. These new cyanate-modifi ed epoxy composites could have the potential to provide better performance in engineering and aerospace applications. 17 refs.INDIA

Accession no.990785

Item 176High Performance Polymers19, No.1, Feb.2007, p.3-20STUDIES ON THE SYNTHESIS AND CHARACTERIZATION OF DIGLYCIDYLETHER-TERMINATED POLYDIMETHYL SILOXANE-MODIFIED EPOXY-BISMALEIMIDE MATRICESKumar R S; Alagar MAnna,University

Diglycidylether-terminated polydimethylsiloxane (DGETPDMS) toughened epoxy matrix systems were deve loped and fu r the r mod i f i ed wi th bismaleimide(BMI), i.e. N,N’-bismaleimido-4,4’-diphenylsulphone. The matrix systems were cured using 4,4’-diaminodiphenylmethane(DDM) as curing agent. The mechanical, thermal, and electrical properties were studied by standard test methods. The introduction of DGETPDMS into epoxy resin improved the impact strength with reduction of TS, fl exural strength and Tg in comparison with the unmodifi ed epoxy, whereas the incorporation of BMI into epoxy resin improved TS, flexural strength, Tg and heat distortion temperature in comparison with the unmodifi ed epoxy resin. The incorporation of BMI into DGETPDMS-modifi ed epoxy resin improved thermal stability, dielectric strength, surface resistivity and arc resistance with increasing loading level. SEM micrographs of both BMI-modifi ed epoxy and BMI-modifi ed DGETPDMS-epoxy systems exhibited homogeneous morphology. The results obtained indicated that these hybrid matrix systems could be used to fabricate advanced composite components for engineering and aerospace applications with better performance and enhanced longevity. 24 refs.INDIA

Accession no.990783



Item 177Aiken, SC, c.2007, pp.12KYDEX THERMOPLASTIC SHEET PRODUCTS IN SPECIALIZED GRADES FOR DEMANDING APPLICATIONSKleerdex Co.LLC

Kydex proprietary thermoplastic was fi rst introduced by Rohm & Haas in 1965. It’s properties made it suitable for applications such as aircraft interiors. In 1987, the Kleerdex company purchased the Kydex product line and developed additional grades to provide the physical, electrical, and chemical properties and fi re ratings required to provide applications in mass transit vehicles, electrical enclosures, medical products and other demanding applications, as well as general purpose grades which outperform fi re retardant ABS and polycarbonate at comparable prices. In addition to thermoforming applications, Kydex sheet is also used as a protective wall covering. It is an extremely durable thermoplastic alloy, extruded in a range of colours, patterns, textures, thicknesses and grades. Specialised grades satisfy the requirements of thermoforming, membrane pressing, post forming, brake forming, laminating, and mitre folding. Production methods, applications, and features are described, and a standard grade overview is included giving tabulated technical details for a range of grades.USA

Accession no.989875

Item 178High Performance PlasticsDec.2006, p.1NANO-RESIN HAS BETTER MECHANICAL PROPERTIES

Nanoledge, a French nanotechnology company, has introduced a carbon nanotube-fi lled resin, which it has called “Nano in Res Laminates 1”, it is announced in this concise article. Brief details are presented about the new product, its properties, and its intended applications.

Nanoledge; CompositecEUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.989554

Item 179Polymer Plastics Technology and Engineering45, No.10-12, Oct.-Dec.2006, p.1143-1153STRUCTURAL CARBON/EPOXY PREPREGS PROPERTIES COMPARISON BY THERMAL AND RHEOLOGICAL ANALYSISCosta M L; Rezende M C; De Paiva J M F; Botelho E CBrazil,Centro Tecnico Aerospacial; Sao Paulo,Centro Universitario Salesiano; UNESP

Two different carbon fi bre/epoxy resin prepreg materials were characterised and compared using DSC, TGA, DMA

and rheological testing. A prepreg system currently used commercially in the aircraft industry (carbon fi bre prepreg/epoxy resin F584) was compared with a prepreg system that is a prospective candidate for the same applications (carbon fi bre prepreg/epoxy resin 8552). The differences in the curing kinetics mechanisms of both prepreg systems were identifi ed. Based on the thermal analysis techniques, it was proved that the curing of both epoxy resin systems followed a cure kinetic of n order. Even though their reaction heats were found to be slightly different, the kinetics of these systems were very similar. The activation energies for both prepreg systems were determined by DSC analysis, using Arrhenius’s method, and were found to be quite similar. DMA measurements of the cured prepregs demonstrated that they exhibited similar degrees of cure and different Tgs. Furthermore, the use of the rheological analysis revealed small differences in the gel temperatures of the two prepreg systems that were examined. 30 refs.BRAZIL

Accession no.988565

Item 180Macromolecular Materials and Engineering291, No.12, 8th Dec.2006, p.1449TWENTY YEARS OF POLYMER-CLAY NANOCOMPOSITESAkane Okada; Arimitsu Usuki Toyota Central R & D Laboratories Inc.

A report on the 20-year history of research into polymer/clay nanocomposites is presented by pioneers in this technology at Toyota Central R & D Laboratories. Nylon-clay nanocomposites are discussed with particular reference to the dry polymerisation method, wet polymerisation methods, compounding methods, and structure and reinforcement mechanism of nylon-6/clay hybrids. Composites of polyimide/clay, polyolefi n/clay, and rubber and thermosetting resin/clay are also described. Nanocomposite hydrogels and liquid crystal/clay composites are considered and the introduction of a layered microdomain structure in block copolymer by clay is examined. 112 refs.JAPAN

Accession no.988479

Item 181Materials Research9, No.3, July-Sept.2006, p.247-256A REVIEW ON THE DEVELOPMENT AND PROPERTIES OF CONTINUOUS FIBER/EPOXY/ALUMINIUM HYBRID COMPOSITES FOR AIRCRAFT STRUCTURESBotelho E C; Silva R A; Pardini L C; Rezende M CBrazil,Instituto de Aeronautica e Espaco; UNESP; Empresa Brasileira de Aeronautica

The development of lightweight hybrid composite laminates of continuous carbon or glass fi bre-reinforced



epoxy resin matrix and aluminium layers for aerospace applications and methods for their fabrication are reviewed. The properties of the laminates, including tensile and compression strength, shear strength and damping properties and the effects of moisture absorption are discussed in terms of the synergistic effects of the combination of metal and polymer composite laminates. 73 refs.BRAZIL

Accession no.987940

Item 182Lancaster, Pa., DEStech Publications, 2006, 126 PapersProceedings of a conference held Dearborn, Mi., 17th-20th Sept.2006PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES. TWENTY-FIRST TECHNICAL CONFERENCE. Edited by: Mallick P K(American Society for Composites; Michigan-Dearborn,University)

Over a hundred papers are presented at this twenty-fi rst technical conference of the American Society for Composites. Papers are divided into the following sessions: fatigue and fracture, composite overwrapped pressure vessels (COPV), impact/impact damage, testing and evaluation, nanocomposites, foamed composites, textile composites, natural fi bre composites, multifunctional composites, joining, environmental effects, analysis, processing, automotive/aerospace applications, civil structures, and education.USA

Accession no.987883

Item 183Macromolecules 40No.2, 23rd Jan.2007, p.290-296MECHANICS OF POLYMER-CLAY NANOCOMPOSITESYuanQiao Rao; Pochan J M Eastman Kodak Co.

The mechanics of polymer-clay nanocomposites is studied using a designed polymer and solution nanocomposite synthesis. A copolymer latex with functional groups that interact strongly with the surface of the clay nanoplatelet and Tg lower than room temperature is synthesised. Uniformly dispersed nanocomposites are then generated using water as the intercalation agent. The chain mobility is studied by dynamic mechanical thermal analysis and dielectric thermal analysis. The modulus of the composite increases signifi cantly and this enhancement is studied experimentally and theoretically. The structure of the nanocomposites is also discussed. 30 refs.USA

Accession no.986861

Item 184Journal of Materials Science41, No.20, Oct.2006, p.6718-6724IMPACT DAMAGE TO THICK CARBON FIBRE REINFORCED PLASTIC COMPOSITE LAMINATESBreen C; Guild F; Pavier MBristol,University; London,University,Queen Mary College

Impact resistance of thick carbon fi bre-reinforced epoxy resin composite laminates for aerospace applications was investigated experimentally by drop weight impact testing followed by examination of the geometry of the damage by C-scan, deply and post-impact strength measurements. The effects of central and edge impacts on the geometry of damage and residual tensile and compressive strengths are discussed. 11 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.984714

Item 185Textile Progress38, No.4, 2006, p.1-71HYBRID YARNS AND TEXTILE PREFORMING FOR THERMOPLASTIC COMPOSITESAlagirusamy R; Fangueiro R; Ogale V; Padaki N

A comprehensive review is presented on thermoplastic hybrid yarns, which includes sections on types of hybrid yarns, hybrid yarn characterisation, textile preforming, manufacture of thermoplastic composites with hybrid yarns and textile preforms, compaction and consolidation of hybrid yarns, hybrid yarn structure-composite property relations, potential applications for thermoplastic composites and trends in thermoplastic composite applications (natural fibre reinforced thermoplastic composites, environmental issues and recyclability). 214 refs.

Accession no.983116

Item 186High-Performance Composites14, No.5, Sept.2006, p.28-34ENGINEERED TO INNOVATEGardiner G

In the 1970s, in space and aircraft applications, aluminium honeycomb became the core of choice. Today, aluminium honeycomb shares the market with aramid and carbon honeycombs in prepreg constructions, and honeycomb is no longer the only core in town. Advanced composite sandwich constructions are employed in a broad range of applications that involve performance demands, moulding methods and constraints on labour, time and cost that make honeycomb’s open cell structure impractical. Albany Engineered Composites has ramped up production of X-COR, its innovative structural core material, which has



been selected for use in the new all-composite tailcone, part of a major upgrade of the US Army’s UH60M Black Hawk helicopter. For a jet engine fan case, WebCore is using a combination of TYCOR core material, with carbon fi bre reinforcement and rigid 100% PMI closed cell foam, and braided fabric skin, which is integrally stitched through the thickness of the entire sandwich structure.WORLD

Accession no.981661

Item 187Journal of Thermoplastic Composite Materials19, No.6, Nov.2006, p.715-729MOISTURE EFFECT ON THE INTERLAMINAR RESISTANCE OF WOVEN FABRIC THERMOPLASTIC COMPOSITEZenasni R; Saadi B AMostaganem,University; Oran,University of Sciences and Technology

An investigation was carried out into the effect of moisture on the interlaminar fracture toughness of woven fabric 8H Satin glass fi bre and 8H Satin carbon fi bre reinforced polyetherimide composites of the type used in aeronautical and aerospace applications. Interlaminar fracture behaviour was analysed using the Mode I, double cantilever beam test and Mode II, end notched fl exure to determine the energy required for initiation and growth of cracks. Delamination energies were calculated using various methods and the fracture mechanism was analysed using scanning electron microscopy. 22 refs.ALGERIA

Accession no.980944

Item 188ANTEC 2006. Proceedings of the 64th SPE Annual conference held Charlotte, NC., 7th-11th May 2006.Brookfi eld, Ct., SPE, 2006, p.258-62HARNESSING MOLECULAR FORCES TO EXFOLIATE CLAY IN THERMOSET SYSTEMSGintert M J; Jana S C; Miller S GAkron,University; US,NASA,Glenn Research Center(SPE)

Layered silicate PMR-15 polyimide nanocomposites are being developed for high-performance aerospace applications. The goal is to achieve full exfoliation under quiescent conditions using a novel approach, whereby intra- and extra-gallery modulus and viscosity are engineered to result in a net force pushing clay layers apart during cure. The current study explores treatment of clay with reactive surfactants which are thermally stable and participate in crosslinking with PMR resin, providing higher thermo-oxidative stability than possible with current technologies. 20 refs.USA

Accession no.980308

Item 189Journal of Composite Materials40, No.20, 2006, p.1871-1883CONSOLIDATION OF REACTIVE ULTEM POWDER-COATED CARBON FIBER TOW FOR SPACE STRUCTURE COMPOSITES BY RESISTIVE HEATINGNaskar A K; Edie D DClemson,University

A crosslinkable, radiation-resistant, phenylethynyl-terminated polyetherimide (Ultem) was applied to carbon fibre tows using a powder coating procedure and an electrical current passed across the coated fi bre tows to melt the thermoplastic powder and form rigid composites, which were characterised by scanning electron microscopy and tensile testing. The melting temperature and specifi c heat of the thermoplastic were measured by differential scanning calorimetry. The power requirement for wetting the fi bre tows with the powder on earth and in outer space was determined by measuring the applied current and degree of consolidation and the curing of the composite was monitored by torsional oscillatory rheological measurements. The results obtained showed that the resistive heating technique was feasible for producing rigid infl atable composites for aerospace applications. 19 refs.USA

Accession no.979869

Item 190European Design EngineerOct.2006, p.46/48THE SKY’S THE LIMIT FOR EPOXY ADHESIVES AND SYNTACTICSChristou PHuntsman Advanced Materials (Switzerland) GmbH

Some of the latest product developments in the fi eld of epoxy resin syntactics and structural adhesives, which can meet the requirements of a range of critical and demanding applications for aerospace manufacturing and repair industries, are described. These developments include an epoxy-based aerofoil syntactic paste for engine vibration damping and a bromine-free, fl ame retardant epoxy syntactic paste for high strength reinforcement in honeycomb core parts.SWITZERLAND; WESTERN EUROPE

Accession no.979107

Item 191Modern Plastics Worldwide83, No.10, Oct.2006, p.88-89PEEK-BASED COMPOSITES

PEEK is now being used as the polymer matrix for thermoplastic composite prepregs, suspending carbon, glass or aramid continuous fi bres for a composite material that can replace metals and thermosets in aerospace,



offshore, medical and industrial applications. The material comes in viscosities ranging from standard, to medium, to very low. PEEK is able to withstand continuous operating temperatures of up to 260 deg.C in low-stress applications and 120 deg.C in aerospace structural applications. Victrex has partnered with composite producers to create dry and multiaxial fabrics; braid, two and unidirectional tape; unidirectional sheet; and consolidated fabric, it is briefl y reported.

Victrex USA Inc.USA

Accession no.978301

Item 192High Performance PlasticsJune 2006, p.4BENZOXAZINE RESINS

Henkel KGaA of Germany has commercialised a range of low-viscosity, one-part benzoxazine resins for use in the manufacture of large fi bre-reinforced plastic parts for aerospace applications. The resins are stable at ambient temperature, have a long pot-life, and are easy to process. This abstract includes all the information contained in the original article.

Henkel KGaAEUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.977783

Item 193SAMPE ‘06: Creating New Opportunities for The World Economy: Volume 51. Proceedings of a conference held Long Beach, Ca., 30th April-4th May 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 36, pp.12 DESIGNING COMPOSITE STRUCTURES FOR THE MANUFACTURING PROCESSUngaro P; Grape JVISTAGE INC.(SAMPE)

Examples of applications in the aerospace and automotive industries are presented, demonstrating how new software enables composite designers and manufacturing engineers to more effi ciently and reliably work together using an integrated Design for Manufacturing process. Three areas of major progress in composite design and manufacturing are covered, namely automated deposition methods, forming and stamping and assembly design, and Vistagy’s Aircraft Design Environment is introduced as an example of a specialised computer aided design environment for effi cient and consistent defi nition of composite assemblies. 3 refs.USA

Accession no.977507

Item 194SAMPE ‘06: Creating New Opportunities for The World Economy: Volume 51. Proceedings of a conference held Long Beach, Ca., 30th April-4th May 2006.Covina, Ca., SAMPE International Business Offi ce, 2006, Paper 3, pp.8NEW LOW STRESS FILM ADHESIVE FOR AEROSPACE APPLICATIONS REQUIRING LOW OUTGASSINGRiegler B; Kaelani F; Long D ANuSil Technology LLC(SAMPE)

The chemistries of silicone and film adhesives are described and the characteristics of a new silicone fi lm adhesive, which combines low outgas properties required for space applications with consistent bond thickness, are reported. The new fi lm adhesive is compared with a low outgas liquid adhesive and is considered suitable for various applications common to satellite manufacturing. 7 refs.USA

Accession no.977488

Item 195SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.Covina, Ca., ACS, SAMPE International Business Offi ce, 2005, paper 82, pp.9ADVANCED COMPOSITE STRUCTURES USING NEW RESIN TECHNOLOGY OFFER WEIGHT AND COST SAVINGSWei H Li; Lehmann S L; Wong R SHenkel Corp.(SAMPE)

To fi ll the gap in service temperatures for composite structures between the high performance epoxy materials at glass transition temperatures at 140 deg.C and BMI at around 220 deg.C, a new range of benzoxazine resins was developed and is described. Resin properties were characterised, including density, shrinkage, moisture uptake, glass transition temperature, compression strength and modulus and notched bend strength. Use of the resins in resin transfer moulding (RTM), resin fi lm infusion, vacuum-assisted RTM, and prepreg applications was discussed. Composites were said to be easy to process and have lower cure shrinkage, superior compression strength and modulus, and a good blend of glass transition temperature and toughness. 6 refs.USA

Accession no.977336

Item 196SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.



COVINA, CA., ACS, SAMPE INTERNATIONAL BUSINESS OFFICE, 2005, PAPER 175, PP.15 VARTM PROCESSING OF TAILORED COMPOSITE STRUCTURES FOR AEROSPACE APPLICATIONSLoos A C; Grimsley B W; Cano R J; Hubert PMichigan,State University; NASA Langley Research Center; McGill University(SAMPE)

Tailored composite structures were prepared using a preform of layers of a uni-weave carbon fi bre fabric coated with tackifi er, followed by impregnation by resin using a modifi ed vacuum-assisted resin transfer moulding process (VARTM). Better mechanical properties were found in the composite than in an equivalent structure prepared by a commercial resin infusion process, due to the increase in fi bre volume obtained in the VARTM process. A model developed to predict infiltration times was evaluated visually using a transparent mould and SAE40 engine oil to simulate the resin, and was found to be accurate. 7 refs.CANADA; USA

Accession no.977300

Item 197Polymer Engineering and Science46, No.8, 2006, p.1079-1084DEVELOPMENT OF NANOPARTICLE-POLYSILOXANE COMPOSITES FOR SPACECRAFT APPLICATIONSHidden G; Boudou L; Martinez-Vega J; Remaury S; Nabarra PToulouse,Universite Paul Sabatier; CNES

In orbit, satellites are exposed to significant thermal variations. To ensure reliable operation of their on-board systems and equipment, a thermal control of the spacecraft is necessary using cold, neutral or warm coatings. The Materials and Coatings Laboratory of the Thermal Control Services at CNES has elaborated a cold coating version by using a polysiloxane deposit on a metal substrate (such as polished aluminium or vacuum deposited silver). In geostationary orbit, polysiloxane, which has a high electrical resistivity, can accumulate implanted charges that can give rise to electrostatic discharges and damage the neighbouring electronic systems. To prevent any electrostatic discharge problems in geostationary orbit, the resistivity of coatings should be reduced without altering their thermo-optical properties, in particular the low solar absorptivity and the high emissivity for cold coatings. Several methods have been studied, such as the incorporation of carbon nanotubes (CNT) and indium tin oxide (ITO) nanoparticles in the polysiloxane matrix, with the objective of attaining a high transparency, a high emissive, and an antistatic resin. In this paper, the infl uence on thermo-optical properties of CNT-Polysiloxane and ITO-Polysiloxane composites, as a function of sample thickness d (micro m) and nanoparticles concentration p (%wt), is reported. 7 refs.

EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.977187

Item 198Polymer Composites27, No.4, 2006, p.402-409EPOXY-MODIFIED CYANATE ESTER RESIN AND ITS HIGH-MODULUS CARBON-FIBER COMPOSITESRen P; Liang G; Zhang ZXian,University of Technology; Xian,Northwestern Polytechnical University

Epoxy E51-modifi ed bisphenol A dicyanate (BADCy) and its high-modulus carbon fibre (M40) reinforced composites were prepared in this research. The carbon-fi bre composites were prepared by autoclave moulding. Differential scanning calorimetry (DSC) and Fourier transform infrared (FTIR) spectroscopy of BADCy-E51 blend systems showed that polycyclotrimerisation of BADCy primarily took place at low temperature. Epoxy group reacted with triazine ring group and produced oxazolidinone at high temperature. The data of mechanical properties, water absorption, and heat defl ection temperature (HDT) of cured castings showed that the matrix system containing 95 wt% BADCy and 5 wt% E51 had optimum characteristics. Scanning electron microscopy (SEM) analysis of M40 fi bre and the fracture surfaces of M40/BADCy-E51 composite displayed that the adhesion between M40 fi bre and BADCy was good though the surface of M40 was inert. The high retention of mechanical properties of M40/BADCy-E51 composite after long-term exposure to environmental conditions indicated that the M40/BADCy composite was suitable for space applications. 18 refs.CHINA

Accession no.977176

Item 199Journal of Applied Polymer Science102, No.2, 15th Oct.2006, pp. 1959-1967MODIFICATION OF HIGH-PERFORMANCE POLYMER COMPOSITE THROUGH HIGH-ENERGY RADIATION AND LOW-PRESSURE PLASMA FOR AEROSPACE AND SPACE APPLICATIONSBhowmik S; Bonin H W; Bui V T; Weir R DCanada,Royal Military College

Attempts were made to modify polybenzimidazole (PBI) by high-energy radiation and low-pressure plasma treatment to permit the preparation of composites with the same polymer. The PBI composites were prepared by using an ultra-high-temperature-resistant epoxy adhesive to join the two polymer sheets. The adhesive had a service temperature range of -260 to +370 deg.C and was highly resistance to acids, alkalis, solvents, corrosives, radiation,



and fi re. Before preparing the composite, the surface of the PBI was ultrasonically cleaned in acetone and modifi ed by high-energy radiation for 6 h in the pool of a nuclear reactor that produced a mixed fi eld of thermal and epithermal neutrons, energetic electrons, and protons, and gamma-rays at a dose rate of 37 kGy/h. Alternatively, the polymer was subjected to low-pressure plasma treatment with a 13.56-MHz radio-frequency glow discharge for 120 s at 100-W power with nitrogen as the process gas. A considerable increase in the joint strength was observed when the polymer surface was modifi ed by either process. A further signifi cant increase in joint strength occurred when the polymer surface was initially modified by exposure to low-pressure plasma followed by exposure to high-energy radiation. To simulate conditions in space, the joints were exposed to cryogenic (-196 deg.C) and high temperatures (+300 deg.C) for 100 h. Joints exposed to these conditions retained about 95% of their strength. Microscopic examination of fractured surfaces of the joints showed that the surface-modifi ed polymer essentially failed cohesively within the adhesive. 21 refs.CANADA

Accession no.977162

Item 200SAMPE ‘05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.Covina, Ca., SAMPE International Business Offi ce, 2005, Paper 229, pp. 11EFFECTS OF PROCESSING PARAMETERS ON THE MECHANICAL PROPERTIES OF CARBON/PEKK THERMOPLASTIC COMPOSITE MATERIALSSalek M H; Hoa S VConcordia,University(SAMPE)

The effects of processing parameters on the mechanical properties of carbon/polyetherketoneketone (PEKK) thermoplastic composite laminates is described. Flat laminates are processed by compression moulding and the tensile strength and moduli determined. SEM is used to observe the different microstructures arising from the different processing conditions. Optimum properties for the laminates are established. The range of parameters can serve as a guide to consolidate carbon/PEKK laminates for high performance aerospace applications. 9 refs.CANADA

Accession no.976910

Item 2018th World Pultrusion Conference: Emerging Markets: Globalization of the Pultrusion Industry. Proceedings of a conference held Budapest, Hungary, 22nd-24th March 2006.Leusden, EPTA, 2006, Paper 6, pp.11

NOVEL USE OF CYANATE ESTERS IN HIGH TEMPERATURE PULTRUSION APPLICATIONSDas SLonza Inc.(European Pultrusion Technology Assn.)

A report is presented on advances in new cyanate ester chemistries, catalyst technology and extended pot-life during processing, which have allowed cyanate esters to be used in applications, such as air ducts for aircraft, requiring vacuum assisted resin transfer moulding, fi lament winding and pultrusion. Resins under consideration in this article are Primaset PT-30, Primaset PT-15 and Primaset-LECY, which can be toughened and synthesised using snap cure catalysts. 11 refs.USA

Accession no.976457

Item 202SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.Covina, Ca., ACS,SAMPE International Business Offi ce, 2005, Paper 7, pp.8SURFACE PREPARATION FOR METALLIC BONDED REPAIR: A COMPARISON OF METHODS FOR NAVAL FLEET DEPLOYMENTTillman M S; Manson R TNAVAIR(SAMPE)

Surface preparation presents major problems for bonded repair of aircraft on vessels at sea. Sol-gel based surface preparations were evaluated and compared to traditional surface preparations such as phosphoric acid and others treatments. It was found that sol-gel methods provided a robust way of chemically treating metallic surfaces, with compatibility to several adhesive systems being of further value in applications of this type. Test methods involved bonding of samples followed by lap shear testing and peel testing during exposure to various environmental conditions. 17 refs.USA

Accession no.976144

Item 203SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.COVINA, CA., ACS,SAMPE INTERNATIONAL BUSINESS OFFICE, 2005, PAPER 5, PP.14 FORMULATION AND EVALUATION OF CARBON NANOFIBRE-BASED CONDUCTIVE ADHESIVESGibson T; Rice B; Ragland W; Silverman E M; Hsaio-hu Peng; Strong K L; Moon DDayton,University,Research Institute; Northrop Grumman Space Technology; US,Air Force Research



Laboratory; ATK Composites(SAMPE)

Developments of epoxy adhesives containing either silver coated or uncoated carbon nanofi bres, for applications requiring electrical conductivity in the aerospace industries, is described. Adhesives were compared to current systems using structural adhesives and electrical bonding, and formulations containing silver coated carbon nanofi bres were found to meet requirements for prevention of static discharges whilst maintaining lap shear strength at joints. Viscosity testing of adhesives, scanning electron microscopy of ruptures surfaces and conductivity testing were used in evaluation of the adhesives. 6 refs.USA

Accession no.976142

Item 204SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.Covina, Ca., ACS,SAMPE International Business Offi ce, 2005, Paper 3, pp.16LIQUID CRYSTALLINE THERMOSETS FOR HIGH TEMPERATURE ADHESIVE APPLICATIONSHaight A E H; Allred R EAdherent Technologies Inc.(SAMPE)

Melt processable liquid crystalline thermoset (LCT) adhesives based on ester bismaleimide monomers and liquid crystalline comonomers such as methylene dianiline (MDA) and diaminodecane were prepared by solution or solid state mixing. Some of these materials showed a wide processing range and excellent thermal stability in air up to temperatures above 400 deg.C. Monomers were characterised according to normal analytical methods, and adhesives were characterised for their curing characteristics by differential scanning calorimetry and polarised optical microscopy, and by lap-shear strength testing and thermogravimetric analysis. It was seen that liquid crystalline order was maintained in the cured system, giving high strength and low coefficients of thermal expansion. Adhesion tests were carried out on a number of substrates including aluminium, titanium and composite materials. Adhesives based on MDA showed the most promise. 9 refs.USA

Accession no.976140

Item 205SAMPE '05: New Horizons for Materials and Processing Technologies. Proceedings of a conference held Long Beach, Ca., 1st-5th May 2005.Covina, Ca., ACS,SAMPE International Business Offi ce, 2005, Paper 2, pp.9SHELF-STABLE LOW TEMPERATURE CURE

EPOXY FILM ADHESIVE FOR ON-AIRCRAFT BONDED REPAIRKovar R F; Weatmark C; Temchenko M; Tiano TFoster-Miller Inc.(SAMPE)

For aircraft applications a shelf stable epoxy film adhesive was developed that incorporated a cure catalyst incorporated within crosslinked gelatin microcapsules. Cure could be activated by either crushing or by temperature. Epoxy resins of this type were characterised for their shelf stability at different temperatures, and for their mechanical properties before and after cure at either 49 or 121 deg.C using elemental analysis, differential scanning calorimetry, torsion braid analysis, peel testing and lap-shear strength. 5 refs.USA

Accession no.976139

Item 206Journal of Composite Materials 40, No.17, 2006, p.1511REVIEW ARTICLE: POLYMER-MATRIX NANOCOMPOSITES, PROCESSING, MANUFACTURING, AND APPLICATION: AN OVERVIEWHussain F; Hojjati M; Okamoto M; Gorga R E Canada,National Research Council; Toyota Technological Institute; North Carolina,State University

The processing, manufacture, characterisation, structure-property relationships, health and safety issues and commercial applications of nanocomposites of thermoplastics with various nanoparticles, including layered silicates and organically modified silicates, graphite nanoplatelets, carbon nanotubes and nanofi bres, are comprehensively reviewed. The future outlook for polymer-matrix nanocomposites, including biodegradable nanocomposites derived from renewable resources, is also discussed. 350 refs. CANADA; JAPAN; USA

Accession no.976134

Item 207Popular Plastics and Packaging51, No.9, Sept.2006, p.73-78SHAPE MEMORY POLYMERS - MATERIALS OF THE FUTURESaroop M; Sarkar ANew Delhi,Indian Institute of Technology; ICI India Ltd.

Shape memory is the ability of a material to recover its original shape, either after mechanical deformation, which is a one way effect, or by cooling and heating, which is a two way effect. This phenomenon is based on structural phase transformation. Shape Memory Polymers exhibit the same physical phenomenon as Shape Memory Alloys, but



are lighter in weight, lower in cost, can be easily processed into complex shapes and exhibit larger recovery strains. Excellent shape memory effect has been observed with trans-polyisoprene, styrene-butadiene copolymer and segmented PUs. The structure of shape memory polymers and shape memory behaviour is discussed. Applications include: biomedical such as implants and smart sutures; aerospace morphing systems; and manufacturing, including composite tooling for fi lament winding. Next generation technologies include self-repairing structural materials, smart coatings in defence applications and self-repairing coatings for automotive and marine applications. 37 refs.INDIA

Accession no.975980

Item 208High-Performance Composites14, No.4, July 2006, p.44-50LIGHTNING STRIKE PROTECTION FOR COMPOSITE STRUCTURESGardiner G

General aviation aircraft, large commercial jets and wind turbines are vulnerable to lightning strike. Unlike their metal counterparts, composites structures in these applications do not readily conduct away the extreme electrical currents and electromagnetic forces generated by lightning strikes. Lightning strike protection strategies have three goals: provide adequate conductive paths so that lightning current remains on the structure’s exterior; eliminate gaps in this conductive path to prevent arcing at attachment points and ignition of fuel vapours; and protect wiring, cables and sensitive equipment from damaging surges. Traditionally, conductive paths in composite structures have been established in one of the following ways: bonding aluminium foil to the structure as the outside ply; bonding aluminium or copper mesh to the structure either as the outside ply or embedded one ply down; or incorporating strands of conductive material into the laminate. Among the newest developments are “all-in-one” LSP prepregs, which contain pre-embedded woven or nonwoven metal meshes.USA

Accession no.975958

Item 209Composites Science and Technology66, No.14, 2006, p.2500-2505FORCE PROTECTION USING COMPOSITE SANDWICH STRUCTURESSierakowski R L; Hughes M LUS,Air Force Research Laboratory; Auburn,University

In the recent past, advances have been made in the attempt to utilize composite materials as components in protective structures such as those employed by the Air Force to secure critical military assets. In such applications, where

lightweight materials that exhibit large levels of energy absorption and high strength/stiffness characteristics are desirable, composite sandwich constructions offer an attractive solution. In an attempt to evaluate the suitability of certain sandwich structures for use in force protection applications, several sandwich constructions with somewhat novel core materials were identifi ed. A group of thermoplastic core materials have been developed that possess features of both a dense elastic solid and a foam type material. This class of core materials incorporates sloping cell walls, rather than the traditional parallel cell wall structure present in, say, a regular aluminium honeycomb. This feature, along with the increased surface area connectivity present between cells (produced by the forming process used to create the core materials) integrates surrounding cells into what may be described as an enhanced hexagonal single unit cell structure. To develop a preliminary understanding of the response of these enhanced cellular materials to the various loading regimes that could be encountered in a protective structure, a series of static and dynamic tests were conducted at Tyndall Air Force Base. A complete description of the novel core materials, as well as the results of the static and dynamic tests, will be presented in this paper. 4 refs. Copyright (c) 2006 Elsevier LtdUSA

Accession no.975777

Item 210Composites Science and Technology66, No.14, 2006, p.2465-2472ON THE DYNAMIC RESPONSE OF SANDWICH COMPOSITES AND THEIR CORE MATERIALSMahfuz H; Thomas T; Rangari V; Jeelani SFlorida,Atlantic University; MeadWestvaco Corp.; Tuskegee,University

Sandwich composites are being aggressively pursued as structural materials by various defence and commercial industries. These include navy, air force, army, automotive and sporting industries to name a few. In the context of structural load bearing members and absorbing dynamic loads, foam core sandwich composites offer unique advantages over traditional composites. The cellular construction of the foam materials not only provides lightweight capability but also a deformation mechanism that allows effi cient absorption of energy. Of particular interest in this study is to investigate the behaviour of the foam materials and their sandwiches under high strain rate (HSR) loading which are very much prevalent in their actual applications. A systematic approach has been taken to study the response of PVC foam materials at strain rates ranging from quasi-static to around 2000 s-1. First, room temperature response has been extracted for various density foams, and determined their strain rate sensitivities and failure characteristics. Next, two microstructures in the construction of the core materials, namely linear and cross-linked foams, were considered in the investigation.



This study revealed that both the categories of foam had direct dependence on temperatures well below the T”g of the base polymer. Consequently, the next phase of the investigation included HSR tests at elevated and sub-ambient temperatures. The study has established that at room temperature (RT), the delamination at the sub-interface zone underneath the actual core-skin interface is the critical mode of failure. This sub-interface is characterized by the separation of the dry and resin-soaked cells near the core-skin interface. Failure modes however changed as the test temperature changed from RT to sub-ambient. 20 refs. Copyright (c) 2006 Elsevier LtdUSA

Accession no.975776

Item 211Composite Structures75, No.1-4, 2006, p.472-478EXPERIMENTAL EVALUATION OF DYNAMIC BEHAVIOR OF METALLIC PLATES REINFORCED BY POLYMER MATRIX COMPOSITESShokrieh M M; Najafi AIran,University of Science & Technology

The applications of composite materials have become common in different industries. These materials introduce lower weight, high strength, and viscoelastic properties. Although composite materials offer many advantages in the designing and manufacturing of structures, they cannot replace the wide range of using metallic materials. Most of the industries especially aerospace try to use composite materials together with metal advantages in order to design a safe and optimized structure. The offshore structure can be reinforced and repaired with composite layers. In this research, the effects of composite reinforcement on the dynamic behaviour of metallic plates are studied. Several panels are treated with different lay-ups and the modal testing was conducted to evaluate the effect of such treatments. This reinforcing can change both stiffness and damping properties of structures. The stiffness properties of such reinforced plates can be infl uenced by fi bre properties, while the damping properties come from the viscoelastic property of the matrix. Modal testing is applied to the specimens and the modal parameters are derived experimentally. This study shows that using composite material can modify both stiffness and damping characteristics. 24 refs. Copyright (c) 2006 Elsevier LtdIRAN

Accession no.975695

Item 212Polymer47, No.17, 2006, p.6091-6098NEW KINDS OF PHENYLETHYNYL-TERMINATED POLYIMIDE OLIGOMERS WITH LOW VISCOSITY AND GOOD HYDROLYTIC

STABILITYRao X; Zhou H; Dang G; Chen C; Wu ZJilin,University

In continuing studies to develop low melt viscosity phenylethynyl end-capped imide oligomers for aerospace applications, new kinds of all-aromatic phenylethynyl-terminated imide oligomers were prepared by the reaction of 3,3’,4,4’-benzophenonetetracarboxylic dianhydride (BTDA) or biphenylenetetracarboxylic dianhydride (s-BPDA) with 2,5-bis(4-aminophenoxy)-biphenyl (p-TPEQ) and 4-phenylethynylphthalic anhydride (PEPA) or 4-(1-phenylethynyl)1,8-naphthalic anhydride (PENA). The oligomers bearing pendant phenyl groups exhibit much lower melt viscosities at low temperatures, and thus provide wide processing window. The thermal curing process of the oligomers was investigated with DSC. The tensile and thermal properties of the cured fi lms were evaluated. Oligomers derived from PENA cured at lower temperatures and the corresponding cured polymers show better hydrolytic stability than those of PEPA. Results showed that the utilisation of diamine monomer (p-TPEQ) can improve the processability and solubility of phenylethynyl-terminated imide oligomers without sacrifi cing their thermo-oxidative stability. 36 refs.CHINA

Accession no.975595

Item 213Journal of Advanced Materials38, No.3, July 2006, p.68-74WHAT WE DREAMT AS CHILDREN - HOW CONDUCTIVE POLYMERS ARE BRIDGING OUR DREAMS TO REALITYHansen GMetal Matrix

A review is presented of the literature on the breadth of materials used to create conductive polymers and on the depth of the research on their use as multifunctional materials. Methods for rendering polymers electrically conductive are described, together with intrinsically conductive polymers and conductive additives for plastics. The use of nanomaterials as conductive additives is considered. A few brief examples of applications of conductive polymers are given, including controlled conductivity, electromagnetic shielding, lightning strike protection of aircraft, elastomers and sensors, and shape memory polymers. 35 refs.USA

Accession no.975385

Item 214Kunststoffe International96, No.7, 2006, p.54-56HIGH PURITY PLUS OUTSTANDING RESISTANCEVan der Weide I; Werth M



Zotefoams PLC; Arkema

The manufacture of high-performance foams based on polyvinylidene fl uoride in a specifi c physical foaming process is described. The resultant foams are shown to combine low weight and insulating characteristics with the resistance to elevated temperatures, corrosive chemicals, fi re and ionising radiation that is typical of PVDF. Data on these properties are included. This property profi le is shown to open up numerous applications in the aviation, chemical and construction industries, and also in architecture.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; UK; WESTERN EUROPE

Accession no.975342

Item 215High Performance PlasticsApril 2006, p.12LOW DENSITY FOAMAt Sandia National Laboratories in the USA, scientists are reported to have developed a low-density PU foam which does not need toluene diisocyanate (TDI) - a possible human carcinogen. Brief details are given in this short article of possible applications of the new foam, which is known as “TufFoam”.Sandia National Laboratories; International Agency for Research on CancerUSA

Accession no.975265

Item 216Polymer Preprints. Volume 46. Number 1. March 2005. Papers are presented at the ACS meeting held San Diego, Ca., March 2005.Washington, D.C., ACS,Div.of Polymer Chemistry, 2005, p.426-427LIBRARIES OF NANOSIZED POLYFUNCTIONAL PLATFORMS AND NANOCOMPOSITES FROM SISESQUIOXANESLaine R M; Brick C; Asuncion M; Roll S; Sulaiman S; Lee M; Kennedy VMichigan,University; Mayaterials.com(ACS,Div.of Polymer Chemistry)

Developments in areas of epoxy materials for use in aircraft underfi lls and epoxy resin coatings for use in anticorrosion applications on aluminium, using cubic silsesquioxane networks in epoxy resin networks, was discussed. Tailoring of various materials by use of nano-building blocks was considered and materials already prepared were listed. 6 refs.USA

Accession no.974786

Item 217Polymer Preprints. Volume 46. Number 1. March 2005. Papers are presented at the ACS meeting held San

Diego, Ca., March 2005 Washington, D.C., ACS,Div.of Polymer Chemistry, 2005, p.190-191CHARACTERIZATION OF LAYER-BY-LAYER ASSEMBLED CARBON NANOTUBE/POLYELECTROLYTE FILMSGupta S; Huang G; Lu H; Mamedov A ANomadics Inc.; Oklahoma State UniversityACS,Div.of Polymer Chemistry

The properties of nanocomposites of single-walled carbon nanotubes (SWNTs) and polyelectrolyte [poly(dimethyldiallylammonium chloride) or poly(acrylic acid)] assembled layer by layer were examined by nanoindentation testing. The uniaxially relaxation modulus was extracted from the load-displacement curve. The modulus of the SWNT/polymer fi lm is much larger than that of a fi lm consisting of polymers alone. The measured modulus was verifi ed by fi nite-element simulation. 10 refs.USA

Accession no.974698

Item 218Polymer Preprints. Volume 46. Number 1. March 2005. Papers are presented at the ACS meeting held San Diego, Ca., March 2005.Washington, D.C., ACS,Div.of Polymer Chemistry, 2005, p.556-557SHAPE MEMORY POLYMER NANOCOMPOSITES; MULTIFUNCTIONAL MATERIALS FOR REVOLUTIONARY APPLICATIONS.Havens E; Dietsch B A; Tong T H; Hood P JCornerstone Research Group Inc.ACS, Div.of Polymer Chemistry

The potential applications of shape-memory polymer nanocomposites are discussed. Materials such as Verifl ex and Veritex can be formed into structures that transform into other structures on heating by an electrical current. Such materials can, for example, be used to produce aircraft parts that change shape when heated by an electrical current to change the fl ight characteristics of the aeroplane. The shape memory effect can also be triggered by other stimuli, such as light or electricity. 0 refs.USA

Accession no.974648

Item 219High Temperature Polymers: Advances and Applications. Proceedings of a conference held Clearwater Beach, Fl., 20th-21st Feb. 1995.Plymouth, Mi., 1995, Paper 3, pp.48 AURUM: NEW TPI-THERMOPLASTIC POLYIMIDE: PROPERTIES AND APPLICATIONSSanguigni J AAdvanced Web Products Inc.



(Executive Conference Management Inc.)

Very comprehensive property data are presented in the form of technical data sheets for Aurum, a new thermoplastic semi-crystalline thermoplastic polyimide developed by Mitsui Toatsu Chemicals Inc. Aurum is an engineering plastic with high performance properties and excellent processability. Information is presented relating to its heat resistance, mechanical and electrical properties, environmental resistance, processability, and its applications in mechanical components and automotive engines.

MITSUI TOATSUJAPAN; USA

Accession no.974309

Item 220High Temperature Polymers: Advances and Applications. Proceedings of a conference held Clearwater Beach, Fl., 20th-21st Feb. 1995.Plymouth, Mi., 1995, Paper 2, pp.22AEROSPACE APPLICATIONS FOR POLYIMIDES AND OTHER HIGH TEMPERATURE POLYMERSScola D AConnecticut,University(Executive Conference Management Inc.)

This paper reviews the most recent high temperature polymers which are currently being considered for, or which have the potential for, use in aerospace applications. The chemistry and thermooxidative stability of such polymers are presented, and engine applications for advanced composites are examined. In particular, consideration is given to polymers which have the potential for short term applications at 371 deg.C, their synthesis and structural similarities. Polymer and composite stability at 371 deg.C are compared and also the mechanical properties at room temperature and at 371 deg.C before and after ageing at 371 deg.C in 1 and 4 atmosphere of air are presented. Polymer composite development opportunities in subsonic, commercial, military and high speed civil transport aircraft propulsion systems are reviewed. 21 refs.USA

Accession no.974308

Item 221Composites Technologies for 2020. Proceedings of the Fourth Asian-Australasian Conference on Composite Materials (AACM-4), held Sydney, Australia, 6th-9th July 2004.Cambridge, Woodhead Publishing, 2004, p1018-1024DELAMINATION MONITORING OF CFRP LAMINATES USING ELECTRICAL POTENTIAL METHODUeda M; Todoroki A; Shimamura Y; Kobayashi HTokyo,Institute of Technology(Asian-Australasian Association for Composite Materials)

Carbon fi bre-reinforced plastic laminates in aerospace applications are monitored using the electrical potential method to detect delamination. The electrical potential method showed a poor performance of estimation when the delamination was located near the centre of the charged electrodes. This problem is overcome by introducing the non-symmetric charging concept to the electrical potential method, the validity of which is demonstrated by means of fi nite element method analyses. 7 refs.JAPAN

Accession no.972349

Item 222Composites Technologies for 2020. Proceedings of the Fourth Asian-Australasian Conference on Composite Materials (AACM-4), held Sydney, Australia, 6th-9th July 2004.Cambridge, Woodhead Publishing, 2004, p.882-887THERMOPLASTIC COMPOSITE ACCESS COVER MANUFACTURED BY CO-CONSOLIDATION AFTER THERMOFORMING STIFFERSKejian Wang; Xiao-Su YiBeijing,Institute of Aeronautical Materials(Asian-Australasian Association for Composite Materials)

Details are given of an integrated manufacturing process for the production of a thermoplastic composite aircraft access cover with L-shaped stiffeners of carbon fi bre reinforced PEEK. The fabrication process is described and involves the use of fl exible prepreg fabric, co-woven with carbon fi bre and PEEK. The stiffeners were produced either in direct press forming from a prepreg or by thermoforming of pre-consolidated blanks. The latter method was found to be more cost-effective and produced a higher quality of product. Both fusion welding and consolidation were used in the manufacture of the part, and the latter proved more cost-effective. The use of thermoforming and co-consolidation was shown to offer strong potential in the large volume production of three-dimensional composite structural parts for aerospace applications. 7 refs.CHINA

Accession no.972338

Item 223International Journal of Adhesion and Adhesives26, No.5, 2006, p.295-303SURFACE CLEANING TECHNOLOGIES FOR THE REMOVAL OF CROSSLINKED EPOXIDE RESINLitchfi eld R E; Critchlow G W; Wilson SLoughborough,University; Bombardier Aerospace; Short Bros.

This study provides details of the use of laser ablation and sodium hydride cleaning processes for the removal of crosslinked epoxide and other residues from resin



transfer moulding (RTM) tool substrates, as used in the aerospace industry. The requirement for removal of such contamination is so that the mould can be re-used, following the subsequent application of an external release agent. These tools are, typically, fabricated from steel, nickel or CFRP composite materials; this paper focuses on the use of nickel substrates. The requirement to clean large surface areas quickly to satisfy commercial restraints, compromises the degree of absolute cleanliness that can be obtained. However, in applications where cleaning time is not a constraint, laser cleaning can be a very gentle and effi cient process; typically Nd:YAG lasers fi nd application in this area. In contrast, high-power lasers are desirable for industrial scale applications where large areas need to be cleaned quickly. In this instance pulsed Co2 lasers can be used. The use of sodium hydride was also found to be highly successful in removing crosslinked organic contamination providing that suitable hard rinse and drying operations were also carried out. 14 refs. Copyright (c) 2006 Elsevier Ltd.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.971142

Item 224Kunststoffe International96, No.5, 2006, p.74/78LIGHTWEIGHT, VERSATILE ALL-ROUNDERBaumgartl HBASF AG

The development by BASF AG of elastic melamine resin foams, which are supplied to converters in slabstock form under the trade name Basotect, is described. The properties of the melamine resin foams are discussed, with particular reference to thermal conductivity, chemical resistance, thermal stability, fl ame resistance, and sound absorption. Applications of the foams, such as cleaning sponges, aircraft seat cushions and acoustic insulation components, are considered.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.970978

Item 225Nippon Gomu Kyokaishi79, No.1, Jan.2006, p.22-29JapaneseTHE ROLE OF POLYMERIC MATERIALS IN SPACE APPLICATION AND ITS DURABILITYYokota RJapan,Aerospace Exploration Agency

Developments in science and technology in the fi elds of high-performance polymers and composites thereof for space applications are reviewed. Areas covered include advanced composites for spacecraft primary structures, deployable structures, fl exible fi lms for space applications,

polymers environmentally stable in space, rubbers and adhesives, thermal protection for the space shuttle and heat resistant advanced composites for primary structures. 27 refs.JAPAN

Accession no.970859

Item 226Composites Technology12, No.3, June 2006, p.30-34THERMOFORMABLE COMPOSITE PANELS, PART IIGardiner G

Structural parts made from thermoformed glass-reinforced PPS panels have been put to notable use on the wing leading edges of both the A340 and new A380 commercial airliners. Predominantly supplied as a unidirectional prepreg, Plytron, a PP composite manufactured by Gurit, also is sold in sheets formed from multiple layers of continuous glass/PP with custom-tailored layup and fi bre orientation. Plytron has demonstrated its ability to offer Class A surface treatment in automotive applications. Twintex commingled PP and continuous glass fi bres has reportedly shown promise for thermoformable sandwich structures, featuring Twintex skins and either foam or PP honeycomb core. Textile coverings or carpets can be easily co-moulded during stamping for automotive interiors. Using a single-step manufacturing technology, FITS Technology produces lightweight, high-strength, high-stiffness FITS (Foamed In-situ Thermoformable Sandwich) panels, featuring an isotropic PEI foam core bonded to continuous fi bre-reinforced PEI faceskins. One of the initial targets for FITS is in overhead storage bins on commercial aircraft.EUROPE-GENERAL; USA

Accession no.970391

Item 227Journal of Reinforced Plastics and Composites 25, NO.8, 2006, P.847

MODELING YOUNG’S MODULUS OF POLYMER-LAYERED SILICATE NANOCOMPOSITES USING A MODIFIED HALPIN-TSAI MICROMECHANICAL MODELYung K C; Wang J; Yue T M Hong Kong,Polytechnic University

The applicat ion of the modified Halpin-Tsai micromechanical model to the calculation of Young’s modulus for nanocomposites of polymers with layered silicates as a function of clay concentration was studied for various parametric variations such as the exfoliation ratio, the particle/matrix stiffness ratio, particle volume fraction and particle aspect ratio. The predictions of the model are discussed in comparison with experimental data for nanocomposites of epoxy resin with montmorillonite clay. 35 refs.



CHINA

Accession no.968499

Item 228Polymer Degradation and Stability91, No.8, 2006, p.1861-1869MODELING OF OXIDATIVE DEVELOPMENT IN PMR-15 RESINTandon G P; Pochiraju K V; Schoeppner G ADayton,University; Stevens Institute of Technology

A multidisciplinary approach focused on models and processes to predict the performance and life expectancy of high-temperature polymer matrix composite (HTPMC) materials used in a variety of aerospace applications is being developed. Emphasis is on the implementation and extension of hierarchical models to represent the polymer behaviour/properties as a function of the degradation state. Neat resin specimens of high-temperature polyimide PMR-15 have been evaluated for various ageing conditions. Characterisation of the properties of the polyimide is focused on development of a constitutive law for use in a micromechanical analysis to predict the behaviour of PMR-15 reinforced composites. Thermo-oxidative ageing is simulated with a diffusion-reaction model in which temperature, oxygen concentration and weight loss effects are considered. One-dimensional simulations illustrate oxidative layer growth for neat resin specimens. Comparisons and correlations with experimental observations of oxidation layer growth are presented. 22 refs. Copyright (c) 2006 Elsevier Ltd.USA

Accession no.968374

Item 229Polimery51, No.2, 2006, p.104-14‘HYBRID’ SILICONES - AN OVERVIEW ON POLYSILALKYLENE OR POLYSILARYLENE SILOXANES FLUORINATED OR NOTGuida-Pietrasanta FMontpellier,Ecole Nationale Superieure de Chimie

An overview on polysilalkylene or polysilarylene siloxanes, fl uorinated or not, i.e. ‘hybrid’ silicones, is presented. The main synthetic routes to obtain these polymers are described, together with the properties of the different polymers. Two routes are presented in more detail, i.e. synthesis of alpha,omega-bis silanol monomers (prepared either via an organometallic route or via hydrosilylation of alpha,omega-dienes), followed by polycondensation of these bis silanols, and polyhydrosilylation of alpha,omega-dienes by alpha,omega-dihydrooligosiloxanes. This new class of polysiloxanes has been developed, mainly since the 1970s, to avoid the possible depolymerisation observed under certain conditions (acid or base, medium or high temperature) for classical polysiloxanes. The elastomers prepared by crosslinking of these inorganic-organic

hybrid polymers exhibit very high thermal stability and rather low temperature fl exibility and, depending on the nature of their backbones or of their side chains, they can be resistant to solvents or fuels. They can thus fi nd applications in advanced technological areas (aerospace, defence, computer applications). 67 refs. (Symposium on ‘Hybrid Polymer Systems of Industrial Importance’, Warsaw, Poland, Sept.2005)EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.968089

Item 230Polymer Engineering and Science46, No.5, 2006, p.581-7MODIFICATION OF BISPHENOL A DICYANATE ESTER BY CARBOXYL-TERMINATED LIQUID BUTADIENE-ACRYLONITRILE AND ITS COMPOSITESJieliang Wang; Guozheng Liang; Wen Zhao; Shenghua Lue; Hongxia YanShanxi,Northwestern Polytechnical University

Cyanate esters with excellent high-temperature properties and easy processing are well known as good resin materials used in aerospace and electrical industries, but the drawback of brittleness limits their usage. In this study, carboxyl-terminated liquid butadiene-acrylonitrile (CTBN) was introduced to improve the toughness of bisphenol A dicyanate resin (BADCy), a typical kind of the cyanate esters. Fourier transform infrared spectroscopy and differential scanning calorimetry were employed to investigate the effects of CTBN on the curing behaviour of BADCy; the results indicate that the addition of CTBN has a great infl uence on the curing behaviour of BADCy at lower temperatures, but little at higher temperatures. Data from the thermogravimetric analysis and heat defl ection temperature analysis showed that the thermal properties of the modifi ed systems were poorer than that of pristine BADCy resin. On the basis of the scanning electron micrographs of the modifi ed systems, toughening mechanism of the systems was discussed. Mechanical and dielectric properties of the cured resins and glass fi bre-reinforced composites were also studied. Modifi ed systems exhibit attractive properties for the future applications in aerospace industries. 15 refs. Copyright 2006 Society of Plastics EngineersCHINA

Accession no.967589

Item 231Extrusion12, No.2, 2006, p.22English; GermanFIRST THERMOSET FOAM SUITABLE FOR THERMOFORMING - MOVING THE BOUNDARIESBASF AG



BASF’s Basotect TG thermoset melamine resin-based foam which can be shaped under heat is briefl y described. It is shown that the impregnating step that used to be indispensable for thermoforming this material is now unnecessary, greatly simplifying its processing. The material can be directly compression-moulded under the usual processing conditions, so that making moulded parts is easier and more effi cient. Applications of Basotect TG in automotive and aircraft construction, e.g. for acoustic insulation, are discussed.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.967145

Item 232Engineering247, No.3, March 2006, p.8FIBRE PROVIDER

A brief report is presented on the use of a honeycomb composite made from DuPont Kevlar paper in the Airbus A350 for applications ranging from fl ooring, interior walls and cabin racks to wing fl aps, radomes and leading edges. The use of Kevlar as a replacement for traditional heavier solutions with Kevlar honeycomb is said to allow increased structural integrity while enabling significant weight savings of 30 to 50%. The use of Nomex fi re-resistant fi bre in the A350’s wallcoverings, structural parts, electric cable conduits, carpeting and seat liners is also mentioned.

DuPont; AirbusUSA; WESTERN EUROPE

Accession no.967115

Item 233Composites Science and Technology66, No.7-8, 2006, p.1010-21FATIGUE FRACTURE OF EMBEDDED COPPER CONDUCTORS IN MULTIFUNCTIONAL COMPOSITE STRUCTURESHyonny Kim; Myounggu Park; Hsieh KPurdue,University

The fatigue fracture of copper strips embedded in a glass fi bre-reinforced epoxy composite for aircraft applications was investigated by means of static and fatigue testing. Fractured specimens were analysed by X-ray imaging and ultrasonic testing and fracture surfaces and debonded surfaces analysed by scanning electron microscopy. Failure mechanisms were identifi ed and methods of improving the performance of the copper interconnects in the composites examined. 22 refs.USA

Accession no.966886

Item 234Composites Science and Technology66, No.7-8, 2006, p.983-92

DURABILITY OF CFRP LAMINATES UNDER THERMOMECHANICAL LOADING: A MICRO-MESO DAMAGE MODELLubineau G; Ladeveze P; Violeau DParis,University

A mathematical model for predicting the degradation of laminated composites for aerospace applications under cyclic loading conditions is proposed and applied to a study of the thermal fatigue of CRFP laminates. It takes into account oxidation effects and is a hybrid model based upon continuous damage mechanics and fi nite fracture mechanics. 31 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.966885

Item 235Macromolecular Symposia No.233, 2006, p.180POLYMER NANOCOMPOSITES: HOW TO REACH LOW FLAMMABILITY?Bourbigot S; Duquesne S; Jama C ENSCL

The flammability properties of nanocomposites of polymers such as ethylene-vinyl acetate copolymer, polystyrene and poly(ether-b-amide) block copolymer, with montmorillonite clay, organically modifi ed montmorillonite clay, polyhedral oligomeric silsesquioxanes and carbon nanotubes are reviewed in terms of heat release rate, UL-94 testing and limiting oxygen index. The characterisation of dispersion of nanoparticles by solid-state NMR and TEM, and the synergistic effects of combining nanoparticles with fl ame-retardants or plasma treatment are discussed. 54 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.966495

Item 236Kunststoffe International96, No.3, 2006, p.76-82THE BLACK GOLD OF LIGHTWEIGHT BUILDINGBittmann EWerkstoff&Struktur

The thriving market for CFRP in achieving lightweight constructions for the civilian aviation industry is discussed and the desire of the automotive industry to participate in this development is examined. There is shown to be a huge disparity between the desire of the automotive sector, which is affected by customer restraint, petrol prices and legislation, to take the potential of lightweight construction far beyond that of the current lightweight metal and GRP applications, on one hand, and the cost of using CFRP, on the other hand. Control of costs is considered. Resin injection liquid composite moulding processes are



described and progress towards a mass-produced CFRP car is considered. The use of CFRP for bridge reinforcement is also mentioned. 22 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.966215

Item 237Journal of Applied Polymer Science100, No.3, 5th May 2006, p.2210-9CHEMISTRY OF THERMAL AGEING IN AEROSPACE EPOXY COMPOSITESBondzic S; Hodgkin J; Krstina J; Mardel JCSIRO

Fourier transform infrared spectroscopy of selected model compounds was used to study the detailed chemical reactions involved in the thermal ageing at 120 deg.C of epoxy composites used in aerospace applications. The major reaction appears to be oxidation of the carbonyl group adjacent to a nitrogen atom in a tetraglycidyl diaminodiphenyl methane group. This appears to be particularly the case where this group is attached to an isomer of the diaminodiphenylsulphone hardener. Other ageing temperatures were considered and differences discussed. 19 refs.AUSTRALIA

Accession no.965868

Item 238Journal of Polymer Engineering26, No.2-4, Feb.-June 2006, p.213-26PROPERTIES AND MANUFACTURING OF SANDWICH PARTS WITH PHENOLIC FOAM CORESHaberstroh E; Schlumm MAachen,RWTH

The manufacture of sandwich structures comprising semi-syntactic phenolic resin foam cores, produced using low-density microspheres and a blowing agent, and fabric skins by a one-step sandwich moulding process in which a dry textile is impregnated with the foam system to give a sandwich laminate was investigated. The mechanical and fi re properties of the sandwich structures are discussed in terms of aerospace applications. 10 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.965680

Item 239Canadian Plastics64, No.2, Feb.2006, p.10SUPERCONDUCTIVE POLYMER TAKES PLASTICS TO NEW HEIGHTSReid R

A research team at Integral Technologies has developed a resin technology to manipulate the molecular structure of virtually any polymer allowing it to fully conduct electricity. When the technology, dubbed Electriplast, becomes commercially available and wire applications are developed from the technique, airplane manufacturers can replace relatively expensive and heavy copper wire with cheaper and lighter plastic wire. Integral has developed PlasTenna, a fl at panel antenna made from Electriplast. The formula developed creates a micron structure in the polymer where electrons can move freely without resistance. This is accomplished through a special concoction of additives and doping technique, which makes virtually any polymer electrically conductive. Electriplast can be moulded on conventional injection moulding machinery. Before Electriplast is available to plastic processors, Integral must fi nd a partner to compound high volumes of the material, about 100,000 lbs/day.

Integral Technologies Inc.USA

Accession no.965454

Item 240High-Performance Composites14, No.2, March 2006, p.44-9AUTOCLAVE QUALITY OUTSIDE THE AUTOCLAVE?Mason K F

Historically, most designers of structural composite components for aerospace applications have taken for granted the need for an autoclave cure. V System Composites is one of a growing number of processors that have begun to question the old assumptions. Using vacuum assisted-resin transfer moulding of aerospace composites, the company reports that 60% fi bre volumes have been achieved with unidirectional fabrics, compared to 62% with autoclaved prepreg. A VARTM’s part’s stiffness, proportional to fi bre volume, would therefore experience a knockdown of only 3-4% compared to autoclave structures. Benefi ts of out-of-autoclave processing include overall weight, part count, manufacturability, processing time, surface quality and cost. VARTM is one of three processing alternatives that proponents claim can achieve aerospace-grade results without resort to autoclave cure. The second alternative is resin transfer moulding, while the simplest and newest method is oven curing of prepregged parts, using prepregs recently developed for out-of-autoclave processing. Examples are presented which illustrate that early results for all three methods are more than promising.USA

Accession no.965393

Item 241Composites Technology12, No.2, April 2006, p.36-41



THERMOFORMABLE COMPOSITE PANELS, PART 1Gardiner G

The advent of thermoformable panels is driving huge growth in the use of reinforced thermoplastics, particularly in the automotive sector. Panel products have been developed from reinforced thermoplastic composites at both ends of the property and cost spectrum. One of the main applications of thermoformable panels in vehicle interiors is headliners, which have become increasingly complex. Typically quite thin at the edges to facilitate attachment and load transfer, headliners must be thicker elsewhere to offer increased heat impact protection and maximise noise abatement. Three different fi breglass-reinforced PP materials have been developed to help fabricators achieve variations in part thickness in a single forming cycle through a mechanical process called lofting. Vehicle door liners and door panels are being thermoformed using natural fi bre-reinforced thermoplastics. Self-reinforced composites are being marketed for underbody shields, bumpers, body panels, headliners, load fl oors and parcel shelves.WORLD

Accession no.965376

Item 242Materials Today9, No.3, March 2006, p.40-50ELECTROSPUN NANOFIBERS: SOLVING GLOBAL ISSUESSeeram Ramakrishna; Kazutoshi Fujihara; Wee-Eong Teo; Yong T; Zuwei Ma; Ramakrishna RamaseshanSingapore,National University

The use of electrospinning to produce highly porous nanofi bre meshes from different materials is described and a review is presented of the literature on applications of electrospun nanofibres in healthcare applications, biotechnology and environmental engineering applications, defence and security applications, and energy generation applications. Specifi c applications considered include micro engineered scaffolds for tissue engineering, wound dressings, membranes for water treatment, protective clothing and fi lters, polymer batteries, photovoltaic cells and polyelectrolyte membrane fuel cells. 64 refs.SINGAPORE

Accession no.965089

Item 243KGK:Kautschuk Gummi Kunststoffe59, No.1, Jan.-Feb.2006, p.45-8STUDY OF DAMPING BEHAVIOR OF RUBBER-PLASTIC BLENDPandey A K; Setua D KIndia,Defence Mat.& Stores R & D Est.

Blends of NR and HDPE in blend ratios of 30:70, 50:50

and 70:30 were prepared in a Brabender Plasticorder and their morphologies, viscoelastic properties and physicomechanical properties investigated by techniques, including scanning electron microscopy, DMTA and hardness, abrasion, flexural and impact testing. The effects of blend ratio and dynamic vulcanisation on blend properties were examined and the suitability of the blends, including thermoplastic vulcanisates, as vibration dampers in aerospace and defence applications considered. 29 refs.INDIA

Accession no.964782

Item 244International Polymer Science and Technology33, No.3, 2006, p.T/31-5INFLUENCE OF THE PHYSICOMECHANICAL CHARACTERISTICS OF HOLLOW GLASS MICROSPHERES ON THE PROPERTIES OF SPHERE-FILLED PLASTICSSokolov I I; Dolmatovskii M G; Deev I S; Stetsenko V YMoscow,Institute of Aircraft Materials; Stekloplastik Research and Production Organisation Co.

The effects of the physico-mechanical characteristics of various types of hollow glass microspheres on the properties of composites with epoxy resin binders were investigated by SEM, density and compression strength measurements. The results are discussed in terms of applications as strengthening fi llers for honeycomb panels used in the aviation industry 7 refs.RUSSIA

Accession no.964375

Item 245Composites Manufacturing (USA)22, No.1, Jan.2006, p.24/33AEROSPACE WILL CONTINUE TO LEAD ADVANCED COMPOSITES MARKET IN 2006Red CComposite Market Reports Inc.

A market overview for CFRP composites in 2006, particularly in aerospace and industrial applications, is presented. Statistics are included on estimated global carbon fi bre production and consumption, 1999 to 2009, on current North American market demand for carbon fi bres, by application, on military fi xed wing aircraft deliveries, commercial jet transport deliveries and business and general aviation aircraft deliveries for 2005 to 2008, and on growth in composites consumption for windmill blades for 2004 to 2008. It is shown that, despite challenging business environments, CFRP materials are poised to provide a strong source of revenue growth for both material suppliers and composites manufacturers during 2006.USA; WORLD

Accession no.963309



Item 246Shawbury, Rapra Technology Ltd., 2006, 21 papersProceedings of a conference held London, 25th-26th April 2006JOINING PLASTICS 2006: 2ND INTERNATIONAL CONFERENCE ON JOINING PLASTICS(Rapra Technology Ltd.)

Manufacturing with plastics often involves a bonding step from packaging, electronic and medical devices to large scale automotive, aerospace and construction projects. This is a continually developing fi eld and the experts at the Second International Conference on Joining Plastics discussed the best methods and options for different applications. Papers are divided into the following sessions: adhesives, adhesive testing, infrared welding, resistance welding and hot plate welding, composite joints, resistance welding, pretreatment, bonding fl uoroplastics, ultrasonic welding and vibration welding, heat tool welding, laser welding.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.962491

Item 247High-Performance Composites13, No.6, Nov.2005, p.22-7UPDATE ON COMPOSITE TANKS FOR CRYOGENSBlack S

Lightweight and strong composite materials are already deployed in many aerospace applications, such as launch vehicle bodies, but tankage for super-cold liquid fuels is still dominated by metals. Despite years of testing, concerns still exist about the potential for leaks, due to microcracking of traditional carbon/epoxy composite laminates at cryogenic temperatures. The focus of work at Lockheed Martin Space Systems has been on reusable, relatively low pressure, pump-fed or gravity-fed tanks of large dimensions for launch vehicles. Engineers have developed a new fi bre placement technique, termed in situ fi bre placement, which achieves full consolidation between plies using heat and compaction supplied by the fi bre placement machine head. Wilson Composites has developed composite tankage for Air Force space programmes. The company’s philosophy is that carbon/epoxy cryogenic tanks can function successfully without liners or even conventional metallic bosses and fi ttings.USA

Accession no.961578

Item 248Reinforced Plastics50, No.3, March 2006, p.22-4POPULARITY OF CARBON FIBREJacob A

Carbon fi bre supplier Toray Industries says that along with the recovery in aircraft demand, the aircraft industry is undergoing a rapid shift to composite materials. The company is currently expanding its carbon fibre and prepreg production capacity and establishing a global supply network. Outside of aerospace, Toray is also seeing increasing demand from large-scale industrial applications requiring carbon fi bre. These include pressure vessels, rotor blades for wind turbines and automotive projects progressing from test phases into mass production. The company believes that global demand for PAN-based carbon fi bres will grow at over 10% a year, from around 25,000 tons in 2005, reaching 34,000 tons in 2008. Carbon fi bre materials also offer the opportunity to enable new, lower cost, deepwater oilfi eld solutions.WORLD

Accession no.961510

Item 249Adhesion 05: Ninth International Conference on the Science and Technology of Adhesion and Adhesives. Proceedings of a Conference held Oxford, 7th-9th Sept.2005.London, IOM Communications, 2005, p.57-60ROOM TEMPERATURE CURING EPOXY ADHESIVES: SYNERGY BETWEEN ELASTOMERS AND NANOPARTICLESSprenger S; Eger C; Kinloch A J; Taylor A C; Lee J H; Mohammed R DHanse Chemie AG; London,Imperial College of Science,Technology & Medicine; Noveon Inc.(UK,Institute of Materials,Minerals & Mining)

The synergy between elastomeric toughening agents and silica nanoparticles in room temperature curing epoxy resin adhesives was studied. Aspects examined included the lap shear strength on untreated aluminium for different rubber concentrations, mode I fracture energy versus addition level of nano-silica and lap shear performance of thixotropic adhesives versus addition level of nano-silica. The results clearly demonstrated the potential of these room temperature curing epoxy resin adhesives not only for automotive applications, but also for bonding of composites and for aerospace applications. (The printed version is an extended abstract of the conference paper.) 8 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; UK; USA; WESTERN EUROPE

Accession no.961328

Item 250Polymers and Polymer Composites 14, No.1, 2006, p.13POLYAMIDE-6/CLAY NANOCOMPOSITES: A CRITICAL REVIEW Gupta B; Lacrampe M; Krawczak P Ecole des Mines de Douai



This review describes the current research situation with regard to polyamide-6/clay nanocomposites, with particular reference to preparation, processing and application issues. The preparation and processing of polyamide-6/clay nanocomposites is discussed with reference to intercalation and exfoliation, polymorphism, polymer/clay interactions, organo-modifi cation, compatibilisers, and thermal degradation. Properties and areas of end-use application are described for automotive parts, barrier layers in packaging, fl ame retardant materials, membranes and textiles. 79 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.958891

Item 251ANTEC 2005. Proceedings of the 63rd SPE Annual conference held Boston, Ma., 1st-5th May.

Brook� eld, Ct., SPE, 2005, pp.5LONG-TERM TENSILE AND COMPRESSIVE BEHAVIOR OF POLYMER FOAMSKraatz A; Moneke M; Kolupaev VDarmstadt,Technical University(SPE)

Polymeric rigid foams are increasingly used for highly loaded mechanical applications, e.g. as the core in foam sandwich constructions in aircraft or automotive parts. So far the mechanical behaviour of rigid foams has not been precisely determined. Therefore the core of sandwich constructions is not taken into consideration for the mechanical design. This leads to oversizing and extended material consumption. This paper presents experimental results of long-term tests and indicates a theory to take into account the difference of tensile and compressive behaviour of foams. This theory is based on a strength hypothesis and can be implemented in commercial fi nite-element programs. The proposed method leads to an improved mechanical design and as a consequence a reduction of mass of construction parts. 9 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.958138

Item 252Reinforced Plastics50, No.1, Jan.2006, p.44-8APPLICATIONS FOR PMI FOAMS IN AEROSPACE SANDWICH STRUCTURESSeibert HRohm GmbH

The his tory of aerospace appl icat ions us ing polymethacrylimide (PMI) foam started in 1971, when the material was successfully introduced as structural sandwich core for helicopter fuselage panels. Today, PMI foams are listed in more than 170 aerospace specifi cations worldwide. In the Delta 2 satellite launch vehicle, PMI

foam was used as a bi-functional core serving as a mandrel and as a structural member of the sandwich contributing to buckling resistance. The excellent resistance to compression creep of the PMI foam, plus its ability to fully support the prepreg during the cure results in a high dimensional stability plus a perfect consolidation of the prepreg. The manufacturing of high performance advanced helicopter rotor blades using Rohacell structural sandwich cores is state-of-the-art technology. By using the Rohacell foam-cored design, the service life of rotor blades was increased from approximately 400-500 fl ight hours for the initial metal blade, to more than 10,000 fl ight hours today.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.957876

Item 253Composites Technology11, No.6, Suppl., Dec.2005, p.8/49WORLD OF COMPOSITES: AN OVERVIEWThis article provides an overview of the properties of composites, fi bre reinforcement and

matrix materials available, part design criteria, fabrication methods and tooling. Markets include boat building, automotive, corrosion-resistant applications, construction, civil infrastructure, oil and gas, sports and recreation, aerospace, wind power and fuel cells. Fibre demand and supply is briefl y discussed.WORLD

Accession no.957856

Item 254Popular Plastics and Packaging51, No.1, Jan.2006, p.124-32POLYMER COMPOSITES: HIGH PERFORMANCE MATERIALSShertukde V V; Rane RMumbai,University Institute of Chemical Technology

Advanced composites consist of high strength reinforcing agents or fibres combined with high performance matrix resin. They differ from conventional FRPs in the requirements for superior performance under extreme mechanical, electrical or environmental conditions. Because of their light weight and superior properties, advanced polymeric composite materials are replacing metals in high structural applications such as in aircraft, spacecraft, satellites, missiles, sporting goods and joint replacements. Matrix resins, both thermoplastic and thermoset, are discussed, together with high performance fi bres and applications. 22 refs.INDIA

Accession no.957832



Item 255SAMPE Journal41, No.7, Nov.-Dec.2005, p.19-27THERMOPLASTICS IN AEROSPACE, NEW PRODUCTS THROUGH INNOVATIVE TECHNOLOGYOffringa AStork Fokker AESP BV

The use of thermoplastic composites in aerospace applications is discussed. Material development is described with reference to evolution of thermoplastic matrices and to thermoplastic composite material forms. Process technology and product applications are then considered, including low-cost processing, thermo-folding and press-forming, the advent of welding, co-consolidation, and current developments. An overview of the manufacturing technologies is given and future prospects are examined. 10 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; WESTERN EUROPE

Accession no.957585

Item 256Advanced Composite Materials14, No.4, 2005, p.365-83CFRP USING BRAIDED PREFORMS/RTM PROCESS FOR AIRCRAFT APPLICATIONSUozumi T; Kito A; Yamamoto TMurata Machinery Ltd.; Nippi Corp.

A novel preforming process which utilises a conventional tubular braiding technique and a deformation technique to manufacture near-net-shaped preforms is described and applied to the fabrication of preforms from carbon fi bre bundles. These preforms are resin transfer moulded into I-beam frames and panels using epoxy resin as the matrix polymer and the tensile properties of the frames and panels determined. A comparison is made of the frames and panels made from the composites with those fabricated from aluminium and the cost of the process is compared with that of a prepreg hand lay-up/autoclave method. 10 refs.JAPAN

Accession no.957525

Item 257SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 125, pp12NEW HIGH PERFORMANCE RTM SYSTEMTontisakis A; Blyakman Y; Chaudhari AHuntsman Advanced Materials(SAMPE)

Huntsman Advanced Materials’ Structural Composites group is a leading supplier of matrix systems for

advanced composites. It has been actively working in the development of high performance systems for resin transfer moulding (RTM) processes for aerospace and industrial composite applications. A new RTM system based on a novel benzoxazine/epoxy chemistry has been developed and is in the fi nal phase of commercial introduction to the market place. This new system is processable at 177 deg.C using traditional RTM techniques. The cured composite properties are superior to the traditional epoxy systems. The 177 deg.C cured composite has glass transition temperatures in excess of 200 deg.C with excellent thermal mechanical properties. The cured neat resin modulus is signifi cantly higher than the traditional epoxy systems, and modulus retention under hot wet conditions is particularly excellent. This is supported by the fact that benzoxazine chemistry has very low moisture absorption characteristics. The overall composite thermomechanical properties are excellent and comparable to the high performance prepreg resin systems. The system has superior thermo-oxidative stability. The chemistry, processing and performance of this system as well as the rationale behind the selection of different components and their effect on the overall system properties are described in detail. Details of neat resin and composite processing and processing kinetics are discussed. 2 refs.USA

Accession no.956980

Item 258SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 121, pp.15LOW OUTGAS SILICONE PRESSURE SENSITIVE ADHESIVE FOR AEROSPACE APPLICATIONSRiegler B; Meyer JNuSil Technology(SAMPE)

The need for a low outgas, thermally stable, high performance adhesive has initiated development of a new experimental silicone pressure sensitive adhesive (PSA) able to pass ASTM E-595, low outgassing requirements of 1% or less total mass loss (TML) and 0.1% or less collectable volatile condensable materials (CVCM). The performance goals are to maintain performance under load at temperatures above 175 deg.C and have similar properties to other low outgassed silicone PSAs as tested by peel, loop tack, shear, release force and Blunt probe tack. 8 refs.USA

Accession no.956976

Item 259SAMPE 2004. Materials and Processing Technology



- 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 120, pp.7DEVELOPMENT OF A NEW HIGH PERFORMANCE BMI STRUCTURAL ADHESIVE FILM FOR CO-CURE OVER HONEYCOMB CORE AND OTHER BONDING APPLICATIONSKohli D K; Trzaskos B; McDaniel T; Boyd JCytec Engineered Materials Inc.(SAMPE)

Development of a next generation BMI structural adhesive film for co-cure over core bonding applications is described. This adhesive fi lm is designed to co-cure with the Cycom 5250-4 BMI prepreg but prevent the fl ow of prepreg resin into the honeycomb cells. This allows the co-cured structure not to be resin starved and provides very low void content cured honeycomb structures. The new BMI adhesive fi lm provides a service temperature of 232 deg.C and is also suitable for bonding of metals and the secondary bonding of composite substrates. The development, processing and applications of this new structural adhesive fi lm for aerospace bonding applications are described. 2 refs.USA

Accession no.956975

Item 260SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 105, pp.6CARBON NANOFIBER FILLED CONDUCTIVE POLYIMIDESJacobsen R L; Walters K R; Matuszewski M; Glasgow D G; Wang C-SApplied Sciences Inc.; Dayton,University(SAMPE)

Low cost carbon nanofi bres have been used to formulate improved versions of conductive polyimide. Carbon nanofibres have superior properties, making them a candidate for this application, including very small diameter (to fi t within a thin fi lm), high aspect ratio (to form a network), moderate electrical conductivity and excellent dimensional stability (one of the properties for which polyimide is useful in aerospace applications.) Nanofi bres in the diameter range from 60-200 nm (as distinct from smaller nanotubes) are now available, relatively cheaply and in quantity. The primary challenge in making polyimide fi lms is achievement of adequate nanofi bre dispersion, complicated by nanofibre entanglement and surface wetting problems. Methods for surface modifi cation of nanofi bres, as well as size separation of nanofi bre agglomerates to promote adequate dispersion in polyimide, are described. Conductivity data on cast nanofi bre fi lled polyimide fi lms are presented. 2 refs.

USA

Accession no.956960

Item 261SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 96, pp.13DCPD - THE PROMISE FULFILLEDToner S A M; Leslie P; Frost J OCymetech LLC(SAMPE)

Three years ago, Cymetech began developing poly-DCPD formulations based on a new family of ruthenium catalysts. As these formulations evolved, it became clear that they would meet or exceed the physical properties of the fi rst generation materials and would offer the benefi ts of reduced sensitivity to impurities and significantly less odour evolution. In 2003, Cymetech introduced four Prometa formulations for the resin transfer (RTM) and rotational moulding industry. Ruthenium based formulations were also demonstrated in VARTM and RIM applications. Each of these formulations targets specifi c applications, and has been demonstrated in commercial parts. These include parts for the corrosion industry, parts for agri-business, tanks for aerospace and industrial components for a variety of applications. Parts made with Prometa resins offer superior toughness, impact resistance, heat distortion temperature and chemical resistance over other materials of construction. Because Prometa resins can be processed using low cost tooling, production runs ranging from ten to two thousand are economical.USA

Accession no.956951

Item 262Plastics Additives and Compounding7, No.6, Nov.-Dec.2005, p.17MODIFIERS OFFER LOW TEMPERATURE PERFORMANCE

The Ultra Low Temperature (-60C) 1500 series of Abust and Mebust impact modifi ers from PolyChemAlloy are finding increasing success in automotive, aerospace, marine and cable applications, it is briefl y reported. The company says that these virgin pelletised impact modifi ers, with a butadiene content in excess of 50%, have no melting point and can be easily mixed with a wide variety of high temperature engineering resins. They have less than 0.05% moisture and are free fl owing. The company adds that the low Tg core enables Mebust and Abust to be used in low temperature applications to create products that will withstand -50C and remain ductile.

PolyChem Alloy Inc.USA

Accession no.956907



Item 263International Polymer Science and Technology32, No.9, 2005, p. T/53-4FIREPROOF INJECTION-MOULDING THERMOPLASTICSPetrova G N; Abakumova N M; Rumyantseva T V; Beider E Y; Sytyi Y V; Perfi lova D N; Volkova T SAll-Russia Scientifi c Research Institute of Aviation Materials

The use of flame retardant injection mouldable thermoplastics in aircraft structures is examined with respect to both structural and decorative applications. This paper examines thermoplastic materials that satisfy fire resistance requirements AP-25, and which are recommended for the production of parts by injection moulding. Properties of grades of polysulphone, polycarbonate, and PBTP composites are discussed, which are recommended for such application. (Article translated from Plasticheskie Massy, No.1, 2005, p.45-6)RUSSIA

Accession no.955497

Item 264Composites Science and Technology65, No.15-16, 2005, p.2575-87DEVELOPMENT OF SMART COMPOSITE STRUCTURES WITH SMALL-DIAMETER FIBER BRAGG GRATING SENSORS FOR DAMAGE DETECTION: QUANTITATIVE EVALUATION OF DELAMINATION LENGTH IN CFRP LAMINATES USING LAMB WAVE SENSINGTakeda N; Okabe Y; Kuwahara J; kojima S; Ogisu TTokyo,University; Hitachi Cable Ltd.; Fuji Heavy Industries Ltd.

The development of small diameter polyimide-coated optical fibre and its fibre Bragg grating sensor for embedding inside composite laminates for damage monitoring in composite structures is described. A damage detection system for quantitative evaluation of delamination length in carbon fi bre-reinforced epoxy resin cross-ply laminates using Lamb wave sensing is discussed in terms of aerospace applications. 38 refs.JAPAN

Accession no.953856

Item 265Journal of Composite Materials39, No.20, 2005, p.1819-42ENERGY RELEASE RATE PREDICTION IN STIFFENED-SKIN STRUCTURE USING A THREE-DIMENSIONAL CRACK TIP ELEMENT ANALYSISDavidson B D; Yu LSyracuse,University

The use of three-dimensional crack tip element and

three-dimensional finite element analyses to predict energy release rates for a stiffened skin structure with aerospace applications, loaded in bending and containing a delamination between its skin and a hat-shaped stiffener are compared. The results for an isotropic confi guration and a variety of graphite fi bre-reinforced epoxy resin lay-ups are considered, and the effects of lay-up on energy release rate distributions are discussed. 17 refs.USA

Accession no.953765

Item 266Journal of Materials Science40, No.14, July 2005, p.3615-23PROCESSING AND HYGROTHERMAL EFFECTS ON VISCOELASTIC BEHAVIOR OF GLASS FIBER/EPOXY COMPOSITESBotelho E C; Costa M L; Pardini L C; Rezende M CBrazil,Instituto de Aeronautica e Espaco; Sao Paulo,University

The effects of curing and prolonged hygrothermal conditioning on the dynamic mechanical properties of glass fi bre-reinforced epoxy resins with aerospace applications were investigated by DSC and vibration damping measurements. The results are discussed in terms of matrix plasticisation by moisture absorption leading to lower stiffness under damping tests. 32 refs.BRAZIL

Accession no.952891

Item 267Materials Research8, No.3, July-Sept.2005, p.317-22CHARACTERIZATION OF CURE OF CARBON/EPOXY PREPREG USED IN AEROSPACE FIELDCosat M L; Botelho E C; de Paiva J M F; Rezende M CSao Paolo,Centro Tecnico Aeroespacial; UNESP; Sao Paulo,Centro Universitario Salesiano

The cure kinetics and rheological properties of a thermoplastic-toughened carbon fi bre fabric-reinforced epoxy resin used in aerospace applications were investigated using DSC, DMA and rheometry. The results are discussed in terms of optimisation of the cure cycle to produce composites suitable for structural components. 20 refs.BRAZIL

Accession no.952847

Item 268ANTEC 2005. Proceedings of the 63rd SPE Annual conference held Boston, Ma., 1st-5th May.Brookfi eld, Ct., SPE, 2005, pp.4EXTRUSION RHEOLOGY OF GLASS-FIBER-FILLED POLYPROPYLENE MELTSRao N S; Subramanian N; Nanguneri S R; Schumacher



GPlastics Solutions International; Indian Institute of Technology; Transfer Mathematics Technology(SPE)

The advantages of glass-reinforced plastics in various branches of industry, such as the automotive and aircraft industries, and also in the manufacturing of furniture and sports goods are well-known. In all these applications, knowledge of the melt fl ow of the composite material is required, in order to design machinery for processing the fi lled polymer. This paper is a contribution to the quantitative description of the rheology of glass-fi bre-fi lled polypropylene melts. The effect of shear rate, melt temperature and fi bre concentration on the melt viscosity was studied by means of a high-pressure capillary rheometer. An equation was derived to correlate the melt viscosity with the fi bre content, using a modifi ed shift factor taking the melt temperature and the fi bre content into account. The proposed modelling could be applied to any fi lled thermoplastic melt. 3 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; INDIA; USA; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.952482

Item 269Journal of Materials Science40, No.17, Sept.2005, p.4541-8ANALYSIS OF PEEL ARM CURVATURE FOR THE DETERMINATION OF FRACTURE TOUGHNESS IN METAL-POLYMER LAMINATESKawashita L F; Moore D R; Williams J GLondon,Imperial College of Science,Technology & Medicine

Metal-polymer laminates consisting of various aluminium alloys as the substrate and various polymers as the adhesive were subjected to variable angle fixed arm peel and mandrel peel tests. Adhesives employed were a rubber-toughened epoxy adhesive for general engineering applications, a toughened epoxy system for aerospace applications, PP and a rubber-toughened epoxy adhesive for automotive applications. Plastic bending energy (Gp) and adhesive fracture toughness (Ga) were determined from the mandrel peel tests and a global energy-balance analysis was employed to predict Ga and Gp in the case of the fi xed arm tests. The maximum curvature of the peel arm and the root rotation angle were calculated using a beam on elastic foundation model and high resolution digital photography was utilised to establish the accuracy of the analytical approach employed.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.952252

Item 270Polimeros: Ciencia e Tecnologia15, No.3, July-Sept.2005, p.224-31

PortugueseESTABLISHMENT OF CURE CYCLE OF AERONAUTIC PREPREGSCosta M L; Rezende M C; Botelho E C

The cure kinetics and rheological properties of various prepreg epoxy systems were investigated using techniques, including differential scanning calorimetry, and mathematical modelling, with the aim of establishing a cure cycle for producing high-performance autoclave moulded composites for aerospace applications. 27 refs.BRAZIL

Accession no.952246

Item 271Reinforced Plastics49, No.10, Nov.2005, p.18ADHESIVE FOR AIRCRAFT INTERIORS

It is briefl y reported that 3M has launched what is claimed to be the fi rst adhesive fi lm for aerospace sandwich panels that fulfi ls stand alone fi re, smoke and toxicity (FST) regulations. AF3070 FST can be used to fi nish edges, splice cores and fi ll gaps in honeycomb sandwich panels. The fi lm is co-cured with the panels to deliver a high quality edge fi nish, helping to ensure compliance with FST requirements. AF3070 FST is a double-sided, foaming fi lm with an advanced epoxy adhesive. Typical applications include overhead luggage compartments, partition walls and fi xed wall, ceiling and fl oor panels.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.951611

Item 272Materials and Manufacturing Processes20, No.5, 2005, p.739-46STRUCTURAL INTEGRITY OF CO-CURED COMPOSITE PANELSHuang C K; Hsu C YLunghwa,University of Science & Technology

The structural strength of co-cured joints in skin and J-shaped stiffeners in carbon fibre-reinforced epoxy resin composite panels used in aerospace applications was investigated by compression testing. The results are compared with predicted values and the effects of web length and thickness on compressive strength of J-stiffened panels are discussed in terms of failure mechanisms. 8 refs.TAIWAN

Accession no.950947

Item 273High-Performance Composites



13, No.5, Sept.2005, p.30-6FROM SPECIALTY FILLERS TO SPACE ELEVATORSPottish N

Considerable research, in progress in university, government and private laboratories, promises not only a better understanding of existing nanomaterials, but new materials as well, together with more efficient, cost-effective processing techniques and methods for using their unique properties in practical applications. Tier 1 nanocomposites can be viewed as an evolution of fi lled polymer technology. In this category, nanoclays are expanding into aerospace applications. Upcoming applications include sacrifi cial ablative materials for rocket motor casings. Recent work by the Air Force Research Laboratory and others has involved using carbon nanotubes in shape memory polymers to make actuators. Three years ago, Metal Matrix Composites began to make and explore Tier 2 opportunities for metal nanofi laments. Currently, the company is exploring the use of nickel nanofi laments to create conductive paths in polymers such as adhesives, coatings and elastomers. Lightning-strike materials probably will be one of the earliest applications that will emerge. Tier 3 nanocomposites are still very much in the basic research realm right now. These could be defi ned as “true” nanocomposites, designed and built with precise control of the nanoscale distribution and orientation of the nanoparticles in the matrix.USA

Accession no.950743

Item 274Popular Plastics and Packaging50, No.9, Sept.2005, p.84-7FIRE RESISTANT POLYMERSKumar V; Singh M; Singh ASant Longowal,Institute of Engineering & Technology

Heat or fl ame resistance of polymers is of vital importance in applications such as aerospace, electrical, automotive, domestic and construction. Heat resistance of polymers can be enhanced by incorporating/adding crosslinking, crystallinity, antioxidants, stiffness, synthesizing ladder polymers and by eliminating weak thermooxidative links. Performance of these polymers can be judged numerically by carrying out Limiting Oxygen Index tests. 6 refs.INDIA

Accession no.950599

Item 275Journal of Testing and Evaluation33, No.5, Sept.2005, p.340-7LOW PROOF LOAD PREDICTION OF ULTIMATE LOADS OF FIBERGLASS/EPOXY RESIN I-BEAMS USING ACOUSTIC EMISSIONFatzinger E C; Hill E KVector Scientifi c Inc.; Florida,Embry-Riddle

Aeronautical University

The development of a procedure for the proof testing of composite glass fi bre-reinforced epoxy resin laminated I-beam sandwich structures with polyurethane foam cores as used in aerospace applications by ultimate load prediction based on acoustic emission testing together with statistical analysis is described. The results obtained using a Kohonen self-organising map coupled with multiple linear regression are discussed in comparison with those obtained using a back-propagation network. 8 refs.USA

Accession no.948909

Item 276Rubber India57, No.7, July 2005, p.15-8NANOCOMPOSITE TECHNOLOGYMajumdar S

Nanocomposites can be polymers of thermoplastics, thermosets or elastomers. These materials provide improvements over other known composites in thermal, mechanical, electrical and air barrier properties. The excellent air retention properties of butyl/halobutyl is well known in the tyre industry and this rubber is extensively used in inner tubes and in inner liners in tubeless tyres. Using butyl and clay as fi ller with high aspect ratio, the air retention properties could be improved to the level of 50 times better than that of normal butyl compound. Other applications including automotive fuel systems, biomedical and aerospace are outlined. 6 refs.INDIA

Accession no.948789

Item 277Polymer 46, No.15, 2005, p.5588SYNTHESIS AND CHARACTERIZATION OF MALEIMIDE AND NORBORNENE FUNCTIONALIZED BENZOXAZINESIshida H; Ohba S Case Western Reserve University

Synthesis of a two types of monofunctional benzoxazines with maleimide or norbornene functionalities, and capable of polymerisation by different free radical mechanisms than conventional benzoxazines, is described. The resulting benzoxazine polymers have improved thermal properties including higher char yields and glass transition temperatures in excess of 250 deg.C. Characterisation of benzoxazine, polymerisation mechanism, and resulting polymers was carried out using Fourier transform infrared and nuclear magnetic resonance spectroscopies, thermogravimetric analysis, differential scanning calorimetry, and viscosity measurements. It was observed that monomer viscosity was not signifi cantly affected by maleimide or norbornene functionalisation, and glass



transition temperatures were affected by the free radical initiator used for polymerisation. 37 refs.USA

Accession no.946902

Item 278Plastics Technology51, No.5, May 2005, p.78/83THERMOFORMING PPSGehrig M J; Kelly S; Carr MEnsinger-Penn Fibre; Magee Plastics; Ticona

The process of thermoforming has advanced as applications have become increasingly challenging and demanding, and thermoformers are now seeking out higher performance resins - a search which has lead them to polyphenylene sulphide (PPS). This article looks at the opportunities which this resin offers, for example in aerospace, chemical, electronics, food, and transportation applications.US,FOOD & DRUG ADMINISTRATION; UNDERWRITERS LABORATORIES INC.

USA

Accession no.946225

Item 279Eureka25, No.7, July 2005, p.35FLEXIBLE POLYMER MAKES THINNER CABLESShelley T

By adding elastomeric properties to polyphenylene oxide (PPO) to make it fl exible for wire and cable covering applications, it is possible to reduce the weight of standard automotive wiring by a quarter, and greatly reduce he space it occupies. GE Advanced Materials has now launched “Flexible Noryl” PPO, which should be of exceptional interest to automotive and aerospace electrical engineers alike.GE ADVANCED MATERIALS

EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.946212

Item 280Journal of Advanced Materials37, No.1, Jan.2005, p.61-6DYNAMIC LOCAL MECHANICAL AND THERMAL STRENGTH PREDICTION USING NDE FOR MATERIAL PARAMETERS EVALUATION OF AEROSPACE COMPONENTSGolfman Y

A report presented on prediction of the dynamic strength of composites for aerospace applications using ultrasound, X-ray, digital radiography and thermography as non-destructive testing techniques. A nose cap fabricated from orthotropic carbon-carbon or graphite epoxy is used as

an example of an aerospace application. Calculations are made of thermal stresses using parameters established by ultrasound and thermography techniques and temperature gradients fl uctuating from -8 to 16C predicted using an approximate solution. Statistical models are used to predict the probability of local cracking. s presented on the prediction of the dynamic strength of composites for aerospace applications using ultrasound, X-ray, digital radiography and thermography as non-destructive testing techniques. A nose cap fabricated from orthotropic carbon-carbon or graphite epoxy is used as an example of an aerospace application. Calculations are made of thermal stresses using parameters established by ultrasound and thermography techniques and temperature gradients fl uctuating from -8 to 16C predicted using an approximate solution. Statistical models are used to predict the probability of local cracking. 12 refs.USA

Accession no.946032

Item 281SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 73 pp.8PULTRUSION RESIN TRANSFER MOLDING OF ADVANCED AEROSPACE MOLDING OF ADVANCED AEROSPACE STRUCTURESHillermerer R W; Friedrich L; Ng DHexcel Corp.(SAMPE)

The pultrusion resin transfer moulding (PRTM) process has been developed for the fabrication of high performance structural composite profi les, particularly for aerospace applications. In PRTM, high performance textiles are continuously shaped, impregnated and cured using a specifi cally developed apparatus combining the positive aspects of RTM and pultrusion. The resulting constant cross-section profiles exhibit excellent dimensional and structural qualities. The inherent disadvantage of conventional RTM materials, specifi cally with respect to their lower compression strength compared to prepreg tape based composites, is overcome by developing specifi c matrix and textile materials for this process. Various material combinations are analysed and compared to aerospace grade composite materials. Mechanical testing of notched properties as well as of compression after impact properties shows that PRTM materials reach the same level as currently qualifi ed aerospace RTM and prepreg materials. These exciting results are encouraging Hexcel to now fully explore the possibilities of this interesting technology.USA

Accession no.945700



Item 282SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 52, pp.13RECENT DEVELOPMENTS IN LIQUID MOLDING MATERIALS AND PROCESSES FOR DAMAGE TOLERANT APPLICATIONSPederson C; Thai B; Lo Faro C; Aldridge M; Maskell RCytec Engineered Materials Inc.; Cytec Engineered Materials Ltd.(SAMPE)

There has been much interest recently concerning liquid moulding as an alternative process for the fabrication of high performance composite structures. The resin impregnation of dry fi bre preforms can be accomplished by a variety of methods, including resin transfer moulding, vacuum assisted resin transfer moulding, etc. The majority of these liquid moulding processes require resin systems characterised by their low viscosities for extended periods of time. The VARTM process offers signifi cant manufacturing advantages but the method requires resin systems displaying low viscosities at ambient temperatures. However, recent advances relating to in-situ toughening technology (hybrid fabrics with epoxy soluble thermoplastic fi bres) potentially offer a route to primary structural applications using room temperature injectable resin systems. A novel approach to toughened composites via the use of a room temperature injectable system is described. State-of-the-art preform assembly methods are also demonstrated. 2 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; USA; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.945679

Item 283SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 42, pp.15DURABLE ANTI-EROSION COATINGS FOR POLYMER MATRIX COMPOSITES IN AEROSPACE APPLICATIONSNaik S K; Sutter J K; Siefker R G; Bowman C L; Miyoshi K; Cupp R; Tabakoff W; Haller H SRolls-Royce Ltd.; US,NASA,Glenn Research Center; AADC; Cincinnati,University; Haller H.S.,& Co.(SAMPE)

Polymer matrix composites (PMCs) are attractive for use in propulsion engine components due to their high specifi c strength. The use of composites could be even more advantageous if the sand erosion life of the component were extended, thereby reducing maintenance costs. NASA Glenn Research Center (NASA GRC) and Rolls-Royce have developed erosion resistant coatings that can

extend PMC component life and are applicable to current available and advanced high temperature PMCs. The performance of SANPRES and SANRES, two similar erosion resistant coating systems subjected to engine test conditions on Rolls-Royce AE 3007 engine bypass vanes, are discussed. The results of the high temperature erosion and vane cascade erosion rig tests, coated component shaker (vibratory) table tests to pre-condition vanes to simulate an accelerated fraction of vane life prior to engine tests, and the ability of the preconditioned coated vanes to withstand the thermomechanical strains after more than 1050 hours of testing on a Rolls-Royce AE 3007 engine are reviewed. 10 refs.USA

Accession no.945669

Item 284SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 39, pp.8FABRICATION OF ELECTRON-BEAM PROCESSABLE POLYIMIDE TAPES AND COMPOSITESHoyt Haight A E; Gosau J-M; Wesson S P; Babow D AAdherent Technologies Inc.(SAMPE)

Electron beam (e-beam) curing of polymer matrix composites (PMCs) is highly desirable from a manufacturing standpoint in that signifi cant cost savings may be realised from the reduced cycle times, the ability to cure large and irregularly shaped parts, and the ability to use inexpensive tooling. However, for many applications in the aerospace and transportation industries, e-beam processable resins currently available do not meet the performance specifications (e.g. excellent thermal stability, high strength and high toughness). Adherent Technologies has recently been developing a graft polyimide-siloxane system incorporating functionalities amenable to crosslinking under electron beam irradiation. The incorporation of these materials into carbon fi bre tapes and the fabrication of e-beam cured composite plates from these tapes are discussed. 4 refs.USA

Accession no.945666

Item 285SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 38, pp.11ELECTRON BEAM CURED RESINS AND COMPOSITES: IMPROVED TWO-STEP CURING MATERIALS FOR CRYOGENIC APPLICATIONS



Bykanova L G; Byrne C A; Palmese G RScience Research Laboratory Inc.; Drexel,University(SAMPE)

There are two major families of resins that cure with electron beams, the cationic epoxies and the vinyl compounds. The vinyl resins, such as acrylates, can be cured in the presence of nucleophilic compounds present in the formulation or on the fi bres, while the cationic epoxies cannot cure under these conditions. SRL and partner Drexel University are continuing to develop and improve two-step cured resins that utilise low temperature epoxy curing combined with electron beam curing to form thermoset networks for carbon fi bre composites. The aim is to toughen these resins, extend the use temperature range and evaluate their properties at temperatures extending from that of liquid hydrogen to at least 120 deg.C. Results of thermal and mechanical testing of both cured resins and continuous fi bre composites prepared from the same resins are discussed. 4 refs.USA

Accession no.945665

Item 286SAMPE 2004. Materials and Processing Technology - 60 years of SAMPE Progress. Proceedings of a conference held Long Beach, Ca., 16th-20th May 2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 36, pp.13VIBRATION DAMPINGOF FLEXIBLE AND RIGID POLYURETHANE COMPOSITESSharma A; Peel L DTexas A & M University(SAMPE)

It is desirable to obtain materials that have high vibration damping while maintaining other structural properties. Aerospace quality composite materials typically have greater strength and stiffness to weight ratios than most metals, while providing increased damping. However, their passive damping capacities are not enough for some applications. Fibre reinforced elastomers (FRE) or elastomer composites are receiving attention because of the ability to tailor their vibration damping, strength, fracture toughness and elongation to the range needed. A series of aluminium panels laminated with ‘skins’ of graphite cloth, glass fi bre cloth and chopped glass fi bre mat is considered. The reinforcements are impregnated with a series of PU elastomers ranging from fl exible to rigid in hardness. For a given type of glass fi bre, the lower durometer elastomer produces the highest loss factor. For a given elastomer stiffness, the stiffest reinforcement produces the highest damping. In general the skin loss factors are inversely proportional to the equivalent axial in-plane stiffness of the composite. Skin loss factors range from 1.5% to approximately 20%. The study provides valuable experimental data useful in developing fl exible or rigid lightweight and cost-effective materials that

provide good damping while contributing strength and stiffness. 9 refs.USA

Accession no.945663

Item 287Journal of Adhesion81, No.6, June 2005, p.561-86COMPARISON OF PEEL TESTS FOR METAL-POLYMER LAMINATES FOR AEROSPACE APPLICATIONSKawashita L F; Moore D R; Williams J GLondon,Imperial College Of Science,Technology & Medicine

Several peel tests, namely fl oating roller, climbing-drum, T-peel, fi xed-arm peel and mandrel peel, were performed on two aerospace toughened epoxy-aluminium alloy laminates. The outputs from the tests were unifi ed in terms of adhesive fracture toughness using a theory of peeling, which accommodates all the above tests, and the methods compared. 12 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.945142

Item 288Advanced Composite Materials14, No.2, 2005, p.211-28IMPACT DAMAGE AND CAI STRENGTH OF MR50K/PET15 CARBON/TOUGH-POLYIMIDE COMPOSITE AT ROOM AND HIGH TEMPERATURESKatoh H; Shimokawa T; Ueda A; Kobayashi D; Hamaguchi YJapan,Aerospace Exploration Agency; Tokyo,Metropolitan Institute of Technology; Toyota Motor Corp.; Komatsu Forklift Co.Ltd.

The impact damage and compression-after-impact properties and strength of a carbon fibre-reinforced polyimide resin composite laminate material developed for aerospace applications were investigated by impact testing and optical microscopy. The results are discussed in comparison with data previously obtained for an alternative carbon fi bre-reinforced polyimide material. 9 refs.JAPAN

Accession no.944662

Item 289Advanced Composite Materials14, No.2, 2005, p.199-210MODELING AND VIBRATION ANALYSIS OF A COMPOSITE SUPPORTER FOR AEROSPACE APPLICATIONSZhang S; Chen HXian Jiaotong,University



Modelling and vibration analysis of a composite supporter with a sandwich structure developed for aerospace applications and manufactured by hand lay-up using a combination of carbon fi bre-reinforced epoxy resin laminate face sheets and Nomex honeycombs is presented. The results of fi nite element modelling are discussed in comparison with experimental data. 12 refs.CHINA

Accession no.944661

Item 290High Performance Plastics 2005. Proceedings of a conference held Vienna, Austria, 5th-6th April 2005.Shawbury, Rapra Technology Ltd., 2005, Paper 12, pp.4AN OVERVIEW OF THERMOPLASTIC STRUCTURAL COMPOSITES FOR AEROSPACE APPLICATIONSConnell J WUS,National Aeronautics & Space Administration(Rapra Technology Ltd.)

A brief report is presented on past and present studies of the use of thermoplastic matrix structural composites for aerospace applications. Airbus’s recent announcement of its selection of thermoplastic composites using polyphenylene sulphide as the matrix for structural applications on the A380 is discussed. Opportunities for other thermoplastic matrix resins such as PEEK and polyetherimide are considered. Tabulated information is presented on traditional trade-offs of thermosets versus thermoplastics and on representative thermoplastic/thermoset composite mechanical properties. 4 refs.

AirbusUSA

Accession no.944204

Item 291High Performance Plastics 2005. Proceedings of a conference held Vienna, Austria, 5th-6th April 2005.Shawbury, Rapra Technology Ltd., 2005, Paper 2, pp.10TECAMAX SRP - COMMERCIALLY AVAILABLE RIGID ROD POLYMER SHAPESMalkovich N; DiSano L PMississippi Polymer Technologies; Ensinger Industries Inc.(Rapra Technology Ltd.)

Ensinger’s TECAMAX SRP (self-reinforced polymer) system, which is based on polyphenylene chemistry and is processable into stock shapes via compression moulding and extrusion, is described. Shapes made from this polymer system by Mississippi Polymer Technologies under the tradename Parmax SRP are shown to have very high strength and modulus with a specifi c gravity of only 1.21 g/cc. The mechanical properties are shown to be superior to those of other reinforced high performance thermoplastics and to be inherently isotropic. The rigid rod polymer is amorphous and highly dimensionally-stable. Unlike

amorphous plastics, Parmax SRP has good chemical resistance, thermal and thermooxidative stability. The high abrasion resistance, toughness and fl ame resistance are shown to make TEXAMAX SRP shapes suitable for demanding applications such as in the aerospace/defence, medical and semiconductor markets. 9 refs.USA

Accession no.944195

Item 292Popular Plastics and Packaging50, No.6, June 2005, p.77-80LIQUID CRYSTALLINE POLYMERS AND THEIR APPLICATIONS (PART I)Patil V V; Mahanwar P AMumbai,University

The three types of liquid crystal phases, nematic, cholesteric and smectic, are described. Liquid crystalline polymers are classifi ed on their synthesis routes and their molecular attachments. LCPs can also be broadly classifi ed based on their thermodynamic behaviour as lyotropic or thermotropic. Main-chain LCPs are formed when the mesogens are in the main chain of the polymer. The high melting points and the high crystallinity of MC-LCPs, together with the readily synthetic accessibility of these polymer types, open up a wide range of possible applications as new materials with excellent properties. Of the lyotropic MC-LCPs, the most notable are the polyamides, of which Kevlar is the best-known example. The properties of LCPs are discussed.INDIA

Accession no.943725

Item 293Polyurethanes Expo 2004. Proceedings of a conference held Las Vegas, Nevada, 18th-20th Oct.2004.Arlington, VA., Alliance for the Polyurethanes Industry, 2004, p.509-12HEAT RESISTANT FLEXIBLE FOAMIwa T; Shibata T; Ohkubo KMitsui Takeda Chemicals Inc.(American Plastics Council; Alliance for the Polyurethanes Industry)

A flexible foam with excellent heat resistance and mouldability is described. This foam is obtained by reacting a polyisocyanate compound with a polyester polycarboxylic acid in the presence of a catalyst. It is well known that an amide linkage is obtained by reacting an isocyanate with a carboxylic acid, and that carbon dioxide is generated in this reaction. Also, it is well known that polyamide has excellent heat resistance compared to PU. Therefore it is of interest that a polyamide foam can be obtained by reacting a polyisocyanate with a polycarboxylic acid. However, previously reported polyamide foams were inferior in mouldability and other desirable properties of fl exible foams, so polyamide foam has been used only



as a rigid foam. Also, using polyamide foams presents other practical diffi culties. A fl exible foam is obtained with excellent heat resistance. Its mouldability, fl exibility and sound absorption are equal to PU fl exible foam. This foam is suitable for high temperature applications where the use of PU fl exible foam is problematic. Therefore, this foam can be used for damping foam, sound absorbing material or cushioning material to surround the engine or exhaust pipe of a car. In general, it can be used widely in applications where heat resistance is required, such as in aircraft and ships. 2 refs.JAPAN

Accession no.940331

Item 294Plastics Engineering61, No.3, March 2005, p.10-1SHAPE MEMORY POLYMERS RESHAPE PRODUCT DESIGNToensmeier P A

Shape memory polymers are the subject of this article. What a shape memory polymer is, how it works, how it can be used as a manufacturing aid, what is going on at a molecular level, and thermoset and thermoplastic examples are all discussed in detail. The article then looks at possible applications, including clothing, biodegradable sutures, composite tooling, and aerospace possibilities.US,DEPT.OF DEFENSE; LORD CORP.; MITSUBISHI HEAVY INDUSTRIES LTD.; COMPOSITE TECHNOLOGY DEVELOPMENT INC.; CRG INDUSTRIES LLC; BAYER MATERIALSCIENCE; MNEMOSCIENCE GMBH; MASSACHUSETTS,INSTITUTE OF TECHNOLOGY

EU; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; JAPAN; USA; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.939784

Item 295Structural Adhesives in Engineering VII. Proceedings of a conference held Bristol, 13th-15th July 2004.London, IOM Communications Ltd., 2004, Paper 38, pp.4THE USE OF PEEL TESTS IN THE SELECTION AND ASSESSMENT OF METAL-POLYMER LAMINATES FOR AEROSPACE ACE APPLICATIONSKawashita L F; Moore D R; Williams J G(IOM Communications Ltd.; UK,Society for Adhesion and Adhesives)

Laminates made of aluminium alloys and epoxy compounds are commonly used in aerospace applications. The strength of the bond is a critical issue as the laminates act as engineering structures. Consequently, the strength of the bond is measured as a requirement for the application. This measurement is made by the determination of peel strength, i.e. the force per unit width required to peel the structure apart. A number of standard methods have been

established for conducting this test, with a climbing drum peel and a fl oating roller peel being two regular approaches. The aim is to apply fi ve methods to the measurement of peel strength and adhesive fracture toughness for two experimental aerospace laminates. This requires the following steps: global energy analysis of the climbing drum peel and the fl oating roller peel methods in order to derive expressions for adhesive fracture toughness from the usual peel strength measurement; a critical review of the calculations involved in the fi xed arm peel and T-peel procedures, and the development of an experimental method for the determination of the radius of curvature of the peel arm, as this is a key parameter involved in the analytical methods; and application of the mandrel peel test with the aim of providing an alleged credible value of the adhesive fracture toughness that can act as a reference. An attempt is made to provide critical and constructive comment in terms of using peel methods to assess and select adhesives for aerospace applications. 11 refs.

Accession no.939182

Item 296Structural Adhesives in Engineering VII. Proceedings of a conference held Bristol, 13th-15th July 2004.London, IOM Communications Ltd., 2004, Paper 35, pp.3COMELD TM-A NEW APPROACH IN COMPOSITE TO METAL BONDINGKellar E J C; Smith FTWI(IOM Communications Ltd.; UK,Society for Adhesion and Adhesives)

The use of composite materials in parts of primary structures can provide signifi cant weight savings while also giving performance benefi ts. However, the joining of composite materials to metals in primary structures presents many challenges. The joint must be able to sustain high levels of often-repeated loading over a wide range of environmental conditions, especially in key applications within the aerospace, military, marine and automotive sectors. The design of the joint and the surface preparation of the adherends (especially the metal) are often a compromise between achieving reliability and performance. The aim of the development work described is to investigate whether the application of a new surface treatment technique, called Surfi-Sculpt, into a new joining system, Comeld, would improve the mechanical performance of joints between composite materials and metals. The data generated show that Comeld joints fail at higher loads than control specimens and prevent sudden bond-line failure occurring. Comeld joints also give a more progressive, and therefore detectable, failure mode than the control joints and absorb more than twice as much energy before failure than the control joints. The material combinations and composite processing route demonstrated are chosen to appeal to certain industry sectors. Further research demonstrates that the technology described is equally applicable to other metals, composite



materials, processing routes and therefore industry sectors. To date Surfi -Sculpt has been successfully applied to aluminium, stainless steel and titanium alloys.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.939179

Item 297International Journal of Adhesion and Adhesives25, No.3, 2005, p.247-56DURABILITY STUDIES FOR AEROSPACE APPLICATIONS USING PEEL AND WEDGE TESTSSargent J PBAE SYSTEMS (Operations) Ltd.

An investigation was carried out into the durability of aluminium joints bonded with epoxy-based (AF163-2K06) and phenolic-based (Redux 775) aerospace adhesives using peel and wedge tests. Peel strength measurements were performed on small, 2 mm wide, specimens immersed in distilled water at 35C for over seven years. Water distribution across the width of the specimens was predicted using diffusion coeffi cient measurements and adherend displacement was determined using an optical image correlation method. 28 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.938734

Item 298SAMPE Journal41, No.2, March-April 2005, p.7-19POLYMER NANOSTRUCTURED MATERIALS FOR HIGH TEMPERATURE APPLICATIONSKoo J H; Pilato L ATexas,University; KAI Inc.

A summary of research work, which has been carried out into the use of polymer nanostructured materials for high temperature applications, is presented. These applications include fire-retardant nanocomposite coatings, nanostructured materials for propulsion systems, nanocomposite rocket ablative materials, nano-modifi ed carbon/carbon composites and damage tolerant high performance epoxy systems. The nanoparticles employed in the research work are montmorillonite organoclays, nanosilica, carbon nanofi bres and polyhedral oligomeric silsesquioxane. 22 refs.USA

Accession no.938699

Item 299Journal of Adhesion Science and Technology19, No.2, 2005, p.109-41MEASUREMENT OF THE MECHANICAL PROPERTIES OF STRUCTURAL ADHESIVES IN TENSION AND SHEAR OVER A WIDE RANGE

OF TEMPERATURESda Silva L F M; Adams R DPorto,Universidade; Bristol,University

The mechanical properties in tension and in shear over a wide range of temperatures of a bismaleimide adhesive and two epoxy adhesives were investigated by measuring strength, ductility and stiffness under static and dynamic conditions. The results are discussed in terms of the selection of adhesives for use in a mixed adhesive joint for aerospace applications. 39 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; PORTUGAL; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.938172

Item 300High Performance PlasticsJan.2005, p.4PA AND SILICONE CLOSED-CELL FOAMS

UK company Zotefoams plc has just introduced two development-grade closed-cell foams, under the brand name “Zotek”. One is based on polyamide, and the other is based on silicone. Brief details of the properties and intended applications of each are given in this little item.ZOTEFOAMS PLCEU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

ACCESSION NO.937425

Item 301ANTEC 2004. Proceedings of the 62nd SPE Annual conference held Chicago, Il., 16th-20th May, 2004.Brookfi eld, Ct., SPE, 2004, p.1558-62NANOCOMPOSITE POLYETHERIMIDE WITH HIGH THERMO OXIDATIVE STABILITYLou J; Harinath V; Sankar J; Roberts K; Uitenham LNorth Carolina,Agricultural & Tech.State Univ.(SPE)

Selected fi llers were incorporated to prepare polyetherimide composite. The infl uence of fi llers on the thermo-oxidative stability of the composite was studied by thermogravimetric analysis. The results showed that at optimal fi ller loading and characteristics, the polymer composite became superior in its thermo-oxidative stability that is very promising in widening the window of service temperature of polyimides for extremely high temperature conditions where most polymeric composites fail. The fi ndings should prove useful in developing high-temperature polymer composites for aerospace and electronics applications. 17 refs.USA

Accession no.935618

Item 302Modern Polymeric Materials for Environmental Applications. Vol. 1. Proceedings of a conference held



Krakow, Poland, 16th-18th Dec.2004.Krakow, Politechnika Krakowska, 2004, p.109-12RECENT ADVANCES IN POLYMER NANOCOMPOSITES IN AEROSPACE APPLICATIONSNjuguna J; Pielichowski K; Banerjee RLondon,City University; Cracow,University of Technology(Cracow,University of Technology)

Polymeric composite structures including fi bre-reinforced (nano)composites, piezoelectric polymers, polymer matrix resins, polymeric coatings and adhesives, and components for vehicle health systems and electronic appliances are reviewed in terms of structural applications. Applications of advanced polymers in ultra-lightweight structures and shape memory macromolecular systems are outlined. 7 refs.EASTERN EUROPE; EU; EUROPEAN COMMUNITY; EUROPEAN UNION; POLAND; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.935002

Item 303JEC CompositesNo.14, Jan.2005, p.59-61HIGH-PERFORMANCE MATERIALS FOR AIRCRAFT APPLICATIONSCoiffi er-Colas C; Sibois H; Lefebure PDassault Aviation; Eurocopter; European Aeronautic Defence & Space Co.

The processing techniques and welding methods considered potentially suitable for the cost-effective fabrication of aircraft parts from high-performance thermoplastic composites are discussed. European companies and institutes involved in the development of these composites for the aerospace industry are listed and other industries interested in thermoplastic composites indicated.

Accession no.934102

Item 304PU MagazinNo.4, Aug.-Sept.2004, p.184-95GermanPOLYUREA OF THE FOURTH GENERATIONKlockemann KNitroil Performance Chemicals

In the past 20 years, polyurea technology has gone through a number of distinct phases. Nowadays, all these applications are made from pure polyurea with 100% amine on the resin side, not containing solvents or other viscosity reducers discussed in the past. Consequently, today’s polyurea formulations fulfi l 2010 VOC (volatile organic compounds) requirements and have become fairly easy to apply. Developments in polyurea over the past 18 months and state of the art application techniques provide more options and opportunities than those developments

of the past 15 years. The variety of product selection options such as high temperature resistance, high shock absorption, adjustable adhesion (from peelable, temporary protection to strongly, permanent adhering), and other current coating developments are accompanied by recent performance steps from the so called generations 3 and 4. These performance steps provide long gel times (up to 4 minutes for self-levelling applications) and allow coating preparation with joint or crack fi lling polyurea formulations which provide excellent inter-layer material compatibility as well as extremely high shock absorbing multi-level polyurea coatings incorporating viscoelastic polyurea foam layers. The technology of polyurea has gone through an enormous development and different generations - from huge, high pressure processing machines towards handy, easy-to-operate equipment and from an extremely fast reaction towards controlled reaction and curing behaviour. In the latest developments, the unique advantages of polyurea coatings and foams are combined. Major applications are insulation for pipes or pipelines carrying hot materials with temperatures consistently around 180 deg.C and applications in the aerospace industry and industrial maintenance. Basically, these latest developments are a continuation of recently presented oligoamines chemistry which allows controlled cure times and thus makes polyurea suitable for slow cure spray and cast applications. 8 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.931427

Item 305Composites Science and Technology64, Nos.13-4, 2004, p.2051-65MODELING OF PERMEATION AND DAMAGE IN GRAPHITE/EPOXY LAMINATES FOR CRYOGENIC FUEL STORAGERoy S; Benjamin MOklahoma State University

Polymer-matrix composite (PMC) materials are ideal for aerospace structural applications, such as cryogenic fuel tanks of reusable launch vehicles (RLVs) and expendable launch vehicles (ELVs), due to their high strength-to-weight and stiffness-to-weight ratio. For the confi dent application of these materials, it is necessary to evaluate the permeation of cryogenic fuel caused due to transverse matrix cracks in conjunction with inter-ply delaminations resulting in an intersecting network of passages. An expression for predicting delaminated crack opening displacement (DCOD) is derived based on fi rst-order shear laminate theory applied to fi ve-layer and three-layer models. The DCOD obtained using both fi ve-layer and three-layer model is verifi ed using 2D fi nite-element analysis. A mathematical model to predict permeability in graphite-epoxy laminate system (IM-7/PETI-5) is developed using Darcy’s law for isothermal,



viscous fl ow of gases through porous media. The results obtained from both fi ve-layer and three-layer model are used as input to the permeability model. Using this model, the permeability is calculated for an orthotropic laminate lay-up for a given delamination length, crack density and loading conditions. 12 refs.USA

Accession no.931389

Item 306Materials and Processing - Sailing into the Future. Vol.36, Proceedings of the 36th International SAMPE Technical Conference held San Diego, Ca., 15th-18th Nov.2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 92, pp.8AN EXAMINATION OF AN ADHESIVE BONDING PORTFOLIO TO SATISFY THE NEED FOR OUT-OF-AUTOCLAVE COST REDUCTION INITIATIVES FOR AEROSPACE STRUCTURAL BONDINGLEGRAND D S

HENKEL TECHNOLOGIES

(SAMPE)

The results are reported of an examination of paste and fi lm adhesives for aerospace applications with the aim of reducing costs and providing equivalent mechanical performance to adhesives cured in classical autoclave conditions. Tests were conducted on Hysol EA9380 adhesive paste and Hysol EA9696.06NW adhesive fi lm curing at low temperatures and data provided on mechanical performance versus cure temperature, cure pressure and cure time. Snap cure systems curing within 30 minutes of being placed in a hot oven are considered promising candidates for cost reduction. 2 refs.USA

Accession no.930824

Item 307Materials and Processing - Sailing into the Future. Vol.36, Proceedings of the 36th International SAMPE Technical Conference held San Diego, Ca., 15th-18th Nov.2004.Covina, Ca., SAMPE International Business Offi ce, 2004, Paper 56, pp.13COMPOSITE MANUFACTURING BY USING A NOVEL MODULAR 2.45 GHZ MICROWAVE PROCESSING SYSTEMFeher L; Drechsler K; Filsinger JForschungszentrum Karlsruhe GmbH; Stuttgart,University; EADS Corporate Research(SAMPE)

The features of a novel industrial microwave system, called Hephaistos, for the automated processing of carbon fi bre-reinforced composites are described and the fabrication of composites for aerospace applications therewith is

demonstrated. The microwave system integrates basic processing steps, such as tooling, tempering, lay-up, impregnation and preforming, with curing and can be used as a stand-alone processing system or as an upgrade system for existing autoclaves. 7 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.930793

Item 308Journal of Adhesion80, No.12, Dec.2004, p.1153-72EVALUATION OF THE LONG-TERM DURABILITY OF HIGH-PERFORMANCE POLYIMIDE ADHESIVES FOR BONDING TITANIUMXu S; Guo S; Dillard D AVirginia,Polytechnic Institute & State University

The long-term durability of high-performance polyimide adhesives for bonding titanium alloy for potential aerospace applications was investigated by DMA, tensile, fracture, flexural and creep testing before and after high-temperature environmental ageing for prolonged periods. The effects of simultaneous reversible physical ageing and irreversible chemical ageing on adhesive bond performance are discussed for several different bonding systems. 24 refs.USA

Accession no.930469

Item 309Composites Technology10, No.6, Suppl., Dec.2004, p.8/41WORLD OF COMPOSITES: AN OVERVIEW

This article provides an overview of the world of composites, including fi bres and matrix materials, part design criteria, fabrication methods and applications.WORLD

Accession no.930307

Item 310Polymer Composites25, No.6, Dec. 2004, p.630-45BIG RETURNS FROM SMALL FIBERS: A REVIEW OF POLYMER/CARBON NANOTUBE COMPOSITESBreuer O; Sundararaj UAlberta,University

A review is presented of recent studies conducted on carbon nanotube/polymer composites. The size scale, aspect ratio and properties of nanotubes are reported to provide advantages in a variety of applications, providing electrostatic dissipation, a combination of strength, stiffness and impact properties. The various processing



methods for the production of nanocomposites are discussed, in particular, melt mixing, solution processing, and in-situ polymerisation. Key results are summarised relating to the mechanical, electrical, thermal, optical and surface properties of nanocomposites. The article also discusses the challenges for the future in terms of processing, characterisation, nanotube supply, nanotube tailoring, and the mechanisms governing the behaviour of nanoscale composites. 253 refs.CANADA

Accession no.930128

Item 311Rubber Chemistry and Technology77, No.3, July-Aug.2004, p.542-51NAVAL APPLICATIONS OF ELASTOMERSRoland C MUS,Naval Research Laboratory

A short review is presented of the literature on selected uses of rubber by the U.S. Navy on surface vessels, submarines and aircraft. The emphasis is on applications which exploit rubber’s capacity for energy transmission, storage and dissipation, including acoustic applications and aircraft tyres. Developing naval technologies are described. 27 refs.USA

Accession no.928925

Item 312Macromolecules37, No.19, 21st Sept.2004, p.7250EPOXY-LAYERED SILICATE NANOCOMPOSITES AND THEIR GAS PERMEATION PROPERTIESOsman M A; Mittal V; Morbidelli M; Suter U W ETH Zurich

The use of organically modifi ed clay as fi ller in epoxy resin nanocomposites, and the effect of different ammonium salts as surface treatments on the clay, was examined by X-ray diffraction, transmission electron microscopy and gas permeability. In particular the oxygen permeability was related to the morphological structure of the nanocomposites, with intercalation, exfoliation, particle shape and molecular length considered. Transmission of water vapour through the composites was shown to be dependent on the hydrophobicity of the clay inclusions. 41 refs.SWITZERLAND; WESTERN EUROPE

Accession no.928585

Item 313Advanced Materials and Composites News26, No.22, 15th Nov.2004, p.1-3ROHACELL STRUCTURAL FOAM CORES MAKE SUCCESSFUL A-STRINGER PROFILES

FOR ENGINE PANELS

The use of stringer profi les has proven to be the most suitable method for stiffening thin carbon/epoxy shells, typically used as engine air inlet duct panels or engine cowling panels. The most effective stiffening can be achieved by using A or hat stringer profi les. Structural Rohacell sandwich foam cores are successfully used in a number of such kinds of aircraft applications. One of the latest applications for foam fi lled stringer profi les is the rear pressure bulkhead of the Airbus A340 and A340-600. The use of Rohacell foam as a mandrel and as a structural member of the sandwich design is discussed.

Rohm AmericaUSA

Accession no.928470

Item 314SAMPE Journal40, No.6, Nov.-Dec.2004, p.23-31THE DEVELOPMENT OF HIGH-TEMPERATURE POLYIMIDES FOR RESIN TRANSFER MOULDINGGray R A; McGrath L RMaverick Corp.

The development of high-temperature polyimide resin systems, characterised by viscosity and glass transition temperature, for resin transfer moulding (RTM) was investigated and the properties of the resulting laminates with carbon fi bres were characterised by mechanical properties including compression strength and interlaminar shear strength. Potential aerospace applications of the resins are discussed. 19 refs.USA

Accession no.927649

Item 315Polymer Testing23, No.8, 2004, p.903MODELING YOUNG’S MODULUS OF RUBBER-CLAY NANOCOMPOSITES USING COMPOSITE THEORIESWu Y-P; Jia Q-X; Yu D-S; Zhang L-Q Beijing,University of Chemical Technology

An investigation was carried out to establish whether the Guth, Halpin-Tsai and modifi ed Halpin-Tsai equations could be employed to explain the superior reinforcing effi ciency of rubber-clay nanocomposites. A modulus reduction factor for the platelike fi llers was established and introduced into the equations and the predictability of the modifi ed equations evaluated. A comparison of experimental data for nanocomposites based on clay and matrices of SBR, NBR and carboxylated NBR with the predictions of the models revealed that the predictability of the models was improved By the introduction of the modulus reduction factor. 24 refs.



CHINA

Accession no.927012

Item 316International Journal of Adhesion and Adhesives25, No.1, 2005, p.47-59ADHESIVE AND COMPOSITE FAILURE PREDICTION OF SINGLE-L JOINT STRUCTURES UNDER TENSILE LOADINGFeih S; Shercliff H RCambridge,University; TWI Ltd.

An investigation was carried out into the design of composite single-L peel joints under tensile loading using, as the adherends, high-tensile strength, unidirectional carbon fi bre prepreg with an epoxy matrix and, as the adhesives, two epoxy resins suitable for aerospace applications. Repeatable joint designs were guaranteed using an adhesive injection method and joint optimisation was achieved through fi llet shape changes. Sub-critical composite failure, composite delamination and adhesive failure were analysed numerically, the failure load best for different fi llet shapes was predicted using a zone criterion and crack growth during adhesive failure was simulated using a damage mechanics approach. 25 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.926099

Item 317Plastics Additives and Compounding6, No.5, Sept.-Oct.2004, p.4METALLOCENE WAXES GO INTO PRODUCTION

The Pigments & Additives Division of Clariant is building the world’s fi rst plant where waxes are produced by metallocene catalysis. The new high-performance polymers produced with metallocene catalysts are known as Licocene. The property profi le of Licocene can be optimised for different applications. The company claims that for the fi rst time it is possible to design waxes with particular properties, such as hardness, melt behaviour and viscosity, which can be adjusted exactly within a wide range. The family of waxes comprises mainly special PP types, as well as waxes based on PE and copolymers. Applications include dispersion agents in masterbatches and in glass- and natural fi bre-reinforced compounds, often in the aircraft and automotive industries.

Clariant,Pigments & Additives Div.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.925637

Item 318Journal of Materials - Design and Applications (Part L)218, No.L3, Aug.2004, p.253-60DEVELOPMENT AND APPLICATION OF

ADVANCED COMPOSITESBannister M KAustralia,Cooperative Research Centre for Advanced Composite Structures

The fabrication of three-dimensional fi bre-reinforced polymer composites by the textile processes of weaving, braiding, stitching and knitting and their mechanical properties are reviewed. Current and potential applications of these composites in the aerospace, maritime, automotive, building and biomedical fi elds are discussed. 28 refs.AUSTRALIA

Accession no.924175

Item 319Advanced Composite Materials13, No.2, 2004, p.81-8PRESSURIZATION TEST ON CFRP LINER-LESS TANKS AT LIQUEFIED NITROGEN TEMPERATUREMorimoto T; Ishikawa T; Yokozeki T; Hayashi Y; Shimoda T; Morino YJapan,Aerospace Exploration Agency; Tokyo,University; Tokyo Business Service Co.Ltd.

Internal pressurisation tests were carried out on toughened epoxy CFRP liner-less tanks at liquid nitrogen temperatures inside a vacuum chamber, and damage onsets such as transverse cracking and leak path formation, were monitored using helium fl ow detection, acoustic emission, and pressure-strain monitoring. The results are discussed in terms of aerospace applications. 18 refs.JAPAN

Accession no.922602

Item 320Reinforced Plastics48, No.9, Oct.2004, p.46-8CHOOSING THE RIGHT CLOSED MOULDING PROCESSLoff AMolding Technologies

Selecting the right closed moulding technique to match the application is critical to successful parts production. The National Composite Center, a comprehensive resource for closed moulding technology, is helping manufacturers eliminate the guesswork with its hands-on practice and application experience. NCC organises closed moulding into the major categories of RTM, RTM Light, structural reaction injection moulding and vacuum infusion processing. Vacuum infusion produces high quality reproducible parts, low void content and near zero emissions of hazardous air pollutants for a cleaner environment. Because the process and its various techniques use a fl exible membrane on the top surface, vacuum infusion is well suited to applications involving large structural composites. Low tooling and



capital equipment costs are vacuum infusion’s primary advantage. NCC is also expanding closed moulding technology beyond the use of traditional materials by successfully infusing nanocomposite additives in large moulded parts.

US,National Composite CenterUSA

Accession no.922334

Item 321Plastics Technology50, No.7, July 2004, p.27SELF-REINFORCED” POLYMER IS NOW COMMERCIAL

This concise article draws to our attention the first commercial grade of “Parmax SRP” (self-reinforced polymer), known as “Parmax 1201”, from Mississippi Polymer Technologies Inc. in the USA. Details are provided on the properties and the intended applications of the new material.

MISSISSIPPI POLYMER TECHNOLOGIES INC.USA

Accession no.921841

Item 322Journal of Adhesion Science and Technology18, No.7, 2004, p.751-64DEVELOPMENT OF METAL-BONDING SPRAY ADHESIVES FOR USE IN AEROSPACE REPAIR APPLICATIONSTillman M SUS,Naval Air Systems Command

The results are reported of an evaluation of fi ve different spray adhesives in aerospace repair applications. The adhesives included two epoxy materials based on diglycidyl ether of Bisphenol A and Epon 828, as well as tetraglycidylmethyldianiline (Araldite MY 9512) and a commercial epoxy resin. The lap shear performance and processability of the adhesives with aluminium as the adherent were evaluated and their fracture surfaces analysed by scanning electron microscopy. 14 refs.USA

Accession no.920572

Item 323Revista de Plasticos Modernos87, No.576, June 2004, p.531-40SpanishPOLYMERS AND MANUFACTURING PROCESSES USED TO MANUFACTURE THE PRIMARY STRUCTURES OF AN AIRCRAFT: AN EXAMPLE, THE AIRBUS A-380Munoz Esquer P LAirbus Espana SA

The properties of composite materials which render them

suitable for use in the manufacture of primary structures for aeronautical applications are discussed and the manufacturing processes used are described. Particular attention is paid to the manufacture by Airbus Espana of components for the A-380, using techniques such as fi bre placement, automatic tape lay-up, resin transfer moulding, resin fi lm infusion and co-bonding/welding of thermoplastic composites.EUROPEAN COMMUNITY; EUROPEAN UNION; SPAIN; WESTERN EUROPE

Accession no.920247

Item 324Chemical and Engineering News82, No.35, 30th Aug.2004, p.34-9COMPOSITE MATERIALSJacoby M

Some 50 years ago, aircraft designers began taking advantage of the high strength-to-weight ratio associated with composites by replacing aluminium parts with others made from the newer materials. In today’s F-22 fi ghters, carbon fi bre composites compose nearly one-third of the jet’s structure. Composites have moved into terrestrial applications rather slowly. The primary obstacles have been the high cost of the materials and the labour-intensive operations and expensive fabrication equipment needed to process them. For various elements of the 500-horsepower Dodge Viper’s fender support, door structures and windshield frame, the carmaker chose parts made from carbon-based SMC or blends of composites. Scientists at the Air Force Research Laboratory at Wright Patterson Air Force Base are studying nanocomposites, focusing on ways of modifying polymer composites with nanoscale materials to produce composites that exhibit unconventional combinations of properties.USA

Accession no.919852

Item 325Synthetic Metals144, No.3, 2004, p.303-7HEAVY ION IRRADIATION ON CONDUCTING POLYPYRROLE AND ZRO2-POLYPYRROLE NANOCOMPOSITESDe A; Das A; Lahiri SSaha Institute of Nuclear Physics

Conducting polypyrrole and nanocomposites of polypyrrole with zirconium oxide were subjected to C12 and O16 beams of moderate energy to evaluate their suitability for use in space probes. An evaluation was made of the effect of irradiation on the electrical conductivity and physical properties of the pure polypyrrole and nanocomposites, which were also characterised by TGA and X-ray diffraction. The nanocomposites were found to be more suitable than the pure polypyrrole for space applications. 5 refs.



INDIA

Accession no.919209

Item 326165th ACS Rubber Division Meeting - Spring 2004. Proceedings of a conference held Grand Rapids, Mi., 17th-19th May 2004.Akron, Oh., ACS Rubber Division, 2004, Paper 21, pp.30HI-TECH FLUORO POLYMERS, NOW USED IN INCREASING VOLUME PRODUCTION, GAIN IMPORTANT BENEFIT FROM HI-TECH PROCESS ADDITIVESBruhn J; Bertrand J; Clarke C; Hensel MSchill & Seilacher Struktol AG(ACS,Rubber Div.)

Steadily increasing requests from many industries regarding technical performance of a rubber part in meeting severe technical specifi cations and regulations has an important infl uence on the increasing consumption of high tech elastomers in the rubber industry. Fluoroelastomers play an increasingly important role. Due to its outstanding proper-ties like excellent heat and weather resistance, possible use in a wide temperature range from -45 deg.C up to 275 deg.C and its resistance to a broad variety of fl uids including aliphatic and aromatic hydrocarbons and strong acids, FPM is often the polymer of fi rst choice. Automotive, aerospace and chemical industries are the main customers for FPM based parts as seals, O-rings, hoses, gaskets and rubber linings. As elastomers are specifi ed in a variety of industrial, automotive and aerospace applications, the need for effi cient part manufacture is imperative to achieve the required balance of part quality and production economy. Ease of processing also impacts part quality since processing diffi culties like mould sticking and fouling, or problems with mould fi lling or extrusion performance, can result in surface defects in e.g. O-rings and tubes. Such processing problems can result in lower productivity and increased production costs because of higher scrap material rate. The advantages of high tech processing additive Struktol HT 290 are demonstrated by showing improvement during processing of different fl uorinated polymers. Injection and extrusion results are shown and processing problems such as insuffi cient compound fl ow, compound sticking and mould fouling are solved. A new concept to rate occurring level of mould fouling and to judge the effectiveness of processing additives related to this problem is introduced and explained. 1 ref.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.918065

Item 327Popular Plastics and Packaging49, No.7, July 2004, p.63/86POLYIMIDES - TRENDSETTERS IN AEROSPACE AND ELECTRONICS

Mirchandani G; Shertukde V VMatunga,University

The classifi cation of polyimides is explained, including condensation polyimides and copolyimides, addition polyimides and thermoplastic polyimides. Polyimides exhibit excellent properties at elevated temperatures, thus qualifying them for use in applications experiencing high service temperatures. In the aerospace industry, material demands are ever increasing. Researchers have met this challenge primarily with polyimides, which can be modifi ed to meet processing conditions while maintaining several of their advantageous properties. Polyimides have been utilised for the fabrication of composites of carbon, quartz, glass, boron and graphite. The Mars Exploration Rovers currently in space include almost 70 yards each of fl exible cable circuits made of thin polyimide laminates and composites. In electronics, applications of polyimides include optical waveguides, roll-up displays, liquid crystal displays and adhesives. 20 refs.INDIA

Accession no.917856

Item 328Advanced Materials and Composites News26, No.15, 2nd Aug.2004, p.4CRYOGENIC LIQUID STORAGE DEVELOPED USING ALL-CFRP COMPOSITE TANKS

It is briefl y reported that, in an extensive Broad Area Announcement study for the Air Force, Wilson Composite Technologies concluded that liner less CFRP composite tanks offer promise for lightweight containment for the long-term storage of liquid hydrogen in space. A manufacturing innovation has been developed for the fi lament winding method for cryo use. WCT also has a second Air Force-sponsored programme to determine the compatibility of various carbon fi bre/epoxy composites with liquid oxygen (LOX). It is hoped to be able to develop composite tanks as replacement for metals for containment of LOX for launch vehicle applications.

Wilson Composite Technologies Inc.USA

Accession no.917810

Item 329JEC CompositesNo.10, June-July 2004, p.72-3NEW SELF-ADHESIVE PREPREG SYSTEMScott MHexcel

Hexcel’s self-adhesive epoxy prepreg system for use in the construction of sandwich panels for aerospace applications is described. The self-adhesive nature of HexPly M50 is shown to allow for the elimination of the adhesive fi lms required to bond the skins to honeycomb, giving weight savings of up to 10%. The peel strength is equal to or



better than those currently obtained for sandwich panels relying on standard adhesive plies. An additional benefi t of the system’s rheology is the virtual elimination of core-crush problems.USA

Accession no.917482

Item 330JEC CompositesNo.10, June-July 2004, p.46-7AUTOMATED PREFORMS: THE NEXT STEP IN REINFORCEMENTS FOR DIRECT PROCESSESGirardy HHexcel

The development by Hexcel of automated preforms with functionalised materials for use in direct processing of composite materials for aerospace applications is discussed. Binders for preform consolidation and functionalisation are described and the manufacture of the preforms is outlined. Hexcel’s RTM 6 monocomponent premixed epoxy resin system, which produces composite parts operating at service temperatures between -60 and 180C, is mentioned.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.917480

Item 331Polymer Plastics Technology and Engineering43, No.2, 2004, p.427POLYMERIC NANOCOMPOSITES: A REVIEWManiar K K Massachusetts,University

A brief review is presented on nanocomposites beginning in 1951 but paying particular attention to post-1996 studies. It is based upon technical publications, which are mostly obtained from ANTEC and SAMPE proceedings and patents. 103 refs.USA

Accession no.916739

Item 332Journal of Materials Science39, No.8, 15th April 2004, p.2855-9INTERFACIAL FRACTURE TOUGHNESS OF POLYESTER-BASED FIBER-METAL LAMINATES WITH PRIMARY CONTACT AND SECONDARY ADHESIVE BONDINGBurns M J; Compston PAustralian National University

Results are presented of preliminary studies of the characterisation of interfacial fracture toughness for two fibre-metal laminates(FMLs) based on materials and manufacturing techniques suitable for non-aerospace and relatively low cost applications. The fi rst FML is based on

primary contact bonding at the bimaterial interface, i.e. simple wet lay-up of glass/polyester to aluminium. The second is based on secondary adhesive bonding where the aluminium and pre-cured laminates are manufactured in a simple stamping process with a hot-melt thermoplastic adhesive at the interface. The results demonstrate that a simple heating-stamping manufacturing process has potential for high volume production of relatively low cost thermoset-based FMLs with a tough ethylene-based thermoplastic fi lm adhesive at the bimaterial interface to ensure interfacial fracture toughness. 7 refs.AUSTRALIA

Accession no.916034

Item 333Eureka24, No.5, May 2004, p.31-2COMPOSITES GO FROM STRENGTH TO STRENGTH

Shelley TThis article reports on some of the latest enhancements in fi bre-reinforced plastic composites, for use in aerospace and military applications. Details of these breakthrough developments were recently presented at the symposium entitled “Composites - the Cutting Edge”, which was part of the Materials Congress 2004 hosted by the UK Institute of Materials, Minerals & Mining.UK,INSTITUTE OF MATERIALS,MINERALS & MINING; LEEDS,UNIVERSITY; LONDON,UNIVERSITY,QUEEN MARY COLLEGE; BOLTON,INSTITUTE OF HIGHER EDUCATION; BRISTOL,UNIVERSITY

EU; EUROPEAN COMMUNITY; EUROPEAN UNION; ITALY; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.914679

Item 334Polyurethanes Expo 2003. Proceedings of a conference held Orlando, Florida, 1st-3rd Oct.2003.Arlington, VA, Alliance for the Polyurethanes Industry, 2003, p.79-85HOT STUFF - THERE IS ANOTHER HURDLE TO TAKE FOR POLYUREA: FROM COATINGS AND SEALANTS TO MICRO CELLULAR FOAMSKlockemann K; Bader MPerformance Chemical International Corp.; Institute for Polyurethane Technology GmbH(American Plastics Council; Alliance for the Polyurethanes Industry)

Polyurea technology has experienced enormous development. From huge, high pressure processing machines to handy, easy-to-operate equipment and from an extremely fast reaction towards controlled reaction and curing behaviour. In Nitroil Performance Chemicals’ latest developments the unique advantages of polyurea coatings and foams are combined. Major applications are insulation for pipes or pipelines carrying hot materials with



temperatures consistently around 350 deg.F or applications in the aerospace industry and industrial maintenance. These latest developments are a continuation of the recently developed oligoamines which allow controlled cure times and thus make polyurea suitable for cast applications. In combination with these amines and blowing agents like HFC 245 fa or HFC 365 mfc, microcellular foams are achieved. Due to their good chemical resistance, heat stability and excellent physical properties, especially impact and abrasion resistance, microcellular polyurea foams offer a new dimension of protective materials with alternative uses, e.g. as dust sealant for switch boxes or fuse cabinets as well as protective soles for shoes exposed to extreme conditions in the workplace. It is demonstrated that properties such as hardness, cell structure, density or resilience can easily be manipulated through the use of an additive package, typically consisting of a blowing agent and a silicone surfactant, whereas the current range of polyurea foams prepared without any additive package is limited in variability but of excellent homogeneity in cell structure and elastic properties. 3 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; USA; WESTERN EUROPE

Accession no.914051

Item 335Reinforced Plastics48, No.6, June 2004, p.42-3FLEXIBLE WAY TO JOIN COMPOSITESScott ReeveUS,National Composite Center

Manufacturers face challenges when it comes to joining composites to other materials. To help companies overcome this production obstacle, the National Composite Center’s patented Litecast process offers a robust joining solution. Litecast offers a fl exible option to mechanical fastening and adhesive systems which can add extra labour costs and reduce the strength of composite products. Litecast produces a mechanical joint that requires no application of adhesives. Molten metals, like aluminium and magnesium, are cast directly onto the composite structure in a die casting operation. Controlled vapourisation of the outer resin layer leaves metal interlocked with the fi bres in the composite to create a mechanical bond. NCC is looking to license the technology to companies which want to implement a reliable joining solution at the design or production phase. Two recent examples include applications for the heavy-duty truck market and earth-orbiting space structures.USA

Accession no.913572

Item 336Reinforced Plastics48, No.4, April 2004, p.28-31UNMANNED AERIAL VEHICLES SPUR COMPOSITES USEBorchardt J K

Unmanned aerial vehicles or UAVs are of growing interest to military operations, but they can also be used in a variety of civilian applications such as monitoring and controlling traffi c fl ow and search/rescue operations. Use of lightweight advanced composites is essential in increasing UAV fl ight time. Thermosets are used more than thermoplastics because the resin readily impregnates fi bres, making it possible to manufacture complex shaped parts. Completely synthetic composite propellers are beginning to be used because they provide both high performance and durability. These are typically comprised of carbon/glass fabric impregnated with high-temperature epoxy resin. The University of Sydney’s UAV Brumby was developed for fl ight research. The main gear of the undercarriage is a carbon fi bre/Kevlar fi bre composite, the fuselage is constructed with a sandwich composite of glass fi bre/Nomex resin and the wings are a composite of glass/Nomex resin.AUSTRALIA; USA

Accession no.910935

Item 337High-Performance Composites12, No.2, March 2004, p.38-43SIZING AND SURFACE TREATMENT: THE KEYS TO CARBON FIBER’S FUTURE?Fisher Mason K

Surface treatment and sizing, the fi nal two steps in the carbon fibre manufacturing process, are the subject of notable trade secrecy. Surface treatment produces additional bonding sites on the fi bre surface, while sizing enhances fi bre processability with a protective coating on the fi bre surface and can provide a coupling agent for the fi bre/resin bond. The relationship between surface treatment and sizing is complex, and the effectiveness of each depends on its compatibility with both the fi bre and the resin. The vast majority of carbon fi bre is still incorporated into standard, qualifi ed epoxy resin systems via well-known fabricating processes, for which sizing and surface treatment “recipes” are so well established and reliable that choice of fi bre is typically based on economics. In a signifi cant and growing number of new applications the risk of fibre/resin incompatibility is increasing, as “off-the-shelf” carbon reinforcements are introduced to applications for which the matrix will be highly modifi ed epoxy resins or non-epoxies such as vinyl ester, polyimide or PEEK.USA

Accession no.909690

Item 338Journal of Applied Polymer Science91, No.5, 5th March 2004, p.3096-106ENHANCEMENT OF PHENOLIC POLYMER PROPERTIES BY USE OF ETHYLENE GLYCOL AS DILUENT



Singh K P; Palmese G RDelaware,University; Drexel,University

Phenolic resins are used for the inner linings of GRP composites in applications such as aircraft or armoured tanks, where fi re resistance is essential. The phenolic resins usually contain water as a diluent to facilitate moulding. Water controls the viscosity, but its evaporation from the resin during cure has caused microvoids to appear in the cured resin which are believed to adversely affect the properties of the fi nal product. The effects of processing parameters such as cure temperature, post cure temperature, catalyst concentration and the use of ethylene glycol as a replacement diluent were studied on the water loss, microvoid distribution and hence the mechanical properties of the polymer. Replacing the initial water with ethylene glycol had the most signifi cant effect on the microvoids and the properties of the polymer. This resulted in a decrease in the void content, an increase in density and a signifi cant improvement in the fl exural modulus and fracture toughness. 10 refs.USA

Accession no.909460

Item 339Journal of Polymer Science: Polymer Chemistry Edition42,No.4, 15th Feb.2004, p.825-34SYNTHESIS AND CHARACTERISATION OF NEW SOLUBLE POLYAZOMETHINES BEARING FLUORENE AND CARBAZOLE UNITS IN THE BACKBONE AND SOLUBILITY IMPROVING MOIETIES IN THE SIDE GROUPKim H-C; Kim J-S; Kim K-S; Park H-K; Baek S; Ree MPohang,University of Science & Technology

The synthesis and characterisation is described of a series of novel, soluble, polyazomethines with fl uorene and carbazole moieties in the main chain and solubility improving groups such as dibutyl, ethylhexyl, thienylethoxy, furyl and fl uorenyl in the side group. Solution casting was used to prepare fi lms. The glass transition temperature, melting point and thermal stability were determined. The side groups were found to improve solubility, without sacrifi cing thermal stability. The products are candidate materials for applications in micro-electronics and aerospace. Features in the UV- visible spectra were red shifted compare to the monomers, indicating that they might be suitable for doping to produce opto-electronic devices. 22 Refs.KOREA

Accession no.908774

Item 340Materials And Processing - Enabling Flight: Our Legacy And Our Future. Vol.35. PROCEEDINGS OF THE 35TH INTERNATIONAL

SAMPE TECHNICAL CONFERENCE HELD DAYTON, OH., 28TH SEPT.-2ND OCT.2003.Covina, Ca., SAMPE International Business Offi ce, 2003, Paper 105, pp.11PMI FOAMS FOR STRUCTURAL AEROSPACE APPLICATIONSSeibert H FRohm GmbH & Co.KG(SAMPE)

The use of polymethacrylimide(PMI) foams in large sandwich components for the Delta family of satellite launchers is described and the reasons for selection of PMI sandwich technology instead of the traditionally-used aluminium honeyconb-cored sandwich design are discussed. Structural applications for civil aircraft such as the front landing gear door of the FD 728, obtained by resin infusion, and the pressure bulkheads and ailerons of the Airbus A340-600 and A380 are reported. The advantages over honeycomb design are considered, with emphasis on manufacturing costs and life cycle costs. Two recently-launched grades of PMI foams, designed for use in the resin infusion process, are described. 9 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.908059

Item 341Materials And Processing - Enabling Flight: Our Legacy And Our Future. Vol.35.Proceedings of the 35th International SAMPE Technical Conference held Dayton, Oh., 28th Sept.-2nd Oct.2003.Covina, Ca., SAMPE International Business Offi ce, 2003, Paper 50, pp.9LIGHTWEIGHT, DAMAGE TOLERANT COMPOSITE SANDWICH STRUCTURES FOR HIGH TEMPERATURE APPLICATIONS IN AIRCRAFT ENGINE COMPONENTSSheppard M; Campbell G S; Stoll FWebCore Technologies Inc.(SAMPE)

A programme was conducted to evaluate TYCOR sandwich panels moulded using a vacuum infusion process(VIP) for use as lightweight, cost-effective, damage-tolerant structures for aircraft engine components. TYCOR sandwich cores used low density foam coupled with structural fi bres to create core material with specifi c structural properties. Two components, an engine fan case and an inlet guide vane, were studied. Full body of revolution VIP moulding was evaluated as a means of processing engine case components. Foam and resin studies were conducted to determine appropriate materials for use in composite fan case and inlet guide vanes. Prototype TYCOR sandwich panels were fabricated and tested for both the fan case and hollow inlet guide vanes.USA

Accession no.908023



Item 342Materials And Processing - Enabling Flight: Our Legacy And Our Future. Vol.35. Proceedings of the 35th International SAMPE Technical Conference held Dayton, Oh., 28th Sept.-2nd Oct.2003.COVINA, CA., SAMPE INTERNATIONAL BUSINESS OFFICE, 2003, PAPER 40, PP.15 DEVELOPMENT OF HIGH-TEMPERATURE POLYIMIDES FOR RESIN TRANSFER MOLDINGGray R A; McGrath L RMaverick Corp.(SAMPE)

A series of addition-cured, polyimide resin systems was developed for high-temperature resin transfer moulding(RTM) applications. These resin systems were specifi cally designed to be cost competitive and free of mutagenic or carcinogenic materials. Monomer stoichiometry and oligomer molec.wt. were balanced in order to produce RTM polyimides that exhibited low melt viscosity. Laminates were fabricated using commercial RTM equipment and found to be free of voids and microcracks. All the candidate systems that exhibited potential were physically and mechanically tested. An RTM resin was identifi ed that had a dry Tg of 305C and good property retention up to 260C. Potential applications of these resins in commercial and military aircraft, launch vehicles and satellites and dual use applications in the automotive and chemical industry are considered. 19 refs.USA

Accession no.908014

Item 343Materials And Processing - Enabling Flight: Our Legacy And Our Future. Vol.35. Proceedings of the 35th International SAMPE Technical Conference held Dayton, Oh., 28th Sept.-2nd Oct.2003.Covina, Ca., SAMPE International Business Offi ce, 2003, Paper 38, pp.9DESIGN AND CHARACTERIZATION OF THERMOSETTING POLYIMIDE COMPOSITE MATRIX SYSTEMSMcGrath J E; Bullions T; Loos A C; Tan B; Watanabe YVirginia,Polytechnic Institute & State University; Eastman Kodak Co.(SAMPE)

An overview is given of the curing, physical behaviour and stability of arylene ether imide oligomers for polymer matrix composites based on well-known available monomers and functionalised with phenyl ethynyl end groups. The phenylethynyl curable arylene ether imide oligomers based on structures analogous to the well-known thermoplastic material Ultem are shown to be suitable for use as the basis of chemically-resistant thermooxidatively- stable materials at 200C for long durations (up to 5000 hours). The possibility of using these materials in future

high performance aerospace applications is examined. 14 refs.USA

Accession no.908012

Item 344High-Performance Composites12, No.1, Jan.2004, p.22-7NICHE ADHESIVES PROFILERATE FOR SPECIALIZED APPLICATIONSDaggett S S

This article discusses the development of structural adhesives for aerospace applications. The two basic forms of structural adhesives, fi lms and pastes, are examined.USA

Accession no.906372

Item 345Shawbury, Rapra Technology Ltd., 2004, pp.x, 290HANDBOOK OF POLYMER FOAMSRapra Technology Ltd.Edited by: Eaves D

Although naturally occurring polymer foams have been known for a long time, (e.g. sponges, cork), synthetic polymer foams have only been introduced to the market over the last fi fty years or so. The development of a new polymer has usually been quickly followed by its production in an expanded or foam form owing to the unique and useful properties, which can be realised in the expanded state. This Handbook reviews the chemistry, manufacturing methods, properties and applications of the synthetic polymer foams used in most applications. In addition, a chapter is included on the fundamental principles, which apply to all polymer foams. There is also a chapter on the blowing agents used to expand polymers, blowing agents having undergone considerable change and development in recent years in order to meet the requirements of the Montreal Protocol in relation to the reduction and elimination of chlorofl uorocarbons (CFC) and other ozone depleting agents. A chapter is also included on microcellular foams - a relatively new development where applications are still being explored.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.906056

Item 346Journal of Advanced Materials36, No.1, Jan.2004, p.3-11EXPERIMENTAL INVESTIGATION OF RESIN TRANSFER MOLDED T-300/PR520 LAMINATE PROPERTIESStickler P B; Ramulu M; Tuttle M E; Coguill S LBoeing Co.; Washington,University; Wyoming,University



The physical, mechanical and strength properties of resin transfer moulded T-300/PR520 graphite fibre/epoxy resin laminates for use in aerospace primary structural applications were investigated. The physical properties included fi bre, matrix and void volumes. Both in-plane and out-of-plane elastic and strength properties were determined. In-plane tension, compression and shear elastic and strength properties were developed using standard test methods. In-plane elastic properties were estimated using a micromechanical analysis and laminate effective properties were calculated using laminated plate theory. Predicted in-plane elastic properties were compared with experimentally-determined values. Out-of-plane shear elastic and strength properties were developed using a standard v-notch beam method and out-of-plane tension properties were experimentally determined using a draft ASTM specifi cation. Signifi cant observations of the experimental test methods, variations in experimental data and specimen failure modes were provided. The results were used in subsequent experimental and numerical analyses of structural T-joints fabricated using these materials and processes. 24 refs.USA

Accession no.905787

Item 347IRC 2003. Proceedings of a conference held Nuremberg, 30th June-3rd July 2003.Frankfurt, Deutsche Kautschuk Gesellschaft eV, 2003, p.87-90NEW FLUOROELASTOMERS WITH IMPROVED LOW TEMPERATURE PERFORMANCEBach D; Van Gool G; Steffens JDyneon GmbH & Co.KG(Deutsche Kautschuk Gesellschaft eV)

Low temperature fl uoroelastomers for use in automotive, aerospace and chemical processing sealing applications are a class of true ‘specialty’ within the commercially available group of fl uoroelastomers (FKM). Currently available fl uoroelastomers designed for low temperature service applications are typically tetra-polymers of tetrafl uoroethylene (TFE), vinylidene fl uoride (VF2), a perfluoro alkylvinylether (PAVE), e.g. perfluoro methylvinylether (PAVE) and a cure site monomer (CSM), to allow the formation of a crosslinked network using an organic peroxide system. The complete substitution of hexafluoropropylene (HFP) in ‘traditional’ FKM fluoroelastomers through PAVE type co-monomers lowers the glass transition temperature and offers a good balance of low temperature flexibility while maintaining fl uid and chemical resistance useful for harsh industrial environments. A new class of low temperature fl uoroelastomers, where the historic properties of PAVEs are complemented by perfl uoro alkoxy alkylvinylethers (PAAVEs), is presented. Compared to currently commercial available PMVE containing FKMs, Dyneon’s new class of low temperature FKMs demonstrate superior chemical

resistance, high thermostability and unmatched low temperature properties. 6 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.905554

Item 348European Polymer Journal40, No.1, Jan.2004, p187-95THERMAL STABILITY AND WATER UPTAKE OF HIGH PERFORMANCE EPOXY LAYERED SILICATE NANOCOMPOSITESBecker O; Varley R J; Simon G PMonash,University

The water uptake and thermal stability of a range of nanocomposites have been studied since they have potential in high performance applications such as aerospace. Three commercial epoxy systems were used as matrices: diglycidyl ether of bisphenol A (DEGBA), triglycidyl p-amino phenol (TGAP) and tetraglycidyl diaminodiphenyl methane (TGDDM). A commercial organoclay, octadecyl ammonium ion-modified montmorillonite layered silicate, was used in concentrations between 0 and 10%. Thermal stability parameters were determined using thermogravimetric analysis. Dynamic mechanical thermal analysis was used to determine equilibrium water uptake, diffusion coeffi cient and alpha- and beta-transition peak temperatures before and after water sorption. It was found that the nanocomposites showed a slight decrease in thermal stability of 5-10 centigrade at 10% clay concentration. Water sorption was decreased relative to neat epoxies however the rate of water diffusion remained the same. 37 refs.AUSTRALIA

Accession no.905513

Item 349High Performance Polymers15, No,4, Dec.2003, p.375-94HIGH TEMPERATURE TRANSFER MOLDING RESINS. LAMINATE PROPERTIES OF PETI-298 AND PETI-330Connell J W; Smith J G; Hergenrother P M; Criss J MUS,NASA,Langley Research Center; M & P Technologies Inc.

Two phenylethynyl terminated oligomers were developed as candidates for composite applications requiring high temperature performance combined with the ability to be readily processed into composites. Potential applications on advanced aerospace vehicles and as aircraft engine components are mentioned. The resins were processed using resin transfer moulding, vacuum assisted resin transfer moulding and resin infusion. The chemistry of the compounds and carbon fabric laminate properties are presented. 25 refs.



USA

Accession no.903237

Item 350Composites Technology9, No.4, Aug.2003, p.26-9VINYL ESTERS MAKE TOUGH PARTS FOR HIGHLY CORROSIVE APPLICATIONSBlack S

An array of case studies showcases the growing acceptance of glass fi bre/vinyl ester composites in harsh industrial environments. The direct cost of metallic corrosion in the USA is staggeringly high - 276 billion UD dollars/year, or about 3% of the country’s gross domestic product (GDP), according to a 2002 report entitled Corrosion Costs and Preventive Strategies in the United States, issued by the US Federal Highway Administration and written by CC Technologies Laboratories, with support from NACE International (National Association of Corrosion Engineers). Every sector of the economy pays the price, including civil infrastructure (highways and bridges), pipelines, water and sewer systems, electrical utilities, ships and aircraft industrial plants and military installations. While there are many strategies for fi ghting the problem - better inspection methods, improved management practices and life-prediction computer models - one of the most obvious solutions is to replace corrosion-prone metal materials with composites. Fibre-reinforced polymer composites made with chemical-resistant resins are virtually corrosion-free and can provide decades of maintenance-free performance, as documented by countless case studies, some of which are outlined.US,FEDERAL HIGHWAY ADMINISTRATION; CC TECHNOLOGIES LABORATORIES INC.

USA

Accession no.901085

Item 351Future MaterialsNov.-Dec.2003, p.25ADDED TRANSPARENCY

M.C. Gill has developed a transparent laminate for use as a see-through aircraft cargo liner, allowing visual inspections of goods in transit without their removal. Unlike previous transparent plastics, Gillite 1401 Transparent Laminate offers improved strength using fi breglass reinforcement and exceptional flammability properties including compliance with burn through requirements. Other potential applications include cargo containers, ceiling panels in commercial transport vehicles, equipment housings and architectural uses.

GILL M.C.,CORP.USA

Accession no.900973

Item 352PEplusNo.34, 30th Oct.2003, p.3CLOSED CELL FOAM SUITABLE FOR HARSH ENVIRONMENTS

Zotek F 30, a closed cell foam of density 30kg.m3 made from Kynar PVDF with applications in aircraft insulation or in air conditioning ducts, is available from Zotefoams. It is also suited to applications such as high and low closure force seals in chemically harsh environments, unsinkable fl oats in chemical tanks and other situations where fl ame-retardant behaviour, chemical resistance or high purity are essential, it is briefl y reported.ZOTEFOAMS PLC

EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.900874

Item 353Applied Composite Materials10, No.4-5, July/Sept.2003, p.189-205AN HISTORIC OVERVIEW OF THE DEVELOPMENT OF FIBRE METAL LAMINATESVermeeren C A J RDelft,University of Technology

Fibre metal laminates are hybrid laminates consisting of thin alternating bonded layers of aluminium and fi bre/epoxy resin. A brief overview is presented of the history of the fi bre metal laminates Arall (aramid-reinforced aluminium laminates) and Glare (glass reinforced, from Akzo/Alcoa) to provide background information for the other technical articles in this journal. The history of Arall is discussed with reference to application of Arall in the wing structure of F-27, fuselage, ballistic Arall, space structure and tubes, and disadvantages. Glare laminates are then examined with emphasis on impact properties, burn-through properties, Glare in the fuselage, residual strength properties, repair with Glare, use of Glare at Airbus, other characteristic properties, laminates for high temperature applications and cost estimation of Glare parts. 8 refs.AKZO; ALCOA; AIRBUS

EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; WESTERN EUROPE

Accession no.899403

Item 354Modern Plastics International33, No.11, Nov.2003, p.41NEW RIGID-ROD POLYMER JUMPS TO MARKETMapleston P

First commercial samples of what is said to be the fi rst thermoplastic “rigid-rod” polymer should be available in November from start-up company Mississippi Polymer Technologies. The first grades of Parmax SRP (self-



reinforcing polymers) will be for compression moulding and extrusion, followed soon by injection moulding grades. MPT also anticipates applications in solvent-cast fi lms for electronics, structural foams, coatings for aerospace, defence, electronic and specialty industrial applications, and composites. The polymers are based on a substituted poly (1,4-phenylene). The rigid-rod backbone imparts strength and stiffness and the substituents allow melt processability and solvent casting.MISSISSIPPI POLYMER TECHNOLOGIES INC.

USA

Accession no.898697

Item 355International Journal of Adhesion and Adhesives23, No.5, 2003, p.343-8USE OF PERMAPOL P3.1 POLYMERS AND EPOXY RESINS IN THE FORMULATION OF AEROSPACE SEALANTSClark L J; Cosman M AAirbus UK; PPG Aerospace

The performance of polythioether polymers in aerospace sealant applications including oxidative and epoxy resin curing systems is reviewed. The characteristics of the epoxy-cured sealants are discussed in terms of glass transition temperatures (by thermal retraction, DMA, DSC and TMA), thermal stability (tensile strength at elevated temperatures), cure properties and adhesion, and compared with those for a manganese dioxide-cured polysulphide sealant. 3 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; USA; WESTERN EUROPE

Accession no.897438

Item 356Synthetic Metals135-136, 2003, p.23-4CONDUCTING POLYMER (CP) INFRARED ELECTROCHROMICS IN SPACECRAFT THERMAL CONTROL AND MILITARY APPLICATIONSChandrasekhar P; Zay B J; McQueeney T; Scara A; Ross D; Birur G C; Haapanen S; Kauder L; Swanson T; Douglas DAshwin-Ushas Corp.Inc.; Jet Propulsion Laboratory; US,NASA,Goddard Space Flight Center

The use of advanced conducting polymer far-infrared electrochromics in spacecraft and defence applications is described. Devices comprised a solid electrolyte sandwiched between two electrodes, each being composed of conducting polymer (aniline/diphenylamine copolymer)/gold/microporous membrane (poly(vinylidene fl uoride)), and their properties were characterised by emittance, solar absorptance, and specular and diffuse IR refl ectance. 4 refs.

USA

Accession no.896257

Item 357Paint and Coatings Industry19, No.9, Sept.2003, p.56/64PERFORMANCE OF DURABLE FLUOROPOLYMER COATINGSAsakawa AAsahi Glass Co.Ltd.

Fluoropolymer coatings are known as highly durable coatings that can maintain their initial performance for a long period. In the 1980s, Asahi Glass developed a copolymer of fl uoroethylene and vinyl ether as a solvent-soluble fl uoropolymer, known as FEVE. FEVE could be used on-site for applications such as heavy-duty architectural and aerospace coatings, as well as for oven-baked coatings. When these fl uoropolymer coatings were applied as protective coatings, they were used as a topcoat and protected under-layer basecoats and substrates from UV attack. FEVE coatings as bridge topcoats, on-line coatings and clearcoats are discussed. In recent years, waterborne fl uoropolymer coatings have been developed and their sales are increasing mainly in architectural applications. Waterborne FEVE has excellent weatherability and it can be blended with acrylic emulsions, making it possible to design coatings in which weather resistance and cost is between that of fl uoro- and acrylic polymers. 4 refs.JAPAN

Accession no.895770

Item 358Polymer44, No.17, 2003, p.4993MODELING PROPERTIES OF NYLON 6/CLAY NANOCOMPOSITES USING COMPOSITE THEORIESFornes T D; Paul D R Texas,University at Austin

The composite theories of Halpin-Tsai and Mori-Tanaka were used to show that the reinforcement of polyamide-6 by exfoliated aluminosilicates was superior to that provided by glass fi bre, attributed to the aluminosilicate’s high modulus, high aspect ratio, and the ability to provide reinforcement in two directions. Increasing the number of platelets per stack and the gallery spacing between platelets as a consequence of incomplete exfoliation dramatically decreased the reinforcing effect. The results were compared with experimental data for nanocomposites containing organically-modifi ed montmorillonite and glass fi bre. This required the development of an experimental procedure for the determination of aspect ratio. The stiffness behaviour predicted by the composite theories was in agreement with the experimental observations, and the experimental heat distortion temperatures were in reasonable agreement with those predicted by modelling



the dynamic mechanical properties. 56 refs.USA

Accession no.894474

Item 359Popular Plastics and Packaging48, No.7, July 2003, p.67-8BENEFITS OF PLASTICS IN SPACEGupta T K S PSant Longowal,Institute of Engineering & Technology

Plastics play a key role in space, with new plastics materials constantly being researched to survive the harsh environment of space. The strength-to-weight ratio, adaptable yet incredibly temperature-resistant, strong and durable nature of polymers has meant that space technologists have been able to develop vehicles, equipment and clothing that are able to withstand the extreme conditions outside the Earth’s atmosphere. Examples of the use of polymers in aerospace applications are given.INDIA

Accession no.892333

Item 360Composites Part A: Applied Science and Manufacturing34A, No.6, 2003, p.551-8VACUUM INJECTION MOULDING FOR LARGE STRUCTURAL APPLICATIONSBrouwer W D; van Herpt E C F C; Labordus MDelft,Centre of Lightweight Structures

This paper describes ways to improve reliability and predictability of the VARTM technology in order to decrease development cost and to make risk of failures during production as small as possible. First, appropriate methods to achieve void free processing of the composite material are described. Secondly, it is explained how the injection strategy can be optimised by using resin fl ow simulation software. Two examples of successful developments of large applications are described: a 20m rotor blade and a 16m long boat hull for a sailing yacht. 8 Refs.EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; WESTERN EUROPE

Accession no.891910

Item 361Engineering244, No.4, April 2003, p.53FLEXIBLE APPLICATIONWard J

A report is presented on the chance discovery by David Lussey of Peratech, while researching electrically-conductive adhesives for the defence industry, of a quantum tunnelling composite consisting of conductive

metal particles held apart by extremely thin layers of non-conductive polymer. The resistance of the composite is very high in the quiescent state but it is conductive after stretching or squeezing. Applications of the technology in switching, temperature sensors, chemical detection sensors, ski apparel and the automotive sector are mentioned.PERATECH LTD.


Accession no.891178

Item 362Eureka23, No.6, June 2003, p.40COMPOSITES WHISPER THEIR PROBLEMSShelley T

This article reports in detail on a new technique that will allow composites to be used more confi dently in safety-critical commercial aerospace applications. It involves detecting the tiny high-frequency sounds which arise at the very beginning of composite micro-damage, long before there any visible signs such as cracks, which only occur very shortly before complete failure.BRUNEL UNIVERSITY; BRITISH AIRWAYS; CORUS UK LTD.; ROLLS-ROYCE; UNILEVER RESEARCH; GLAXO SMITHKLINE; PROCESS ANALYSIS & AUTOMATION LTD.; UK,ROYAL AIRFORCE


Accession no.890979

Item 363163rd ACS Rubber Division Meeting - Spring 2003. Proceedings of a conference held San Francisco, Ca., 28th-30th April 2003.Akron, Oh., ACS Rubber Division, 2003, Paper 24, pp.32NEW FLUOROELASTOMER DEVELOPMENTS FOR AEROSPACE SEALING APPLICATIONSThomas EDupont Dow Elastomers(ACS,Rubber Div.)

A new range of peroxide curable specialty fl uoroelastomers, utilising Advanced Polymer Architecture technology, was reviewed to evaluate their compatibility with advanced gas turbine engine lubricants and reference fluids. Tests of sealing performance, including heat ageing resistance, retained elongation, volume swell and hardness change, were carried out in comparison with existing fl uoroelastomers and the results are discussed. 21 refs.USA

Accession no.889979

Item 364Pitture e Vernici79, No.6, 1st-15th April 2003, p.55-65



Italian; EnglishEPOXY ADHESIVES AND SEALANTSGrandi A

Adhesives have been one of the major application fi elds for epoxy resins since their introduction in 1946, and they have been formulated to be used for a wide range of applications: metal/metal, glass/glass, wood/wood bonding, printed media and structural welding. Main applications are found in fi eld of structural adhesives for metal bonding, especially in the aeronautical and aerospace industry, for military equipment, and also for small metal or plastic component assembly operations. To describe the technological versatility of adhesives based on epoxy systems, storage and application conditions, as well as the working temperature and the shear strength rate of various formulated products are presented. The data listed are obtained from a previous test by Carson. The range of properties versus the formulations proves the numerous structural applications of epoxy resins.EUROPEAN COMMUNITY; EUROPEAN UNION; ITALY; WESTERN EUROPE

Accession no.889282

Item 365Journal of Composite Materials37, No.8, 2003, p.687-700STRUCTURAL STABILITY OF COMPOSITE LAMINATED COLUMN EXPOSED TO HIGH TEMPERATURE OF FIREAnilturk D; Chan W STexas,University

With the increasing use of composite materials in applications of aerospace and civil structures, their safety and reliability under high temperature and fi re environments must be assured. A study of structural integrity of composite structures exposed to fire or intensive heat is presented. The parameters that affect their critical buckling loads and the buckling strengths under these circumstances are investigated. It is shown that for a given material, increasing the ply thickness will increase the buckling strength of the laminate. It is also concluded that a symmetric lay-up of laminate exhibits a higher buckling strength than the one of an unsymmetric lay-up. 20 refs.USA

Accession no.889275

Item 366Plastics Technology49, No.6, June 2003, p.37/41“SELF-REINFORCING” THERMOPLASTIC IS HARDER, STRONGER, STIFFER WITHOUT ADDED FIBERS

“Parmax SRP” (self-reinforcing polymer) is the sole product of US research and development company Mississippi Polymer Technologies Inc. It is a high-

performance readily-processable rigid-rod thermoplastic with a striking list of advantageous properties. This article provides full details of the new material, including its structure, properties, and potential applications, and also provides us with background information on its producer.

MISSISSIPPI POLYMER TECHNOLOGIES INC.; GE PLASTICS; US,DEPT.OF DEFENSEUSA

Accession no.888351

Item 367Polymer Preprints. Volume 43. Number 2. Fall 2002. Papers presented at the ACS Meeting held Boston, Ma., 18th-22nd Aug.2002.Washington, DC, ACS, Div.of Polymer Chemistry, 2002, p991-2SYNTHESIS AND CHARACTERIZATION OF LOW MELTING, OLIGOMERIC PHTHALONITRILE MONOMERS FOR AEROSPACE AND SHIP APPLICATIONSDominguez D D; Keller T MUS,Naval Research Laboratory(ACS,Div.of Polymer Chemistry)

In a continuing investigation of high temperature polymers with good thermal properties, a new class of low melting, oligomeric phthalonitrile monomers has been developed in which multiple aromatic ether linkages interconnect the terminal phthalonitrile units. These materials are designed to address the need for processable resin systems for composite fabrication below 150 deg.C. The new phthalonitriles complement the current phthalonitrile, 4,4’-bis(3,4-dicyanophenoxy)biphenyl, which is initially processed at temperatures between 250-300 deg.C. Synthesis of the oligomeric phthalonitrile monomers has been achieved in a novel one-pot, two-step reaction. The initial, key step of the reaction takes place under mild conditions and results in a high yield of a hydroxy-terminated oligomeric diarylether. The synthetic method, based on a general procedure for the formation of diaryl ethers from the reaction of aryl bromides or iodides with hydroxyaryl compounds, is a modifi cation of the traditional Ullman ether synthesis. The hydroxy-terminated diarylether is then reacted with 4-nitrophthalonitrile to obtain the oligomeric phthalonitrile monomer. In an extension of work on aromatic ether-containing phthalonitrile resins, a series of low melting, oligomeric phthalonitrile monomers with different chains lengths has been prepared and various curing additives have been used to affect polymerisation of these materials to thermosets. The synthesis, polymerisation and preliminary thermal analyses on the monomers and polymers are described. 8 refs.USA

Accession no.887913



Item 368High Performance PlasticsMay 2003, p.9/10MICROSCOPY TECHNIQUE AIDS NANOCOMPOSITE RESEARCH

By adapting the tiny cantilever and position measurement systems used in atomic force microscopy, researchers at the Georgia Institute of Technology are assisting NASA to shorten the process of selecting the right polymer to use in nanocomposites reinforced with carbon nanotubes, for aerospace applications. Full details are presented.GEORGIA,INSTITUTE OF TECHNOLOGY; NASA

USA

Accession no.886608

Item 369Adhesive Joints: Formation, Characteristics and Testing, vol.2.Utrecht, VSP BV, 2002, p.329-36, 25 cm, 6A1DURABILITY OF STRUCTURAL ADHESIVES AND THEIR BONDED JOINTS FOR HIGH SPEED AEROSPACE APPLICATIONSParvatareddy H; Shuangyang X; Dillard DDow Chemical Co.; Virginia,State UniversityEdited by: Mittal K L(VSP BV)

This study aims to evaluate the durability of structural adhesive joints for application in the proposed Mach 2.4 high speed civil transport aircraft. The criterion for selection is based on the bonded system exhibiting suffi cient durability for over 60,000 hours in service environment conditions. Ti-6A1-4V/FM-5 bonds and neat resin samples were aged at 177 deg.C and 204 deg.C in one of three different environments: atmospheric air, and reduced air pressures of 2 psi and 0.2 psi. The adhesive used in the study was a polyimide. The bonded specimens and neat adhesive fi lms were conditioned in ageing ovens for 24 months and selected samples were periodically removed and tested at ageing times which were logarithmically separated, in order to measure the critical strain energy release rate as a function of temperature and environment. 6 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; USA; WESTERN EUROPE

Accession no.885675

Item 370Journal of Composite Materials37, No.5, 2003, p.381-400THE BEHAVIOR OF COMPRESSIVELY LOADED STIFFENER RUNOUT SPECIMENS - PART I: EXPERIMENTSFalzon B G; Davies G A OLondon,Imperial College of Science,Technology & Medicine

The results are reported of an investigation into the failure

of thick-sectioned stiffener runout specimens for aircraft applications loaded in uniaxial compression. Tests were carried out on eight different specimen confi gurations. The specimens tested had different nominal skin thicknesses and were made from carbon fi bre reinforced plastics. Strain gauge results for the different specimens are presented and details of the failed specimens are illustrated. 12 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.885336

Item 371Advanced Materials and Composites News25, No.7, 7th April 2003, p.4-5AIRBUS THERMOPLASTIC APPLICATIONS - PRESENT AND FUTURETurner G F

Today’s Airbus primary and secondary structures utilise a signifi cant amount of advanced composites, although thermoplastic (TP) materials still play a rather minor role in aircraft structures. Airbus France successfully introduced TP ribs for the all-composite keel beam primary structure, in the process achieving a weight saving of 500kg versus the metal baseline version of this large and unique structure. Aileron ribs for the A340-600 were successfully developed and put into production by Airbus France using both glass and carbon fabric reinforced PPS composites. Other developing applications include TP auxiliary ribs for Airbus elevators, A380 wing slat components and A380 fuel tank access covers.AIRBUS DEUTSCHLAND GMBH


Accession no.885207

Item 372Reinforced Plastics47, No.4, April 2003, p.28-32BALANCING PROPERTIES FOR CORE SUCCESSSimpson K

Sandwiching a lightweight core material between skins of fi bre reinforced plastic can signifi cantly increase the stiffness of a laminate without adding much to its overall weight. The three main core types are foam, honeycomb and cellulose. The key to choosing the most appropriate core material is to fi nd the right compromise between performance and manufacturability. With many fabricators turning to closed moulding processes to reduce emissions and improve part quality, one of the latest developments in foam cores is the introduction of cores that are specially modifi ed to aid vacuum infusion. Some impressive new applications are in the pipeline for composite sandwich structures, including heavily loaded structures for Airbus’ latest aircraft. In the automotive sector, foam cores are currently being used in a project to develop technology



for the high volume manufacture of car, truck and trailer assemblies.WORLD

Accession no.885186

Item 373Journal of Materials Science Letters22, No.3, 1st Feb.2003, p.201-2STUDY OF THE INFLUENCE OF THERMAL SHOCK ON INTERFACIAL DAMAGE IN THERMOSETTING MATRIX ARAMID FIBRE COMPOSITESRay B CIndia,National Institute of Technology

A better fi bre/matrix adhesion/bond will impart better properties such as interlaminar shear strength, delamination resistance and corrosion resistance to a polymeric composite. The interface-sensitive properties are weaker in polyaramid-reinforced composites than in their glass or graphite counterparts. Aramid fi bre is a generic term for aromatic polyamide fi bres which have high specifi c strength, great cohesiveness and a tendency to form fi brils. They absorb much more energy than brittle fi bres and are widely used in aircraft, aerospace and ballistic applications. The interfacial adhesion between the aramid fi bre surface and the polymer matrix is of major infl uence on the response of the composite to stress. The fi bre/matrix interfacial behaviour is based on mechanical principles with the assumptions made at either the level of fi bre/matrix adhesion or using the chemistry approach. It is reasonable to assume that the interfacial shear strength is the net result of a number of contributions to the fi bre/polymer adhesion. These possibly include chemical bonding, secondary forces of attraction, residual thermal compression forces due to differential shrinkage and also mechanical interlocking between the fi bre and matrix. The unique chemistry and morphology of Kevlar aramid fi bre is also manifested in its composite behaviour. The high radial expansion coeffi cient of the Kevlar fi bre also causes an unfavourable tensile stress state at the interface. The weak interfacial adhesion of Kevlar/polymer makes the composite more sensitive to environmental exposure. This interfacial bonding is further weakened by exposure to active environments. The comparative mechanical behaviour of Kevlar/epoxy and Kevlar/polyester composites with thermal and cryogenic conditionings and combined effects of thermal shock is studied. These aerospace materials frequently experience this kind of severe environmental exposure during their service life. 6 refs.INDIA

Accession no.884615

Item 374Polymer Preprints. Volume 43. Number 2. Fall 2002. Papers presented at the ACS meeting held Boston, Ma., 18th-22nd Aug.2002.

Washington, D.C., ACS, Div.of Polymer Chemistry, 2002, p.783-4STABILITY OF A HYDROPHILIC POLYMER MATRIX IN A WET ENVIRONMENTHan S O; Han M H; Schalek R; Drzal L TKorea,Institute of Energy Research; Michigan,State University(ACS,DIV.OF POLYMER CHEMISTRY)

The use of biocomposites for automotive applications has gained a lot of momentum in recent years. Studies for the development of biocomposites using natural fibres are actively performing to widen applications to aerospace industries. One of the major reasons for the active growth on the research of biocomposites is an increased environmental awareness, refl ected in phrases such as ‘protection of resources’, ‘CO2 emission reduction’ and ‘recycling’. Biodegradable polymers could be incorporated into a classic polymer such as an epoxy or PP, or used by itself as the polymer matrix. Popular biodegradable polymers such as polylactic acid (PLA) and polyhydrosuccinate (PHS) contain a relatively high concentration of hydrophilic groups in their structure. The hydrophilic properties of the biodegradable polymers can provide better adhesion to natural fi bres compared to the classical hydrophobic polymers such as PP. This increased adhesion results in a higher performance of biocomposites. Unfortunately, the abundant hydrophilic functional groups of the biodegradable polymer and the natural fi bres can easily react to the water molecules in a wet or humid environment. High water absorption ability can significantly compromise the composite physical properties compared to synthetic polymers. Changes in physical properties include a decrease of the mechanical properties, microcracks, chain scission, degradation of fi bre and matrix interface bonding. These disadvantages are the main reason why biocomposites are mostly used in car interiors without an option for outside applications. The hydrophilic polymer matrix of an epoxy and a biodegradable polymer, glucose based copolymer, is prepared and characterised for the application of biocomposites. Stability of the hydrophilic polymer matrix in a wet environment is examined as a function of curing temperature. 9 refs.KOREA; USA

Accession no.884446

Item 375Materials Today6, No.4, April 2003, p.44-8ACTIVITIES IN BIOCOMPOSITESNickel J; Reidel UDLR German Aerospace Centre

The German Aerospace Centre (DLR) is developing, in addition to classic composites reinforced with carbon or glass, so-called “biocomposites” which are derived from renewable resources. Biocomposites have similar properties to traditional glass-fi bre composites, but offer



additional environmentally-friendly recovery options. This detailed article reports on the latest developments in the fi eld, and on new biocomposite applications. 14 refs.DEUTSCHE BAHN AG; LOWER SAXONY,MIN.OF FOOD,AGRICULTURE & FORESTRY; COGNIS DEUTSCHLAND GMBH

EU; EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.883348

Item 376Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.1168-79MECHANISM OF MARCEL FORMATION IN THICK TAPERED COMPOSITESNg S J; Vizzini AUS,Naval Air Warfare Center; Maryland,University(SAMPE)

Fibre distortions (marcels) or layer waviness is a signifi cant manufacturing defect found in thick, complex composite parts. Marcels can cause significant degradations in mechanical properties and fatigue life in primary structural aircraft applications, despite its formation mechanism remaining largely uncertain. The objective is to investigate the basic mechanism(s) which causes marcelling in thick linear tapered laminates. A fi bre optic based in-process measurements techniques is adapted to interrogate and determine the time and external compaction pressure at which marcelling occurs. The technique is generic and can be applied to any geometric or material type structure susceptible to marcelling. Combinations of semi-empirical cure kinetics and process model are also developed to describe the in-situ deformation behaviour of thick composite processing, and used for prediction of marcelling. The process model shows good correlation with the in-process measurement data. The model provides an indication of the location of marcel. The verifi ed process model results illustrate clear indication of out-of-plane deformation arising from tool/laminate interaction during material compaction as the basic mechanism which causes marcelling in two distinct regions in the tapered section of the composite structure for the test case condition. 3 refs.USA

Accession no.882840

Item 377Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.1086-97

DETECTION OF MOISTURE IN ADHESIVE BONDS USING ELECTROCHEMICAL IMPEDANCE SPECTROSCOPYDavis G DDACCO SCI Inc.(SAMPE)

The use of electrochemical impedance spectroscopy (EIS) sensors to track moisture intrusion into aluminium-aluminium bond lines is investigated. Lap shear and wedge test specimens are prepared using Forest Products Laboratory (FPL)-etched or phosphoric acid anodised (PAA) aluminium bonded with Cytec FM73 or FM300 adhesives. Pad sensors are mounted on opposite adherends after bonding (i.e. the sensor electrodes are not embedded in the bond line, but are applied to the pre-existing structure). The specimens are exposed to high humidity/temperature and EIS measurements are taken periodically. The EIS data are modelled with an equivalent circuit. The moisture uptake is calculated from the circuit capacitance. The capacitance and other circuit parameters are correlated with bond performance (pull strength or crack growth). Enhanced diffusion of moisture along the strained adhesive/FPL oxide interface is detected. The sensor system is sensitive to low levels of moisture absorption and gives advance warning of potential environmental degradation of the bond. It is thus suitable for input to a condition-based maintenance or predictive assessment scheme. Other work has shown that the sensor system is also suitable for graphite, glass and boron composite adherends. Possible applications include bonded repair patches and composite structures on aircraft. Possible dual-use applications include composite reinforcement of bridges and other infrastructure. 18 refs.USA

Accession no.882833

Item 378Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.949-58POLY(ETHER KETONE KETONE) MATRIX COMPOSITESPratte J F; Bai J M; Leach DCytec Engineered Materials Inc.(SAMPE)

Poly(ether-ketone-ketone) (PEKK) is a semi-crystalline polymer which offers an attractive balance of properties. With a glass-rubber transition temperature of 156 deg.C and a melting temperature of 300-310 deg.C, it provides easy processing with good performance for most commercial applications. This combined with its excellent fl uid resistance due to its semi-crystalline morphology and very low fl ammability make it an attractive option for a variety of aerospace and industrial uses. PEKK has been used for some time in aircraft interiors in the form of



unreinforced sheet. Composites have been developed in a variety of forms to meet specifi c application requirements. These include short and continuous fi bre composites with glass and carbon fibres. The continuous fibre forms include tape and fabric materials. Tape materials with carbon and fi bre reinforcement are evaluated for mechanical performance compared to current industry standard materials. Properties of interest include lamina properties, and service related tests such as open-hole tension and compressions, and compression after impact. Fabric-reinforced PEKK, including S-2 and E-glass fabrics are evaluated. An important aspect with glass composites is the glass-polymer interface and several different glass sizing are evaluated to provide the optimum interface in ‘dry’ and ‘hot-wet’ conditions. Properties evaluated include moisture uptake open-hole compression and glass-rubber transition temperature. 6 refs.USA

Accession no.882820

Item 379Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.772-80EFFECT OF PROJECTILE SHAPE DURING BALLISTIC IMPACT OF VARTM CARBON/ EPOXY COMPOSITE PLATESUlven C; Vaidya U K; Hosur M VAlabama,University at Birmingham; Tuskegee,University(SAMPE)

The use of carbon/epoxy composites in aircraft, marine and automotive structural applications is steadily increasing. Robust composite structures processed using low-cost techniques with the purpose of sustaining high velocity impact loads from various threats are of great interest. An example of a low-cost process is the out-of-autoclave, vacuum-assisted resin transfer moulding (VARTM) technique. The perforation and damage evolution created by various projectile geometries in carbon/epoxy laminates are evaluated. The laminates are produced from eight-harness satin weave carbon fabric with an epoxy matrix processed using VARTM. A series of ballistic impact tests is performed on satin weave carbon/epoxy laminates of different thickness with projectile geometries representing hemispherical, conical, fragment simulating and fl at tip. A gas-gun with a sabot stripper mechanism is employed to impact the samples with 50-calibre projectiles. The perforation mechanism, ballistic limit and damage evolution of each laminate are studied. 16 refs.USA

Accession no.882804

Item 380Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.531-45LOW COST CARBON FIBER FROM CHEMICALLY MODIFIED ACRYLICSDasarathy H; Schimpf C; Burleson T; Smith S B; Herren C W; Frame A C; Heatherly P WHexcel Composites; Advanced Fiber Technologies Inc.(SAMPE)

For over three decades, carbon fi bre (CF) manufacturers worldwide have been producing high performance CF from polyacrylonitrile (PAN) precursor fi bres for aerospace and other industrial applications. The Department of Energy (DOE), in order to reduce energy consumption in cars, funded research activities to replace metals with lightweight materials such as CF composites. Research groups in industry and academia were challenged to provide a technology road map for producing CF with tensile properties of 2760 MPa (400 ksi) strength, 172 GPa (25 Msi) modulus and a minimum 1% strain to failure at less than 11 US dollars/kg. Until now, commercial textile acrylics were not considered suitable for CF manufacturing due to poor carbon fi bre processing characteristics, technical challenges to achieve desired mechanical properties and high cost associated with the conversion process. The results of work performed by Hexcel, Carbon Fibers R&T, aimed at determining whether these shortcomings could be overcome by chemical modifi cation of textile acrylics, are presented. Results show that the chemical modifi cation of the textile acrylics in the spinning process changes the fi bre chemistry, accelerates the stabilisation step and improves CF properties. The properties of CF processed from the modifi ed textile acrylic fi bre exceed the programme targets for low cost carbon fi bre. 8 refs.USA

Accession no.882783

Item 381Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.377-88POLYIMIDES CONTAINING PENDENT PHOSPHINE OXIDE GROUPS FOR SPACE APPLICATIONSThompson C M; Smith J G; Watson K A; Connell J WUS,NASA Langley Research Center(SAMPE)

As part of an ongoing materials development activity to produce high performance polymers durable to the space environment, phosphine oxide containing polyimides have been under investigation. A novel dianhydride is prepared from 2,5-dihydroxyphenyldiphenylphosphine oxide in



good yield. The dianhydride reacts with commercially available diamines, and a previously reported diamine reacts with commercially available dianhydrides to prepare isomeric polyimides. The physical and mechanical properties, particularly thermal and optical properties, of the polymers are determined. One material exhibits a high glass transition temperature, high tensile properties and low solar absorptivity. The chemistry, physical and mechanical properties of these resins are discussed. 14 refs.USA

Accession no.882770

Item 382Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.365-76CARBON NANOTUBE/SPACE DURABLE POLYMER NANOCOMPOSITE FILMS FOR ELECTROSTATIC CHARGE DISSIPATIONSmith J G; Watson K A; Thompson C M; Connell J WUS,NASA Langley Research Center(SAMPE)

Low solar absorptivity, space environmentally stable polymeric materials possessing sufficient electrical conductivity for electrostatic charge dissipation (ESD) are of interest for potential applications on spacecraft as thin fi lm membranes on antennas, solar sails, large lightweight space optics and second surface mirrors. One method of imparting electrical conductivity while maintaining low solar absorptivity is through the use of single wall carbon nanotubes (SWNTs). However, SWNTs are difficult to disperse. Several preparative methods are employed to disperse SWNTs into the polymer matrix. Several examples possess electrical conductivity suffi cient for ESD. The chemistry, physical and mechanical properties of the nanocomposite fi lms are presented. 9 refs.USA

Accession no.882769

Item 383Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.358-64STUDY ON REGOLITH MATERIAL FOR STRUCTURAL AND SPACE RADIATION SHIELDING APPLICATIONSZhou J; Moore J; Huff H; Ardlan S; Wilkins R; Fogauty T; Zhong YUS,NASA,Applied Radiation Research Center(SAMPE)

Convenient in-situ materials are used to construct bulk

shields for human inhabitant and electronic devices on Mars in order to avoid excessive launch weight. Martian regolith is considered to be an economic resource for this purpose. The objective is to study the radiation shielding effectiveness and radiation effects on properties of this potential habitat material. Polyimide bonded Martian regolith is exposed to 55 MeV proton, 800 MeV proton, and high-energy neutron radiation. The radiation fl uence shielded by the regolith panels is measured in the 55 MeV proton radiation tests with an incident fl uence of 1 x 10 6 pronton/sq.cm. The results show that the material containing 60% regolith with a thickness of 1.89 g/sq.cm can shield 19% of the fl uence while the one containing 80% regolith with a thickness of 2.01 g/sq.cm reaches an effectiveness of 33%. In neutron exposures, electronic chips are placed behind regolith panels and the numbers of errors that occur on the electronic circuits are recorded to characterise the shielding effectiveness. A slightly increase in the numbers of errors in the electronic chips is noticed when the regolith panels, either with 60% or 80% regolith, are used. It indicates that although the regolith materials with thickness about 2 g/sq.cm are not adequate in protecting chips from neutron radiation, it does not cause a strong secondary radiation. Compression testing and thermal analysis are performed on the regolith materials before and after each type of radiation exposures. No noticeable compression strength deterioration and glass transition temperature changes are found, but the sample containing 60% regolith shows some drop in modulus after high-energy exposures. 6 refs.USA

Accession no.882768

Item 384Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.323-32DURABILITY OF SOLAR SELECTIVE COATINGS IN A SIMULATED SPACE ENVIRONMENTJaworske D AUS,Nasa,Glenn Research Center(SAMPE)

Solar selective coatings are being considered for heat engine and thermal switching applications on minisatellites. Such coatings must have the combined properties of high solar absorptance and low infrared emittance. High solar absorptance is needed to collect solar energy as effi ciently as possible while low infrared emittance is needed to minimise radiant energy loss at operating temperature. These properties are achieved in sputter deposited thin fi lms through the use of molecular mixtures of metal and dielectric. Solar selective coatings having a solar absorptance to infrared emittance ratio of 9 are successfully deposited using a mixture of nickel



and aluminium oxide. The space environment, however, presents some challenges for the use of materials on the exterior of spacecraft, including durability to atomic oxygen and vacuum UV radiation. To address these concerns, several candidate solar selective coatings are exposed to atomic oxygen in a plasma asher and to UV radiation in a vacuum facility equipped with calibrated deuterium lamps. The optical properties of the coatings are monitored as a function of time to evaluate their performance over long-term exposure to the simulated space environment. Several coatings are found to be durable to both the atomic oxygen and the vacuum UV environments. 4 refs.USA

Accession no.882765

Item 385Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.308-22DEVELOPMENT OF HIGH TEMPERATURE COMPOSITE SOLAR ARRAY SUBSTRATE PANELS FOR THE MESSENGER SPACECRAFTWienhold P D; Persons D FJohns Hopkins University(SAMPE)

The MESSENGER (Mercury Surface, Space, ENvironment, GEochemistry and Ranging) spacecraft will be the fi rst spacecraft to orbit the planet Mercury. Designed and built by the Johns Hopkins University’s Applied Physics Laboratory (APL), the spacecraft will orbit the planet for one year. In order to reduce cost and schedule of this NASA Discovery Mission, the solar arrays were required to be constructed of conventional, space-qualifi ed materials. System thermal, mass and stiffness requirements dictated that the panel facings be fabricated from a high thermal conductivity and stiffness pitch fi bre composite material capable of withstanding short-term temperatures as high as 270 deg.C. A toughened, 177 deg.C curing cyanate ester composite material resin system with extensive fl ight heritage was chosen, with a post-cure used to extend the glass transition temperature closer to the maximum predicted temperature. A lengthy development program was conducted at APL to provide assurance that the materials and processes chosen were capable of performing under such a demanding thermal environment. The results of this program will be applicable to other high temperature spacecraft applications of advanced pitch fi bre cyanate ester composite structures. 3 refs.USA

Accession no.882764

Item 386Materials and Processing - Ideas to Reality. Vol. 34.

Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.222-35AUTOMATED RTM OF A MULTI-COMPONENT RESIN SYSTEM - A PARAMETRIC EVALUATIONGraf N A; Joyce P JUS,Naval Air Systems Command; US,Naval Academy(SAMPE)

The Polymers and Composites Branch of the Naval Air Systems Command (NAVAIR) has teamed with fellow Navy, university and industry partners to demonstrate the viability of resin transfer moulding (RTM) for the manufacture of primary structural components for naval aviation applications. One objective of this research includes the design, demonstration and evaluation of an intelligent, supervisory, computer controlled RTM process. A second objective involves the selection and characterisation of candidate materials, with a focus on two-part resin systems with textile reinforcement. The goal is to evaluate the feasibility and process error tolerance of this intelligent RTM process applied to two candidate resin systems. A study is performed to examine the effects of major process parameters including variations in the resin component mix ratio, injection temperature, cure cycle modifi cations and ‘aeration’. This involves fl at panel fabrication and a wide array of testing including physical evaluation, thermal analysis and mechanical testing. The results of this parametric study and the associated recommendations regarding intelligent RTM with the candidate material systems are discussed. 10 refs.USA

Accession no.882757

Item 387Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.12-26RAIN DURABILITY EVALUATION OF HIGH SPEED COMPOSITE RADOMESWillardson R P; Kennedy C F; Meeker BRaytheon Electron Systems; Cambridge,University; US,Naval Air Warfare Center Weapons Div.(SAMPE)

A method to evaluate high-speed composite radomes for rain durability is discussed. A general background discussion of rain damage (or erosion) on aerospace components, particularly composite material components is given. Emphasis is placed on the need for rain durability on several current high-speed missile applications. A statistical method for determining rain fi eld environments for a given geometry is presented. A liquid impact damage theory, along with a number of liquid-impact test methods and their advantages and disadvantages, is presented. The water jet test method is discussed in depth and a method



for determining water jet testing parameters for missile radome geometry is outlined. Finally, water jet test results are presented for a composite laminate and two laminate coating systems. 30 refs.USA

Accession no.882741

Item 388Materials and Processing - Ideas to Reality. Vol. 34. Proceedings of the 34th International SAMPE technical conference held Baltimore, Md., 4th-7th Nov.2002.Carina, Ca., SAMPE International Business Offi ce, 2002, p.1-11EVOLVING NATURE OF AEROSPACE COMPOSITESGriffi th J M(SAMPE)

Organic or polymer matrix composites (OMC or PMC) entered aerospace production applications and use during the 1950s for areas with electrical requirements such as radomes using fi breglass reinforcements. PMC usage expanded in the 1960s and 1970s, fi rst with boron and then with carbon reinforcements. Polymer chemistries also improved to be able to handle higher operational temperature requirements during this time period too. The 1980s saw a signifi cant increase in PMC usage to meet performance requirements primarily for weight and special structures. The 1990s showed an increased emphasis on trades of acquisition cost to performance with an associated reduction of composites usage on military airframes. Also during the 1990s, there was an increase of composites usage on helicopters for weight reductions. Future trends of composites are examined. A parallel of the evolving nature of composites to the evolution of metals in aerospace applications is presented.USA

Accession no.882740

Item 389Popular Plastics and Packaging48, No.2, Feb.2003, p.61/82ELECTRICALLY CONDUCTING POLYMERSPillai C K SThiruvananthapuram,Regional Research Laboratory

This comprehensive article discusses electrically conducting polymers, including their initial discovery. Structural features of conjugated polymers, band theory, doping of organic conjugated polymers, general methods of preparation of conducting polymers and attempts to improve the processability of conducting polymers are discussed. The synthesis of polyaniline is examined in some detail. Finally, applications of conducting plastics are outlined. 107 refs.INDIA

Accession no.881612

Item 390SAMPE Journal38, No.6, Nov.-Dec.2002, p.33-45EMERGING MATERIALS FOR REVOLUTIONARY AEROSPACE VEHICLE STRUCTURES AND PROPULSION SYSTEMSHarris C E; Shuart M J; Gray H RUS,NASA,Langley Research Center

A comprehensive survey is presented of emerging materials with applications to aerospace vehicle structures and propulsion systems aimed at assisting NASA’s long-term mission planning and providing an appropriate research investment strategy. Materials already under development that could be available in 5 to 10 years and those that are in the early research phase and may not be available for another 20 to 30 years are identifi ed and the results of several systems analysis studies, which highlight the potential of carbon nanotubes are presented. 46 refs.USA

Accession no.880182

Item 391SAMPE Journal39, No.1, Jan.-Feb.2003, p.38-43MODULAR TOOLING FOR AFFORDABLE RTMDavenport DAdvanced Technical Products Inc.

The challenge facing the resin transfer moulding (RTM) industry to develop affordable RTM tooling for aerospace and defence applications is addressed and the development of a new approach, called Modular Tooling, which offers the potential to dramatically reduce non-recurring tooling costs of production by enabling multiple parts to be moulded from a single mould is reported. The applicability of this new approach, which has been employed to make helicopter fuselage sections for the AH64 Apache Longbow Helicopter, to other RTM affordability challenges is also considered.USA

Accession no.880133

Item 392RP Asia 2002: Composites in the global market. Proceedings of a conference held Kuala Lumpur, Malaysia, 5th-6th Sept.2002.Oxford, Elsevier Science Ltd., 2002, Paper 8, p.167-74USE OF ARALDITE ADHESIVES TO BOND COMPOSITE MATERIALSBieniak DVantico Pty.Ltd.(Elsevier Science Ltd.)

The Adhesives and Tooling Division of Vantico Pty. Limited is an innovative developer and manufacturer of high quality Araldite, Epibond and Epocast epoxy resins systems, many of which are specifi cally used as adhesives,



and also the Uralane PU adhesive systems. These adhesives can be used to bond a wide variety of substrates including composite materials which are being used widely in a variety of applications, some of which are discussed in this paper.AUSTRALIA

Accession no.879306

Item 393RP Asia 2002: Composites in the global market. Proceedings of a conference held Kuala Lumpur, Malaysia, 5th-6th Sept.2002.Oxford, Elsevier Science Ltd., 2002, Paper 7, p.150-66USE OF PMI-FOAMS IN DEMANDING SANDWICH STRUCTURESSeibert H FRohm GmbH(Elsevier Science Ltd.)

The paper introduces the properties of a family of already very well established rigid sandwich foam cores based on polymethacrylimide (PMI). It will be shown that PMI is widely used as core material for demanding sandwich structures in many fi elds of application, for example, air- and spacecraft, railway rolling stock and ships. Typical applications will be discussed to characterise the performance of these particular foam plastics and to show that they signifi cantly contribute to weight and cost savings. Most recently, a new PMI grade has been launched which will also be discussed.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.879305

Item 394Structural Health Monitoring1, No.2, Oct.2002, p.161-84STRUCTURAL INTEGRITY MONITORING OF BONDED COMPOSITE PATCH REPAIRS OF AGING AIRFRAMES USING WAVELET TRANSFORMSAmaravadi K; Rao V; Derriso MMissouri-Rolla,University

In recent years there has been a considerable interest in the design and application of bonded composite repairs to restore cracked or corroded metallic airframes. The long-term durability in terms of disbond of composite patch, fracture at the bond-lines, delaminations in composite patches and structural crack growth is to be thoroughly investigated before the aerospace industry adopts composite repair technology. Many have investigated the use of structural modal response (natural frequencies and mode shapes) for assessing the integrity of structural systems. Although these methods have been successfully employed in some practical systems, there still exist some problems for applications in bonded repair systems such as the high sensitivity of these systems to model and

measurement errors. Wavelet maps and neural networks are used to detect and quantify damage in composite bonded repair systems. Two algorithms are presented, one for the location of damage in both single and multiple locations and the other for quantifying the damage. The developed algorithms are successfully utilised for detecting and quantifying damage in bonded repair systems using simulation and experimental results. These methods can also be used to detect damage at multiple locations in a bonded repair system. The mode shapes of the test structure are obtained analytically using linear elastic fi nite element analysis and experimentally with a laser vibrometer. The results obtained are satisfactory. 31 refs.USA

Accession no.878219

Item 395High Performance Polymers14, No.3, Sept.2002, p.293-308CYANATE ESTER COMPOSITES CO-CURED WITH A SILICON-BASED THERMAL PROTECTION SYSTEMGanguli S; Dean D; Aglan H; Jordan KTuskegee,University; Raytheon Systems Co.

Cyanate esters (CE) have emerged as attractive materials for aerospace applications, due to their ease of processing and excellent high-temperature properties. Using a thermal protection system can increase the service temperature even further. The objective is to develop a co-cure cycle for a cyanate ester/silicon polymer (SM8000) hybrid composite system. The chemorheology and cure kinetics of the CE along with the thermochemical behaviour of the SM8000 resin are used to develop a co-cure cycle. Samples prepared by this cure cycle exhibit 270 deg.C increase in the onset of thermal decomposition. Interfacial fracture toughness tests reveal a very robust interface, validating the cure cycle. 20 refs.USA

Accession no.877792

Item 396ACS Polymeric Materials: Science and Engineering. Spring Meeting. Volume 84. Proceedings of a conference held San Diego, Ca., 1st-5th April 2001.Washington, D.C., ACS, Div.of Polymeric Materials Science & Engng., 2001, Paper 401, p.742-3SYNTHESIS AND CHAIN-END FUNCTIONALIZATION OF A NEW HYPERBRANCHED POLY(ARYLENE-ETHER-KETONE-IMIDE)Baek J-B; Mather P T; Tan L-SDayton,University; Connecticut,University; US,Air Force Research Laboratory(ACS,Div.of Polymeric Materials Science & Engng.)

Aromatic polyimides (PIs) are well known, high-performance materials with widespread applications



in the aerospace and electronics industries due to their excellent thermomechanical and dielectric properties. It was recently demonstrated that they are useful as optical materials based on their optical anisotropy when cast in directions parallel (in-plane) and perpendicular (out-of-plane) to the fi lm surface. However, when fully imidised, most aromatic PIs have limited solubility in common organic solvents, thus restricting the choice in their processing options. Numerous research efforts have been focused on organo-soluble PIs from the modifi cation of the structure without substantially decreasing rigidity of their backbone. Solubility is sought to allow processing polymers with preformed imide units and, many problems associated with handling polyamic acid (PAA) precursors can be avoided. In addition, homogeneous, post-polymer reactions of soluble aromatic polyimides would also allow better control in the introduction of desirable functional groups. Another viable alternative to attaining solubility in aromatic PIs is to change the traditional, linear geometry of the macromolecules to 3D, highly branched (dendritic) architecture. As a subset of dendritic polymers, hyperbranched polymers have several important advantages such as better solubility compare to their linear counterparts, and easier synthesis than their analogous dendrimers, which involve tedious multi-step synthesis. Large quantity of hyperbranched polymers can be easily produced from ABx (x = or is greater than 2) monomers. The objective of this research is to synthesise self-polymerisable AB2 monomer and functionalise the resulting hyperbranched polyether-ketone-imide with reactive chain ends. Such reactive hyperbranched polymers may be useful as toughening additives for high-temperature thermosets. 13 refs.USA

Accession no.877485

Item 397Design EngineeringDec.2002-Jan.2003, p.31-2COMPOSITE FUTUREBishop GNetComposites Ltd.

Thermoset composites still take the lion’s share of the composites market and these are used in all areas of application. However, thermoplastic composites are experiencing a growth rate approximately twice that of thermosets, especially in Europe, with the automotive industry acting as the major pull due to the twin drivers of recyclability and weight. In the fi bres market, carbon fi bre is forecast to exhibit the highest growth, especially in lower performance applications, and there is also an increased trend to natural fi bres due to their perceived lower environmental impact. In manufacturing, there is a clear trend towards the uptake of higher-skill, more capital intensive processes such as resin infusion and resin transfer moulding.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN

EUROPE

Accession no.876286

Item 398High-Performance Composites10, No.6, Nov.2002, p.7-19HIGH-PERFORMANCE COMPOSITES: AN OVERVIEW

This article provides a brief technical introduction to the composites industry, reviewing the various types and combinations of composite materials and the forms in which they are used. Design considerations and tooling options, a complete discussion of manufacturing methods and market applications are also covered.WORLD

Accession no.874698

Item 399Shawbury, Rapra Technology Ltd., 2002, pp.144, 29 cm, Rapra Review Report 152, vol.13, No.8, 2002. NALOANNATURAL AND WOOD FIBRE REINFORCEMENT IN POLYMERSBledzki A K; Sperber V E; Faruk OKassel,UniversitatEdited by: Humphreys S(Rapra Technology Ltd.)Rapra.Review Report No.152

The use of natural and wood fi bre reinforcements in polymers is reviewed with respect to types, properties, surface treatment of fibres, processing, properties of composites, and applications. End-use applications examined, include the automotive industry, building industry, furniture and panels and aerospace applications. Some statistics are included for the consumption of natural fi bres in Europe by the automotive industry 1996-2010. 485 refs.NORTH AMERICA; WESTERN EUROPE

Accession no.874532

Item 400HPE 2002. Proceedings of a conference held Cologne, Germany, 13th-14th Nov.2002.Shawbury, Rapra Technology Ltd., 2002, Paper 14, p.139-50LIQUID PERFLUOROETHER ELASTOMERUritani P; Kishita HShin-Etsu Chemical Co.Ltd.(Rapra Technology Ltd.; European Rubber Journal)

Liquid perfluoroether elastomers are discussed with reference to chemical structure (perfluoropolyether backbone with vinyl silicone end-caps at each end), crosslinking mechanism, low temperature properties, curing conditions, chemical resistance, strength retention at high temperature, electrical properties, permeability and



silylation treatment for improvement of compression set. The properties are considered in relation to the potential use of these elastomers in applications such as O-rings, diaphragms and semiconductors. 2 refs.USA

Accession no.873301

Item 401Materie Plastiche ed Elastomeri66, No.10, Oct.2001, p.662/72ItalianPLASTICS FROM DEEP SPACEZargani C

Space applications of plastics are examined, and some ways in which the transfer of space technology is contributing to developments in everyday applications of plastics are discussed.EUROPEAN SPACE AGENCY


Accession no.872613

Item 402Injection Molding10, No.12, Nov.2002, p.66-9SINTERING: A CRITICAL STEPGerman RPenn State University

Powder injection moulding (PIM) takes advantage of the fl uid-like behaviour of a heated powder-polymer feedstock to form complex shapes. It can be performed with wax-like polymers and any sinterable alloy, ceramic or inorganic powder. After mould fi lling, the polymer is solidifi ed to hold the mould shape, but the powder polymer mixture has little strength beyond that required for injection. Subsequently, the polymer (binder) is removed using heat, solvents or catalysts and the powder is sintered to nearly full density. Sintering is a heat treatment that is applied to the powders to strengthen and densify the particles. The sintering process has been known for thousands of years, and is today employed in a diverse range of products that includes dental implants, automotive valve seats, rocket nozzles, aircraft wing weights, ultrasonic transducers, ceramic turbochargers and golf clubs. Many of the modern applications are justifi ed by factors such as manufacturing economy, improved properties and novel compositions. Details are given.USA

Accession no.871791

Item 403Popular Plastics and Packaging47, No.11, Nov.2002, p.67-72SELF-HEALING PLASTICSSingh B; Mhaske S; Mehta N; Tamboli S

Mumbai,University

Structural polymeric composites are susceptible to cracks which may develop deep within the structure. It is very diffi cult to determine or observe cracks or damages in composites used in crucial applications such as infrastructure and aerospace. It is, therefore, essential to design smart materials that can repair themselves while in service. Autonomic healing does not require any mechanical intervention. Healing of cracks in structural polymers is accomplished by incorporating a healing agent and a catalytic chemical trigger in the polymer matrix. When the material cracks, the microcapsules rupture and release the healing agent into the damaged region by means of capillary action. As the healing agent comes into contact with the embedded catalyst, polymerisation is initiated, which then bonds the crack face. The self-healing process, method of microcapsule preparation and confi rmation of self-healing are discussed. 5 refs.INDIA

Accession no.871697

Item 404Journal of Applied Polymer Science86, No.5, 31st Oct.2002, p.1149-56EVALUATIONS OF AN ARAMID FIBER IN NONWOVEN PROCESSES FOR HONEYCOMB APPLICATIONSWu Y-J; Seferis J C; Lorentz VWashington,University; Rhodia Kermel Co.

Details are given of the relationships between material requirements in making a honeycomb core material for aircraft interior applications using an aromatic polyamide. The characterisation and processing of a model aramid fi bre into nonwoven samples were investigated. Data from thermal analysis, microscopy and mechanical analysis are presented. 21 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; USA; WESTERN EUROPE

Accession no.868298

Item 405Chemical and Engineering News80, No.39, 30th Sept.2002, p.15-6RENAISSANCE IN FLUOROELASTOMERSTullo A H

The largest applications for fl uoroelastomers are O-rings, gaskets, seals and hoses found in automotive or aircraft fuel lines. This is because they can withstand acids, bases, oil, solvents and other chemicals at temperatures ranging from -30 to 250C. DuPont Dow Elastomers puts the value of the global market at 450m US dollars in 2002, with growth of 3-5%/year. Both DuPont Dow and Ausimont have new product lines that they say make fl uoroelastomers easier to work with. In July, DuPont Dow fi nished a new unit in Dordrecht, the Netherlands, dedicated to fl uoroelastomers that incorporate its new advanced polymer architecture



technology. Also in July, Ausimont started up a plant at its complex in Thorofare, N.J., to make its new Tecnofl on HS line of fl uoroelastomers.WORLD

Accession no.868279

Item 406Reinforced Plastics46, No.10, Oct.2002, p.24-8PREPREGS - RAW MATERIAL FOR HIGH-PERFORMANCE COMPOSITESMarsh G

Prepregs have become accepted where performance, material qualification and product consistency are paramount requirements. Prepregs can be manufactured by the solvent impregnation and hot-melt impregnation methods. Prepregs would fi nd greater market acceptance if the costs of acquiring, storing and processing them could be reduced. A major contribution to this would be to reduce cure temperature. Hexcel chemists have moved in this direction with M21, a tough third-generation epoxy matrix that has the mechanical properties required for demanding aerospace applications, but can be cured at 130C rather than the more usual 180C. Another noteworthy development is the growing availability of thermoplastic prepregs. Attracting much attention currently is the extension of the “semi-preg” approach. These new material systems have sheets of pre-catalysed resin fi lm interleaved into dry fi bre fabric stacks so that when heat is applied, resin permeates the fi bres laterally and cure takes place.WORLD

Accession no.868223

Item 407Composites InternationalNo.53, Sept.-Oct.2002, p.89English; FrenchRP46: NEW THERMOSET RESIN SYSTEM

Originally seen as a safe alternative to existing prepregged polyimides in the aerospace industry, RP46 from Unitech now sees utilisation across a broad spectrum of applications subject to extreme operating conditions. In composite form, RP46 has a continuous operating temperature of 700C. Powder versions are available for compression moulding into virtually indestructible bearings, slip-rings or races. A more recent development has resulted in the formulation of a coating version that is the core of a super-strong, high-temperature adhesive, it is briefl y reported.UNITECH LLC

USA

Accession no.868142

Item 408Reinforced Plastics46, No.9, Sept.2002, p.20

RESEARCH INTO REDUCING MICROCRACKS

Technical researchers at the Aerospace Engineering Department’s Structures and Materials Laboratory of Delft University of Technology (DUT) have conducted innovative research with thermoplastic composites. The results indicate some promising behaviour in terms of greatly reducing or eliminating microcracking in continuously-reinforced carbon fi bre/PPS laminates by using rubber forming and special heating techniques. Aerospace engineer Bert Weteringe and colleagues Harald Bersee and Adriaan Beukers performed their experiments over the past two years with carbon/PPS laminate (made with Ticona FORTON 0214C PPS resin) trademarked as Cetex and supplied by Ten Cate Advanced Composites in The Netherlands. Weteringe says a key advantage of working with the Ten Cate material is that it was especially developed for aeronautical applications, with excellent mechanical properties and resistance to Skydrol, and so is certifi ed as such by various aircraft original equipment manufacturers. Five harness carbon fabric was used, with a fi bre volume fraction in the laminate of 49.2%. The researchers intend to study different types of infrared heaters in their next level of research into thermoplastic composites, and determine a non-destructive test method in order to more accurately and fully detect microcracks. Details are given.DELFT,UNIVERSITY OF TECHNOLOGY


Accession no.867412

Item 409Polymer43, No.19, 2002, p.5209-18MOISTURE ABSORPTION BY CYANATE ESTER MODIFIED EPOXY RESIN MATRICES. PART I. EFFECT OF SPIKING PARAMETERSKarad S K; Jones F R; Attwood DMaharashtra Institute of Technology; Sheffi eld,University; BAE Systems

The moisture absorption of cyanate ester modifi ed epoxy resin matrices has been studied under thermal spiking conditions. The relationships were evaluated between material behaviour and variables such as maximum and minimum temperatures during a thermal spike, the duration of the spike, dry spiking and number of spikes. Improved moisture absorption was observed at spike-temperatures above 120 degree C. In desorption studies it was found that some of the water molecules remained entrained in the polymer. Regular and intermittently applied thermal spikes during moisture conditioning caused enhanced absorption of the cyanate ester modifi ed epoxy resins. A maximum moisture enhancement spike-temperature exists for the resin. The spiking of the samples above or below this temperature resulted in lower moisture content. The amount of the entrained water increased with a spiking-temperature. Part of that was constant over a wide-range



of conditions and may be attributable to hydrogen bonded water of to the reaction with isolated cyanate ester groups. On isothermal resorption, the moisture concentration was found to be similar to that achieved through thermal spiking, showing that the entrained water at the lower spike-temperatures can also be achieved under mild conditions. These matrices are useful for aerospace applications. 23 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; INDIA; UK; WESTERN EUROPE

Accession no.866532

Item 410Composites Part A: Applied Science and Manufacturing33A, No.7, 2002, p.913-34SELECTION OF COMPOSITE MATERIALS AND MANUFACTURING ROUTES FOR COST-EFFECTIVE PERFORMANCEBader M GSurrey,University

A study was conducted with the aim of estimating the costs of manufacture of a simple component in a number of different composite materials and by different manufacturing routes. The materials and routes selected covered the range of composites from those appropriate for general engineering applications to those for aerospace applications. A simple methodology was introduced for a comparison on the basis of cost-performance effi ciency. It was shown that more economic solutions could often be realised by selection of ‘expensive’ carbon rather than ‘cheaper’ E-glass as the reinforcing fi bre. Non-prepreg and non-autoclave processes were shown to offer many cost and production advantages, but sometimes at the expense of poorer mechanical properties. 8 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.865934

Item 411Advanced Materials and Processes160, No.6, June 2002, p.19-20NANOCOMPOSITE DENSE PLASTIC FOAM REPLACES SOLID PLASTIC

It is briefly reported that researchers at Ohio State University claim to have developed nanocomposite plastic foam that is strong enough to replace solid plastic in structural applications such as car or airplane panels. To make foam, manufacturers inject gases into hot liquid plastic. The Ohio State researchers added nanometre-size clay particles to the molten plastic, and small bubbles of the injected gas about fi ve microns across formed around the nanoparticles, adhering to them. With a foam that contains 5% clay particles, boards were made that are just as strong as typical foam, but two thirds as thick.

OHIO,STATE UNIVERSITY

USA

Accession no.864095

Item 412Tech XXV. 25 Years of Tape Innovations. Proceedings of a conference held Atlanta, Ga., 1st-3rd May 2002.Northbrook, IL., 2002, Paper 24, p.313-22BOEING PAINT HANGAR PRESSURE SENSITIVE TAPE APPLICATIONSUngerecht C; Andrews S MBoeing Commercial Airplane Group(Pressure Sensitive Tape Council)

Masking tape is a critical component of the painting process for commercial aircraft. The tape must adhere to several different substrates, remove cleanly, and provide a sharp paint line. The tape must withstand, exposures to solvent, water, abrasives, and multiple 120 deg.F heat cure cycles. The tape may remain on the airplane for several days before removal. The performance of the tape must be consistent and predictable. The cost and schedule impact when the masking tape fails is signifi cant on commercial aircraft. Variation during manufacture of the tape can change the expected performance causing adhesive residue, diffi culty applying or removing the tape, poor paint lines, and ultimately rework and delays. Rework and delay costs easily ran into thousands of dollars per day. For this reason, Boeing performs several qualifi cation tests prior to accepting a masking tape for use in the paint hangar. However, these tests cannot guard against variability and manufacturer changes in the production of the masking tape. The tape may pass the lab and shop tests only to fail in production on the airplane. Variation of the tape from batch to batch or within a batch often results in intermittent and unpredictable failures. Several components of the tape construction are considered. Tests are conducted with the same materials used in production and the actual production process is followed.USA

Accession no.863711

Item 413Journal of Advanced Materials34, No.3, July 2002, p.21-6WATER ABSORPTION OF MODEL PHENOLIC RESIN SYSTEMS FOR COMPOSITE APPLICATIONSGuionnet S; Seferis J CWashington,University

The effects of water absorption and thermal cycling on the thermomechanical properties of glass fi bre-reinforced phenol-formaldehyde resins were investigated using TGA and dynamic mechanical analysis. Samples were subjected to the effects of cycling between the extremes of 25 and 150C and to temperature environments commonly encountered by aircraft in fl ight. It was found that water



absorption followed a Fickian diffusion model and that most of the changes in the properties of the composites occurred when they were exposed to extreme conditions, which caused freezing or evaporation of the absorbed free water. 10 refs.USA

Accession no.862203

Item 414Journal of Materials Science37, No.13, 1st July 2002, p.2693-8DETERMINATION OF MOISTURE EFFECTS ON IMPACT PROPERTIES OF COMPOSITE MATERIALSWoldesenbet E; Gupta N; Vinson J RLouisiana,State University; Delaware,University

Many applications of structural materials involving composites include impact or dynamic loading in a humid environment. Composite materials are known to degrade when subjected to humid conditions, and therefore the humidity confounds the diffi culty of determining the high strain rate behaviour of composites. Several researchers have found that water absorption by composites causes degradation of matrix dominated quasi-static properties. However, very little is known of the effect of absorbed moisture on the high strain rate properties of polymer matrix composites, that are useful in the automotive, aerospace and naval applications of composite structures. A Split-Hopkinson Pressure Bar facility is used to study the effect of absorbed moisture in high strain rate tests (200-1200/s) of a unidirectional IM7/8551-7 graphite/epoxy composite. The study includes dry, medium and saturated moisture conditions. The tests show signifi cant variation of high strain rate properties from static properties, and the reasons are identifi ed. In addition, a better understanding of the effect of the matrix and fi bre/matrix interface on the high strain rate properties of composites is achieved. 13 refs.USA

Accession no.861969

Item 415Polymer Preprints. Volume 43, Number 1. Spring 2002. Papers presented at the ACS meeting held Orlando, Fl., 7th-11th April 2002.Washington D.C., ACS, Div.of Polymer Chemistry, 2002, 603-4METHYLATED AND TRIFLUOROMETHYLATED AROMATIC POLY(ETHER ETHER KETONE DIPHENYL KETONE)SHu W; Liu B; Zhao S; Chen C; Wang G; Wu Z; Jiang ZJilin,University(ACS,Div.of Polymer Chemistry)

Aromatic polymers are known for their usefulness in meeting the high-performance requirements for structural

resins, polymer fi lms and coating materials. Polyaryl ether ketones (PEKs) are examined for use in aerospace and electronics applications due to their combination of chemical, physical and mechanical properties. Considerable attention has been devoted to the preparation of fl uorine-containing polymers. The fl uorine-containing polymers have been prepared for applications as advanced optical and microelectronics materials. Due to these advantages, PEKs containing hexafl uoroisopropylidene units have been widely studied. Novel PEKs are prepared via aromatic nucleophilic substitution reaction. The bulky pendant groups are incorporated into the main chains containing diphenyl moieties. All the polymers showed higher Tgs and good thermal stability. Tough, fl exible films can be obtained by compression moulding and good solution casting. The mechanical properties of 3F-PEEKDK are discussed. These polymers may be useful in microelectronic applications, gas separation membranes and matrix resins. The study into this type of polymer continues. 4 refs.CHINA

Accession no.860437

Item 416Advanced Materials and Processes160, No.5, May 2002, p.14COMPOSITE STRUCTURE FOR CAMERA ON HUBBLE SPACE TELESCOPE

A graphite epoxy bench, which serves as a high-precision stable truss for the Advanced Camera for Surveys, is made by Alliant Techsystems and provides the strength, light weight and heat stability required for applications in space.ALLIANT TECHSYSTEMS

USA

Accession no.859105

Item 417Advanced Materials and Processes160, No.5, May 2002, p.13CARBON NANOFIBER COMPOSITES REDUCE WEIGHT FOR AIRCRAFT

The Air Force Research Laboratory’s Materials and Manufacturing Directorate at Wright-Patterson Air Force Base has developed vapour grown carbon fi bre technology, which can be used in the cost-effective manufacture of composites with high stiffness and thermal conductivity for military and aerospace applications.WRIGHT-PATTERSON AIR FORCE BASE

USA

Accession no.859101

Item 418High-Performance Composites10, No.2, March 2002, p.27



COMPOSITE PROPELLER BLADE OUTFLYS COMPETITION

AeroComposites set out manufacture a composite propeller blade that would outperform existing blades on high-performance aircraft engines for the General Aviation (GA) market, it met the challenge with a new mould material, a unique preform and a vacuum assisted resin transfer moulding (VARTM) process. Apex Machine Tool machined the mould from and ACI design, using a vacuum cast aluminium alloy called Alpase M-1 Mold Plate, rather than the 440 stainless steel or steel alloy typically used in such applications. The material requires no heat treatment during or after machining, and can be quickly preheated, enabling optimum temperature control. Demoulded parts have consistent geometry, extremely low void content and require minimal post-mould processing. At less than half the thickness of wood-core blades used on many aerobatic craft, ACI’s 7 lb problade is 20-50% lighter and, in critical regions, 10-15% thinner, with up to fi ve times centrifugal load capacity than aluminium blades. Its design reduces noise, stall fl utter and results in more even load distribution on the propeller hub’s blade retention. The composite’s low weight and natural damping characteristics also reduce vibration. According Aero Composites, its new blade is strongest in the GA market. Details are given.AEROCOMPOSITES INC.; EDAC TECHNOLOGIES CORP.; A & P TECHNOLOGY; TEXTILE PRODUCTS INC.; STEPAN CO.; CYTEC ENGINEERED MATERIALS

USA

Accession no.856521

Item 419Shawbury, Rapra Technology Ltd., 2002, pp.x, 428HANDBOOK OF POLYMER BLENDS AND COMPOSITES, VOLUME 2Petru Poni,Institute of Macromolecular Chemistry; Indian Petrochemical Corp.Ltd.Edited by: Kulshreshta A K; Vasile C

This handbook provides an overview of the theory and practice of polymer blends and composites. It comprises a collection of monographs on the subject of polymer blends and composites from over 50 professionals from academia and industry with chapters covering the following topics: overview of composite fabrication, design and cost; liquid moulding processes; use of advanced composite materials in the construction of suspension push-rods for a Formula One racing car; corrosion resistance of polymers, polymer blends and composites in liquid environments; new approaches to reduce plastic combustibility; fi bre reinforced plastic composites for biomedical applications; composite materials in the nuclear and space industries; advanced composes for offshore developments; functional polymer composites; conducting polymer composites; and recycling of automotive composites.EASTERN EUROPE; INDIA; RUMANIA

Accession no.856080

Item 420High-Performance Composites10, No.3, May 2002, p.56-60IMPROVED CORE MATERIALS LIGHTEN HELICOPTER AIRFRAMESBlack S

Honeycomb, usually made of aramid or aluminium, is now the preeminent core material in sandwich construction for aerospace applications. Nowhere is honeycomb’s high strength and low weight more important than in helicopters. The fi rst choice for many structural aerospace applications is phenolic-impregnated aramid paper. While Nomex, the fi rst aramid paper, is still widely used by many OEMs, DuPont has developed improved precursor materials - Korex and N636 Kevlar - with better properties, including less moisture uptake, better strength in hot/wet environments and much less expansion/deformation during autoclave processing. Ultracor has developed and patented a new carbon/carbon honeycomb core panel for use as fi rewall protection in helicopters.USA

Accession no.855271

Item 421High-Performance Composites9, No.5, Sept./Oct.2001, p.41-5EVOLVING PREFORMS ARE THE CORE OF COMPLEX PARTSCarter K

Composites researchers have touted near-net preforms as a cost-effective answer to production of composite parts since the 1980s. Advanced fi bre preforms are made using textile technologies such as weaving, knitting and braiding of carbon, glass or aramid fi bres and can be produced by either 2D or 3D techniques. More than 90% of preforms are manufactured by liquid moulding processes such as resin transfer moulding and vacuum-assisted resin transfer moulding, or, less frequently, resin fi lm infusion. Preforms are most economical when the cost of designing, testing and manufacturing them can be spread across a large number of parts. The aerospace industry has investigated preform use during the last 20 years and has, in general, found many applications in which preforms meet quality and price criteria. Lockheed used braided preforms to great advantage in the design of JASSM, a short-range cruise missile.USA

Accession no.855262

Item 422High-Performance Composites9, No.4, July/Aug.2001, p.20-6THERMOPLASTICS PROVIDE ATTRACTIVE OPTIONSBlack S



Thermoplastics have maintained a foothold in aerospace, as evidenced by use of thermoplastic composites for the wing leading edge on the Airbus A340-500/-600, landing gear doors and access panels on the Northrop Grumman F-5 and the fl oor panels in the EH Industries EH-101 helicopter. Interest in thermoplastic composites is currently even stronger in Europe than in the US, especially in aerospace and offshore oil applications. Engineering thermoplastic resins offer fairly high-temperature in-service capabilities under severe hot/wet operating conditions and good damage tolerance. Thermoplastic prepreg forms made using traditional prepregging approaches are hard to work with, especially for complex shapes. As a result, the industry has, over time, developed different approaches to produce more workable intermediate forms, for example, slurry impregnation and electrostatic powder coating. Developments in manufacturing methods and resin formulations are discussed.USA

Accession no.855103

Item 423Plast’ 21No.107, Dec.2001, p.63SpanishINJECTION MOULDING OF NATURAL FIBRE-REINFORCED PLASTICS

The advantages of natural fi bres such as hemp and fl ax as replacements for glass fi bres in plastics composites are discussed, and applications of such composites are reviewed with particular reference to components for automotive and other transport applications. Developments by Demag Ergotech in processes and machinery for the injection moulding of natural fi bre-reinforced plastics are examined.DEMAG ERGOTECH; FRAUNHOFER-INSTITUT FUER CHEMISCHE TECHNOLOGIE


Accession no.854894

Item 424Polymer Engineering and Science42, No.5, May 2002, p.983TENSILE MODULUS OF POLYMER NANOCOMPOSITES Xiang Ling Ji; Jiao Kai Jing; Wei Jiang; Bing Zheng Jiang Changchun,Institute of Applied Chemistry

Based on Takayanagi’s two-phase model, a three-phase model including the matrix, interfacial region and fi llers was proposed to calculate the tensile modulus of polymer nanocomposites. The composites were assumed to be composed of three independent segments connected to one another, in a series or a parallel manner. A linear gradient distribution of modulus of the interface was assumed. It

was also assumed that the fi llers (sphere-, cylinder- or plate-shape) were randomly oriented in a matrix. The effects of dispersed particle size, shape and thickness of the interfacial region exhibited a dominant infl uence on tensile modulus. Particulate-to-matrix modulus ratio and a parameter describing a linear gradient change in modulus between the matrix and the surface of particle both had a minor infl uence on tensile modulus. At a fi xed volume fraction of dispersed phase, the smaller particles provided an increasing modulus for the resulting composite as compared with the larger particles because the interfacial region markedly affected tensile modulus. When the size of the fi llers was in the scale of micrometers, however, the infl uence of interfacial region was neglected and the deduced equation was reduced to Yakayanagi’s model. 47 refs.CHINA

Accession no.854767

Item 425Engineering E2May 2002, p.15. This issue is published within Engineering, 243, No.5, May 2002.FOAM OF ONE’S OWN

A brief report is presented on the development by L.J.Lee et al. at Ohio State University of dense foam material reinforced with very small clay particles and on the use of such nanocomposites to replace solid plastics materials in structural applications such as car or aeroplane panels. The team has also developed techniques to eliminate the use of chlorofl uorocarbons in foam production.OHIO,STATE UNIVERSITY

USA

Accession no.854708

Item 426Rapid Tooling 2002. Proceedings of a conference held Coventry, 7th March 2002.Shawbury, Rapra Technology Ltd., 2002, Paper 6, p.51-9METAL SPRAY TOOLING FOR COMPOSITE FORMINGGibbons G JWarwick,University(Rapra Technology Ltd.; Plastics & Rubber Weekly)

The results are reported of a research programme, the IMI Spray Mould programme, aimed at developing a method of manufacturing tooling for the production of large primary composite structures, in particular, for aerospace applications. Work areas covered include spray methods and materials, pattern material development, backing and support, post-treatment and automation. A cost comparison for the manufacture of a composite forming tool by traditional fabrication and machining of Invar (nickel/iron alloy), carbon fi bre composite and a promising new Spray



Mould Invar metal spray process is made. 25 refs.IMI


Accession no.854557

Item 427Polymer Composites23, No.2, April 2002, p.141-52HYGROTHERMAL CYCLING EFFECTS ON THE DURABILITY OF PHENOLIC BASED COMPOSITESChung K; Yoshioka K; Seferis J CWashington,University

The thermal and mechanical properties of resin transfer moulded, carbon fibre-reinforced phenolic resins subjected to hygrothermal cycling were investigated as engineering materials for aerospace applications using DSC, DMA, TGA and double cantilever beam, fl exural and tensile testing techniques. The void content of the cross-section of specimens was evaluated by means of optical microscopy and the fracture morphology of specimens after interlaminar fracture testing was analysed by scanning electron microscopy. The effect of a silicone-based modifi er with phenolic end groups on the fracture performance of the composites was examined and the properties of the phenolic composites compared with those of epoxy composites.USA

Accession no.853501

Item 428Polymer Preprints. Volume 42. No.2. Fall 2001. Conference proceedings.Chicago, Il., Fall 2001, p.471SYNTHESIS AND CHARACTERISATION OF FLUORINATED POLYETHER CONTAINING BIPHENYLLiu B; Hu W; Chen C; Zhao X; Jiang Z; Zhang W; Wu ZJilin,University(ACS,Div.of Polymer Chemistry)

Aromatic polyethers have long been known for their high performance. These polymers are studied for use in aerospace and electronic applications because of their unique combination of chemical, physical and mechanical properties.’ Considerable attention has been devoted to the preparation of fl uorine-containing polymers because of their unique properties and high temperature performance. The incorporation of fl uorine atoms into the chain leads to polymers with increased solubility, fl ame resistance and thermal stability, while also leading to decreased colour, crystallinity, dielectric constant and moisture absorption. A type of fl uorine-containing monomer is synthesised and characterised. The preparation of novel aromatic polyether is accomplished via aromatic nucleophilic substitution of

activated aromatic halide with alkali metal bisphenate. The polymer has high Tg, excellent thermal stability and good solubility. 5 refs.CHINA

Accession no.853453

Item 429Chemical Week164, No.14, 3rd April 2002, p.22NEW PLASTIC TAKES ON A TOUGH MARKETPLACEWood A

Mississippi Polymer Technologies has started semi-commercial production of its proprietary ultrahigh-strength Parmax thermoplastic at Port Bienville, MS. The company has completed a 100,000-lbs/year unit for its polymer, which is as strong as steel, yet can be fabricated and machined using conventional methods. Parmax polymers are based on a substituted poly(1,4-phenylene). The fi rst commercially available products have benzoyl-substituted units. MPT has received a total of about 4.9m US dollars in R&D contracts from the US military to develop defence applications for Parmax.MISSISSIPPI POLYMER TECHNOLOGIES

USA

Accession no.852368

Item 430Plastics News InternationalMay 2001, p.24-5PLASTICS IN OUTER SPACE... SOLUTIONS FOR OUR PLANET

Some of the applications likely to form part of the K2001 presentation, which deals with the uses of plastics in aerospace technology and their potential applications on Earth, are listed and briefl y discussed. This presentation was jointly launched by Messe Dusseldorf, the European Space Agency, the Association of Plastics Manufacturers in Europe and the Association of the Plastics Producing Industry.MESSE DUSSELDORF; EUROPEAN SPACE AGENCY; ASSOCIATION OF PLASTICS MFRS. IN EUROPE; VERBAND KUNSTSTOFFERZEUGENDE INDUSTRIE EV

USA

Accession no.850363

Item 431European Design EngineerApril 2002, p.70TRANSPORT INTERIORS BENEFIT FROM NEW ADHESIVE TECHNOLOGY WHICH OFFERS REDUCED WEIGHT ADVANTAGE

Permabond has launched a fast setting two-part epoxy resin, E3300, which can be rapidly applied from one litre sticks and is particularly suitable in aircraft interiors and



other transport applications.PERMABOND

USA

Accession no.849953

Item 432Polymer Preprints. Volume 42, Number 2, Fall 2001. Proceedings of a conference held Chicago, Il., 26th-30th August 2001.Washington D.C., ACS,Div.of Polymer Chemistry, 2001, p.377-8SYNTHESIS AND CHARACTERISATION OF NOVEL SOLUBLE POLYARYL ETHER KETONESLiu B; Hu W; Jin Y; Chen C; Jiang Z; Zhang W; Wu ZJilin,University(ACS,Div.of Polymer Chemistry)

Polyaryl ether ketones (PEKs) are a class of high performance engineering thermoplastics known for their good thermal stability, excellent electrical and mechanical properties. This kind of advanced material is currently receiving considerable attention for its potential application in aerospace, automotive, electronics and other high technology fi elds. To obtain different properties and for different applications, structural changes have been introduced to the basic chain. To modify solubility and processability, much current work on PEKs is directed toward the synthesis of more soluble materials. Introduction of pendant groups onto the main chain is an effi cient way. PEK-type polymers with methyl, phenyl, and t-butyl substituents have already been prepared. Recent work has led to the preparation of new PEEK and PEEKK with (3-methyl)phenyl side group. Introduction of the big pendant group would affect glass transition temperature, crystallinity, dielectric constant, and modify solubility, fi lm formation, processability, etc. Functioned PEKs may be obtained due to existence of methyl group (-CH3). A monomer with high reactive activity is synthesised and characterised. The novel m-TPEEK and m-TPEEKK are prepared and characterised based on the monomer. M-TPEEK and m-TPEEKK have excellent thermal stability and good solubility. Strong, transparent and fl exible fi lms are readily obtained. 5 refs.CHINA

Accession no.849842

Item 433Advanced Composite Materials10, No.4, 2001, p.339-47APPLICABILITY OF CFRP MATERIALS TO THE CRYOGENIC PROPELLANT TANK FOR REUSABLE LAUNCH VEHICLE (RLV)Morino Y; Shimoda T; Morimoto T; Ishikawa T; Aoki TJapan,National Space Development Agency; Japan,National Aerospace Laboratory; Tokyo,University

It is essential to utilise CFRP for the main structural

materials of cryogenic propellant tanks in order to realise the drastic weight reduction needed for effi cient reusable space transportation systems. Recently-developed, toughened CFRP materials, expected to show good cryogenic properties, are considered promising candidates for these kinds of applications. The cryogenic properties of candidate materials and structural elements, including Y-joint structural models, are investigated. 300 mm diameter fi lament wound tank and 600 mm diameter lay up tanks are fabricated and tested. Based on experimental data, the feasibility of a CFRP cryogenic tank is discussed and future research tasks proposed. This research is conducted under the co-operation contract between the Japanese National Space Development Agency (NASDA) and the Japanese National Aerospace Laboratory (NAL). 3 refs.JAPAN

Accession no.849323

Item 434Polymer Preprints. Volume 42, number 2. Fall 2001. Proceedings of a conference held Chicago, Il., 26th-30th August 2001.Washington, D.C., ACS,Div.of Polymer Chemistry, 2001, p.276-7THERMAL PROPERTIES OF PHTHALIC ANHYDRIDE AND PHENOLIC RESIN CURED RIGID ROD EPOXY RESINSSu W-F; Lee Y-C; Pan W-PTaipei,National Taiwan University; Western Kentucky,University(ACS,Div.of Polymer Chemistry)

Rigid rod epoxy resins have been developed as a high performance polymer for electronic and aerospace applications due to their good thermal properties. Good mechanical and electrical properties are also obtained. Improved thermal properties for sulphanilamide or methyl cyclohexane cured epoxies bearing azomethine or biphenol rigid rod group have been demonstrated. Biphenol epoxy was also cured with trimellitic anhydride and diamino diphenylsulphone, and the cured epoxies exhibit good thermal and electrical properties. Good high-temperature resistance has also been observed for methylene dianiline or 4,4’-amino-phenoxy hexane cured biphenol epoxy. The diglycidyl ethers of bisphenol A (DGEBA) and tetramethyl biphenyl (TMBP) are cured with phthalic anhydride and phenolic resin. The selection of phthalic anhydride is based on its good electrical insulation and low cost. The choice of phenolic resin is for its good thermal stability. DGEBA has more fl exible structure than TMBP. The effects of structure of cured epoxy resin with the same curing agent on thermal properties are investigated. 6 refs.TAIWAN; USA

Accession no.849017



Item 435Journal of Applied Polymer Science83, No.10, 7th March 2002, p.2213-24STUDY OF THE PROCESSING CHEMISTRY OF POLYIMIDES WITH THERMOGRAVIMETRY/FOURIER TRANSFORM INFRARED/MASS SPECTROMETRY TECHNIQUESWei Xie; Heltsley R; Han-Xu Li; Lee C; Wei-Ping PanWestern Kentucky,University

Carbon fi bre-reinforced composites of polyimides are used in aircraft engines and in space applications. The processing chemistry of high-temperature polyimide prepregs was investigated using thermogravimetry, FTIR and mass spectrometry evolved-gas analysis techniques. The curing time and temperature for off-gas productions were determined. The thermal curing of the polyimides studied proceeded by: (1) the elimination of methanol from amic acid prepolymer formation; (2) the release of water from subsequent imidisation; and (3) thermal crosslinking. The FTIR/MS data obtained suggested that alternatively the elimination of water from amide ester formation may be followed by the release of methanol from subsequent imidisation. 11 refs.USA

Accession no.848107

Item 436Polymer Preprints. Volume 42. Number 2. Fall 2001. Proceedings of a conference held Chicago, Il., 26th-30th August 2002.Washington, D.C., ACS,Div.of Polymer Chemistry, 2001, p.23-4NATURAL FIBRE REINFORCEMENT OF POLYMERIC COMPOSITES BY REACTION-INDUCED PHASE SEPARATIONPrieto A; Jana S CAkron,University(ACS,Div.of Polymer Chemistry)

In recent years, many natural fibre-filled polymer composites have been reported. Thermosetting polymers such as polyesters, epoxy, cyanate esters and thermoplastic polymers such as PP, PE, PVC and PS have been compounded with wood fl our, wood pulp and cellulose fi bres to form composites. Despite of ongoing research activities, many issues need to be resolved to expand the use of natural fi llers in polymer products for diverse applications in automotive, aerospace and building industries. One such issue is poor polymer-fi bre bonding in the fi nal composites, mainly due to hydrophobic nature of the polymers. Another issue is low decomposition temperatures of natural fi bres which seldom exceed 200-220 deg.C. This precludes many engineering polymers, whose processing temperatures often exceed 250 deg.C, from consideration. New technologies, therefore, are needed to reduce the gap between processing temperatures of engineering polymers and decomposition temperatures of natural fi bres. A novel methodology is developed for

combining wood fl our particles with a high temperature thermoplastic polymer PPE with the aid of liquid epoxy. The epoxy coating layers around wood fl our particles provide good adhesion and stronger interfaces with the PPE phase. The composite material performs better than many engineering polymer composites in terms of mechanical properties. 11 refs.USA

Accession no.847951

Item 437Journal of Applied Polymer Science83, No.2, 10th Jan.2002, p.408-16STUDIES ON COMPRESSION BEHAVIOUR OF CARBON-EPOXY LAMINATES WITH AND WITHOUT BUFFER-STRIP LAYERS IN DRY AND WATER-ABSORBED CONDITIONSKishore; Khan B; Viswanath BIndian Institute of Science; Bangalore,Aeronautical Development Establishment

The compression behaviour is investigated of laminated carbon-epoxy composites with inserted interleaved polytetrafl uoroethylene-coated fabric material at different locations either continuously or discontinuously. The composite materials can be used in aerospace or other technologically advanced applications. The effect of water ingress in these specimens on the strength value is measured. Signifi cant differences were noticed in the trend of the strengths for different architectural arrangements in dry and water-immersed samples. The introduction of small amounts of less adherent layers of material at specifi c locations causes a decrease in the load-carrying capability of the composite. With an increase in the number of buffer/delaminating strips insertions, water ingress increases and compressive strength decreases. A correlation was seen between the observed strength values, architecture and failure mode. 11 refs.INDIA

Accession no.846627

Item 438Polymer43,No.6,2002,p.1717-25N-(2-BIPHENYLENYL)-4-(2’-PHENYLETHYNYL)PHTHALIMIDE - NEW MONOMER SYNTHESIS, CURE AND THERMAL PROPERTIES OF RESULTING HIGH TEMPERATURE POLYMERGeorgiades A; Hamerton I; Hay J N; Shaw S JSurrey,University; QinetiQ

A synthetic route is described to a new monomer, N-(2-biphenylenyl)-4-(2’-phenylethynyl)phthalimide (BPP), which contains both phenylethynyl and biphenylene reactive functional groups. The monomer can be made either from N-(2-biphenylene)acetamide or 2-aminobiphenylene, by reaction with the phenylethynyl-containing anhydride. The monomer was characterised fully and the thermal



cure of the material was studied by IR spectroscopy and DSC. The IR spectra showed that the phenylethynyl group reacted completely within 1 hour at 370C. DSC showed the polymerisation exotherm of BPP centred at 379C, lower than two NASA-developed phenylethynyl-terminated imide (PETI) resins. In comparison with the PETI systems, the Tg of cured BPP was about 100C higher, making it a candidate for possible high temperature applications. 31 refs.EU; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE; WESTERN EUROPE-GENERAL

Accession no.846141

Item 439Reinforced Plastics46, No.2, Feb.2002, p.44-9RESIN FILM INFUSION - COMPOSITES COST REDUCERMarsh G

It is explained that, until recently, resin fi lm infusion had not found widespread use, but now the system is showing signs of joining the reinforced-plastics fabrication mainstream, with commercial applications emerging in the automotive, aerospace, and marine sectors. This article describes the process, reviews its benefi ts, and considers some of its applications.AUSTRALIA; EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; UK; WESTERN EUROPE

Accession no.845700

Item 440High Performance PlasticsFeb.2002, p.3PBT ELASTOMERS MADE BY ONE-STEP EXTRUSION PROCESS

Cyclics Corp. of the USA has developed PBTP-based elastomers, using a novel reactive extrusion technique in which polymerisation and processing are carried out in a continuous one-step process. This article briefl y describes the technology, explains its unique advantages, and lists applications for the elastomers so produced.CYCLICS CORP.

EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; USA; WESTERN EUROPE

Accession no.845659

Item 441Plastics, Rubber and Composites30, No.10, 2001INTERPENETRATING POLYMER NETWORKS BASED ON MODIFIED CYANATE ESTER RESINFan J; Hu X; Yue C YNanyang,Technological University

High-performance interpenetrating polymer networks (IPNs) containing various ratios of cyanate ester and 2,2’-

diallylbisphenol A having two phenolic hydroxy groups with added bismaleimide were synthesised. The catalytic effect of the hydroxy phenolic groups and reactivity of the IPNs were investigated by DSC and their Tgs and mechanical properties determined by DMA and fl exural and impact testing. The dielectric properties of these IPNs were also determined and their potential applications in the aerospace and microelectronics industry considered. (International Conference on materials for Advanced Technologies, Singapore, 1-6 July, 2001). 23 refs.SINGAPORE

Accession no.845237

Item 442Composite Structures55, No.2, Feb. 2002, p.217-23EXPERIMENTS ON SINGLE LAYER TEXTILE COMPOSITESD-Amato EL’Aquila,University

A two-stage study was carried out into the strength and stiffness of braided composites intended for aerospace applications. In the fi rst stage, tests were carried out on specimens with a certain degree of damage in order to establish the incidence of damage. The second stage focussed on geometrical characteristics and specimen preparation in order to examine stress decay processes and reduce scattering in the data and involved the characterisation of strength concentration on the side edge and in the outlet areas of tabs. 6 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; ITALY; WESTERN EUROPE

Accession no.845185

Item 443Reinforced Plastics

46, No.1, Jan. 2002, p.22-4AEROSPACE COMPOSITES DOWN BUT NOT OUTMarsh G

The effect of the September 11th terrorist attack on the World Trade Center is discussed, with reference to the composites industry, and in particular, suppliers to the aerospace industry. Despite many airline companies going out of business and suffering severe losses, it is argued that although material suppliers are inevitably caught up in this aftermath, military and security markets will provide growth sectors, and in particular, with reference to supplies of Kevlar for use in reinforcing aircraft installations and in ballistic applications, DuPont is reported to be increasing production capacity.USA

Accession no.843843



Item 444Reinforced Plastics46, No.1, Jan. 2002, p.17SIMULATING LIQUID MOULDING

Details are given of a computer software package for use in the design of composite parts made using processes such as resin transfer moulding, vacuum assisted RTM and resin fi lm infusion. LCMFLOT 2001 has been developed by ESI Group USA specifi cally for liquid composite moulding processes, and aims to help users decrease part weight and improve quality in composite components used in industries such as aerospace, automotive and consumer goods. The software is designed to provide a simulation process for the optimisation of moulding parameters. Its capabilities and typical applications are briefl y described.ESI GROUP USA

USA

Accession no.843842

Item 445Journal of Intelligent Material Systems and Structures12, No.4, April 2001, p.265-70IMPROVED SURFACE TREATMENT OF SMA FOILS AND DAMAGE SUPPRESSION OF SMA-FOIL EMBEDDED CFRP LAMINATESOgisu T; Ando N; Takaki J; Okabe T; Takeda NFuji Heavy Industries Ltd.; Tokyo,University

Research and development studies have been conducted on some applications of embedded SMA foil actuators in CFRP laminates for weight reduction and improvement of reliability for next generation aircraft. The goal of this research is to develop a method for the suppression of damage growth in CFRP laminates. It is certified that one of the key technologies is bonding properties between SMA foils and CFRP laminates. Improvement of bonding properties between SMA foils and CFRP and confi rmation of suppression effects of damage growth are described. Some surface treatments are performed on SMA foils. Peel resistance and single lap shear strength tests are performed using surface treated SMA foils. It is found that treatment by 10% NaOH is the most effective treatment for improvement of bonding properties. The treated surface is found to be porous and rough, which is supposed to provide anchoring effects of SMA/CFRP interfaces. Quasistatic load-unload tests are performed using the optimum treatment to investigate the damage behaviour of quasi-isotropic CFRP laminates with embedded SMA foils. Micromechanisms of fracture behaviour and the correlation between the crack density and the residual strain are discussed. The recovery stress of the SMA foil generated at over Af temperature shows capability of suppression for onset of transverse cracks in quasi-isotropic CFRP laminates with embedded SMA foils. 4 refs.

JAPAN

Accession no.843717

Item 446Composites InternationalNo.48, Nov./Dec.2001, p.57/68English; FrenchSUCCESS OF LIGHTWEIGHT MATERIALS

We are told that honeycomb has already proved itself in the aviation industry, where weight savings and stiffness have always been a priority, but that other solutions are also appearing in response to the constraints of mass markets. This article provides an up-to-the-minute report on the techniques and applications involved.BELGIUM; EUROPE-GENERAL; EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; USA; WESTERN EUROPE

Accession no.843341

Item 447European Plastics News29, No.2, Feb.2002, p.18SAFETY IN THE AIR

Telair International has begun production of a ballistics-tested and flammability qualified “hardener” panel material for aircraft cockpit doors and other cabin security applications. The panel is a multilayer composite that uses a patent-pending construction of Kevlar, Nomex and phenolic materials. The new material is said to be highly resistant to material fatigue and retains most of its structural integrity, even after repeated ballistic impacts.USA

Accession no.842380

Item 448Macplas InternationalDec. 2001, p.65-9FORMING PROCESSES FOR THERMOPLASTIC COMPOSITESCarrino L; Napolitano G; Strano MCassino,Universita

The forming techniques currently available, including compression moulding, matched die moulding, diaphragm moulding and deep drawing, are described and polymers, reinforcements and semi-fi nished structures employed to make formed parts are discussed. The utilisation of these processes to make a range of applications, including aerospace, medical, military, sport and automotive applications, is also covered.EUROPEAN COMMUNITY; EUROPEAN UNION; ITALY; WESTERN EUROPE

Accession no.841800

Item 449Materials World9, No.11, Nov. 2001, p.22-4



TECHNOLOGICAL & ENVIRONMENTAL PRESSURES ON ADVANCED ADHESIVESKeddie J; Mallegol J; DuPont OSurrey,University; UCB Chemicals

Developments in pressure-sensitive adhesives are examined as the industry responds to environmental and technological challenges which enable them to be increasingly used in high-performance applications. The ability of PSAs to remain transparent under a variety of conditions enable them to be used in applications requiring aesthetic properties. Their strength and durability enable them to replace bolts and welding and automotive and aerospace applications, and when used as components of wound dressing, are able to be easily removed when required, yet have the necessary adhesion to stay in place for as long as necessary.BELGIUM; EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.840535

Item 450Polymer Engineering and Science41, No.11, Nov.2001, p.2036PROCESSING AND PROPERTIES OF POLYMERIC NANO-COMPOSITES Hua Wang; Changchun Zeng; Elkovitch M; Lee L J; Koelling K W Ohio,State University

Polymeric nano-composites were prepared by melt intercalation. Nano-clay (montmorillonite) was mixed with either a polymer (nylon-6, PP or PS) or a polymer blend by twin-screw extrusion. The clay-spacing in the composites was measured by X-ray diffraction. The morphology of the composites and its development during the extrusion process were observed by SEM. Melt viscosity and mechanical properties of the composites and the blends were also measured. It was found that the clay spacing in the composites was markedly infl uenced by the type of polymer used. The addition of the nano-clay could greatly increase the viscosity of the polymer when there was a strong interaction between the polymer and the nano-clay. It could also change the morphology and morphology development of nylon 6/PP blends. The mechanical test showed that the presence of 5 to 10 wt % nano-clay signifi cantly increased the elastic modulus of the composites and blends, while signifi cantly decreasing the impact strength. The water absorption of nylon 6 was decreased in the presence of nano-clay. The effect of nano-clay on polymers and polymer blends was compared with that of kaolin clay under the same experimental conditions. 22 refs.USA

Accession no.840103

Item 451Journal of Composite Materials

35, No.20, 2001, p.1815-43DAMAGE TOLERANCE ANALYSIS OF CRACKED STIFFENED COMPOSITE PANELSChen P; Shen Z; Wang J YShaanxi,Aircraft Strength Research Institute

An approach based on a displacement compatibility model was developed for stiffened composite panels with a crack. Improvements on the damage tolerance analysis of the stiffened composite panels were made. Applications in the aircraft industry are mentioned. Data are given for graphite fi bre-reinforced epoxy resins. 17 refs.CHINA

Accession no.839568

Item 452Composites Science and Technology61, No.15, 2001, p.2337-44NEW ADVANCES IN DAMAGE MECHANICS AND COMPUTATIONAL METHODS FOR COMPOSITES: FROM RESEARCH TO INDUSTRY FOR SPATIAL APPLICATIONSAubard XSNECMA

Advances in the mechanical modelling of composites for aerospace applications aimed at reducing costs are discussed and examples of these advances in the modelling of carbon fibre-reinforced phenolic composites for aerospace applications propellant booster nozzles, carbon/carbon composites produced by densifi cation and nozzle bearings made from multi-layer composites incorporating fl exible rubber pads are presented. The capabilities of current industrial modelling procedures for aerospace applications are summarised and the shortcomings of these methods are considered. 7 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; FRANCE; WESTERN EUROPE

Accession no.839361

Item 453Adhasion Kleben und Dichten45, No.7/8, 2001, p.33-7GermanADHESIVE TECHNIQUES FOR REPAIRING CONTAMINATED CARBON FIBRE REINFORCED PLASTIC LIGHTWEIGHT TYPES (PART I)Wolfrum J; Boelingen M; Luigart F; Czarnecki JGermany,Federal Offi ce Defense Technology & Procurement

High-performance compound materials with carbon fi bre plastic reinforcement are important materials in technical air travel applications because of their outstanding specifi c toughness, strength and rigidity. With regard to a planned 30 to 40 year cycle of use, new aircraft can only sensibly be operated if suitable repair procedures are available. This article reviews storage conditions and treatment of



laminated plates, the potential of contamination-tolerant adhesive systems, moisture adsorption, IR-spectroscopy including DRIFT tests, shear-tension tests and analysis of surface fracturing.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; WESTERN EUROPE

Accession no.839192

Item 454Adhasion Kleben und Dichten45, No.7/8, 2001, p.10-2

GermanCOLD-BONDING - INNOVATORY LEAP FORWARD IN AIRCRAFT CONSTRUCTION (PART I)De Wit F; Sauer JAirbus Deutschland GmbH; Vantico AG

Structural bonding and gluing used in aircraft construction are traditionally applied with hot-curing fi lm adhesives on an epoxy base. Efforts to reduce the costs linked to the application of fi lm adhesives have led to the development of cold-bonding and a two-component paste adhesive suitable for this on an epoxy base. The advantages of carbon fi bre reinforced plastic in aircraft structures are examined alongside adhesive applications in fi bre-bonded materials in the Airbus A319 and A320. 1 ref.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; SWITZERLAND; WESTERN EUROPE

Accession no.839187

Item 455Advanced Materials and Processes159, No.11, Nov. 2001, p.12LOW-DIELECTRIC POLYMERS SPEED INTEGRATED CIRCUITSWright-Patterson Air Force Base

The Wright-Patterson Air Force Base has reported the development of polymers with ultra-low dielectric constants for high-speed integrated circuits. These polymers are fl exible, aromatic benzoxazole polymers containing a perfl uoroisopropyl unit, which are thermooxidatively stable and have a low moisture uptake. Applications include space-based radar, satellite communications and high-speed computers.USA

Accession no.837118

Item 456Polymer Engineering and Science41, No.9, Sept.2001, p.1486-96REACTIVE BLENDING OF FUNCTIONALIZED ACRYLIC RUBBERS AND EPOXY RESINSDispenza C; Carter J T; McGrail P T; Spadaro GPalermo,University; ICI Technology

A high molec.wt. acrylonitrile-butadiene-methacrylic

acid(Nipol 1472) rubber was selected to control processability and mechanical properties of a tetraglycidyl diaminodiphenylmethane-based epoxy resin formulation for aerospace composite applications. The physical blend of rubber and epoxy resin, achieved by dissolution of all the components in a common solvent, formed a heterogeneous system after solvent removal and exhibited coarse phase separation during cure that impaired any practical relevance of this material. A marked improvement of rubber-epoxy resin miscibility was achieved by reactive blending of the epoxy oligomer with the functional groups present in the rubber. The epoxy-rubber adduct thus obtained appeared as a homogeneous system at room temp. and also after compounding with the curing agent. Depending on the nature and extent of interactions developed between the rubber and the epoxy resin during ‘pre-reaction’, materials with different resin flow characteristics, distinctive morphologies and mechanical properties after curing were obtained. The effect of ‘pre-reaction’ on the resin cure reaction kinetics was also investigated. 24 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; ITALY; UK; WESTERN EUROPE

Accession no.836148

Item 457Chemical and Engineering News79, No.18, 26th Nov. 2001, p.8CAUSE OF PLANE CRASH SOUGHTTullo A

A report is presented on the crash of an Airbus A-300-600 series aircraft in Queens, N.Y., which investigators consider may have been contributed to by a defect in the carbon fi bre/epoxy composite tail fi n. Doubts have since been cast on the safety of composite materials, which entered fl ight-critical applications 15 to 20 years ago. Some consider that composites may be subject to fatigue like metals, resulting in delamination and part failure, while others refute this theory.USA

Accession no.836023

Item 458Advanced Materials and Composites News23, No.22, 19th Nov.2001, p.8MC GILL OFFERING COCKPIT ARMOUR PANELS

M.C.Gill of El Monte, California, is reported to be nearing federal certifi cation on three ballistic laminate panels for aircraft cockpit protection and other armoring applications. Gillfab ballistic panels are reported to include fabrics made of Kevlar aramid fi bre, penetration-resistant glass laminate, and specially woven glass fabric. The laminates have undergone tests for fl ammability, smoke and heat release required for use in commercial aircraft interior applications and are said to be among the few to meet these requirements simultaneously. Very brief details are noted.



GILL M.C.,CORP.

USA

Accession no.835681

Item 459Polymer Preprints. Volume 41. Number 2. Conference proceedings.Washington, D.C., 20th-24th Aug.2000, p.1391-2STUDY OF CRYSTALLISATION KINETICS IN ZENITE THERMOTROPIC LIQUID CRYSTALLINE POLYMERPramoda K P; Chung T SSingapore,Institute of Materials Research & Engineering; Singapore,National University(ACS,Div.of Polymer Chemistry)

Zenite liquid crystalline polymer resins are wholly aromatic polyester resins and are easily melt processed. These materials should be considered in applications requiring high temperature performance, retention of properties over a wide temperature range, dimensional stability, chemical resistance and excellent electrical properties. They are well suited for use in automotive, electrical/electronic, fi bre optics, telecommunications and aerospace industry. No systematic study appears to have been carried out of the thermal behaviour and post-treatment of Zenite 8000B (Z8000B). The effects of thermal post-treatment on the crystallisation behaviour of Z8000B using differential scanning calorimetry are reported. 15 refs.SINGAPORE

Accession no.835414

Item 460Polymer Preprints. Volume 41. Number 2. Conference proceedings.Washington, D.C., 20th-24th Aug.2000, p.1342-3FABRICATION AND PROPERTIES OF NEW ARAMID FIBRE-CYANATE ESTER COMPOSITESSankarapandian M; Shih P; Gabara V; Hendren G L; Loos A C; McGrath J EVirginia,Polytechnic Institute & State University; DuPont Fibers(ACS,Div.of Polymer Chemistry)

Aramid fi bre composites fi nd wide applications in many areas including the sandwich structures for military aircraft, in skins and core of advanced radomes and as laminate substrates for high speed computer circuit boards. In addition to the use of epoxy as matrix resins, studies have also been performed using phenolic resin and elastomers as matrix materials for aramid fi bre reinforced composites. Aramid fi bres have a tensile strength comparable with that of carbon fi bre and the modulus between those of glass and carbon fi bre aramid fi bre based composites are of interest due to the close match of coeffi cient of the thermal expansion to that of the matrix. An attempt is made to fabricate new aramid fi bre composites based on

cyanate ester as the matrix resin and evaluate the thermal and mechanical properties of the composites. Both Nomex and Kevlar mats are used for reinforcements. 4 wrefs.USA

Accession no.835387

Item 461Polymer42, No.24, 2001, p.9783SYNTHESIS, STRUCTURE, MECHANICAL PROPERTIES, AND THERMAL STABILITY OF SOME POLYSULFONE/ORGANOCLAY COMPOSITESSur G S; Sun H L; Lyu S G; Mark J E Yeungnam,University; Cincinnati,University

A solution-dispersion method was used to prepare polysulphone/organoclay nanocomposites which were then characterised using X-ray diffraction, transmission electron microscopy, thermogravimetric analysis and tensile measurements. Three levels of clay addition were used, 1,3 and 5 weight percent, and compared to the pure polymer, improvements in tensile and thermal properties were reported. 206 refsKOREA; USA

Accession no.831803

Item 462Advances in Polymer Science2001, 155, p.1CYANATE ESTER RESINS, RECENT DEVELOPMENTSNair C P R; Mathew D; Ninan K N Vikram Sarabhai Space Centre

The search for advanced, high performance, high temperature resistant polymers is on the increase due to growing demand for polymer matrix composites that are to meet stringent functional requirements for use in the rapidly evolving high-technology area of aerospace. Cyanate esters form a family of new generation thermosetting resins whose performance characteristics make them attractive competitors to many current commercial polymer materials for such applications. Recent developments in the chemistry, technology and applications of cyanate esters are analysed. Emphasis is placed on advances in research and development related to fundamental and applied aspects of cyanate esters during the last few years. A brief account is given of the overall scenario of the developments in this area, prior to discussing recent trends in detail. 382 refs.INDIA

Accession no.816043

Item 463Shawbury, Rapra Technology Ltd., 1997, pp.132. Rapra Industry Analysis Series



POLYMERIC MATERIALS IN AGGRESSIVE ENVIRONMENTS. MATERIAL IN USE AND THEIR MARKETPLACEDrake N Rapra Technology Ltd.

This report on the use of polymeric materials in aggressive environments covers materials for high and low temperature environments, chemically aggressive conditions and applications requiring resistance to weathering. End-use applications examined, include aerospace, automotive, electrical/electronic, and medical applications. Properties relevant to polymers used in aggressive environments are discussed, in particular, physical, thermal and chemical properties. Materials considered include polychloroprene, PU elastomers, HNBR, fl uoroelastomers, thermoplastic elastomers, liquid crystal polymers, polyamides, poly-p-phenylobenzobisthiazole fi bres, PEEK, polyimides, polyketones, polymer blends, syndiotactic polystyrene, sulphone polymers, and thermosets. 33 companies involved with polymeric materials for aggressive environments are identifi ed, and research currently being conducted, and new product developments are reviewed with reference to specifi c companies.EUROPE-GENERAL

Accession no.815491

Item 464SAMPE Journal37, No.2, March/April 2001, p.102OVERVIEW OF POLYMER MATRIX COMPOSITES PERFORMANCE AND MATERIALS DEVELOPMENT FOR AEROSPACE APPLICATIONSMorgan R J; Shin E E; Lincoln J; Jiang Zhou Michigan,State University

A review is presented of the authors’ present and future studies of the use of polymer matrix fi brous composites for aerospace applications. Aspects covered include structure-property relations of polybismaleimide- and polyimide-carbon fi bre composites, accelerated test methodologies, performance and materials development of electron beam-cured cryogenic containment composites, and development of low cost, carbon-based structures. 14 refs.USA

Accession no.810322

Item 465Journal of Polymer Science: Polymer Physics Edition 38, No.22, 15th Nov.2000, p.2873MECHANICAL PROPERTIES OF CLAY-POLYIMIDE NANOCOMPOSITES VIA ODA-MODIFIED ORGANOCLAYTyan H-L; Wei K-H; Hsieh T-E Taiwan,National Chiao Tung University

Clay-polyimide nanocomposites were synthesised from

modifi ed montmorillonite and polyamic acid. The layered silicates of organoclay were intercalated by polyimide and examined by X-ray diffraction and TEM. Tensile properties of the nanocomposites were investigated. 25 refsTAIWAN

Accession no.797643

Item 466Materials Challenge - Diversifi cation and the Future. 40, No.2, Symposium proceedingsHIGH TEMPERATURE PERFORMANCE OF GLASS FABRIC/POLYIMIDE COMPOSITESChen X; Muzzy J D Georgia,Institute of Technology

Polyimide composites have been used at temperatures exceeding 300 deg.C in the aerospace and electronics industries. Emphasis is placed on assessing the thermo-oxidative stability of composites comprised of a polyimide resin, Avimid N, with S-glass and quartz as fabrics treated with A-1100 coupling agent. Since this coupling agent is not tailored for high temperature applications, this system provides a baseline for evaluating high temperature coupling agents. Thermal ageing at 343 deg.C for up to 200 hours leads to substantial reductions in fl exural strength and short beam shear strength. The loss in strength occurs more rapidly in the smaller short beam shear samples. The degradation is dependent on the relative proportion of cut surfaces where fi bre ends are exposed in the samples subjected to ageing. 6 refs.USA

Accession no.698012

Item 467Composites-French/EnglishNo.28, 15th Aug-30th Sept.1998, p.70HIGH PERFORMANCE RTM AND RESIN DEVELOPMENTS FOR AEROSPACE INDUSTRYFrancomb J; Parmer M; Taylor A Pera Technology

Continuous fi bre reinforced composites are now fi rmly established engineering materials for the manufacture of components with high added value. They offer design engineers enormous opportunities for introducing new concepts into their designs while reducing costs. The resin transfer moulding process is playing an important role in increasing the use of advanced composites. This comprehensive article highlights the latest high performance resin transfer moulding and resin developments with particular emphasis on applications in the aerospace industry.EUROPEAN COMMUNITY; EUROPEAN UNION; UK; WESTERN EUROPE

Accession no.696236



Item 468PROTECTIVE COATINGS FOR POLYIMIDE COMPOSITESPatent US 5716677 A 19980210Mazany A M; Prybyla S G Ohio Aerospace Institute

The service life of fi bre-reinforced polyimide composites in a high temperature oxidative environment is extended by coating with a polyimide precursor solution prepared by reacting an aromatic dianhydride with an aromatic diamine in a non-reactive solvent. The reactive solution is heated to a temperature suffi cient to reduce its viscosity prior to its use as a coating. Preferably, a mixture of meta-phenylenediamine and para-phenylenediamine is reacted with biphenyl dianhydride in N-methyl pyrrolidinone solvent and heated to between about 50 and 150C under nitrogen while stirring for a time suffi cient to produce a polyamic acid polyimide precursor coating solution having a Brookfi eld viscosity of from about 500 to 5,000 cP and a solids content of from about 5 to 35 wt.%.USA

Accession no.688132

Item 469Journal of Applied Polymer Science65, No.5, 1st Aug.1997, p.1031HEAT RESISTANCE PROPERTIES OF POLY(P-PHENYLENE-2,6-BENZOBISOXAZOLE) FIBREKuroki T; Tanaka Y; Hokudoh T; Yabuki K Toyobo Co.Ltd

The high temperature properties of poly(p-phenylene-2,6-benzobisoxazole)(PBO) fi bre were examined and compared with those of p-aramid fi bre. In particular, the temperature dependence of tensile strength of the PBO fi bre was reported for the fi rst time. 9 refs.JAPAN

Accession no.650299

Item 470Advanced Materials and Processes149, No.3, March 1996, p.37POLYMER COMPOSITES FOR AEROSPACE

This comprehensive article supplies a detailed assessment of the different types of polymer composites used in aerospace applications. The various types of thermosetting resins are described, together with their properties and advantages. Information is included on the different reinforcing fi bres employed and the functions of the matrix resin materials.USA

Accession no.585371

Item 471Composites Part A: Applied Science and Manufacturing

27A, No.4, 1996, p.329THERMOPLASTIC COMPOSITES - RAPID PROCESSING APPLICATIONSOffringa A R Fokker Special Products BV

Processing techniques for continuous fi bre-reinforced thermoplastic composites are discussed, with particular attention to thermofolding, press-forming, welding, creep-forming and membrane-forming. Applications of the different techniques are considered, with emphasis on aerospace applications. 9 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; NETHERLANDS; WESTERN EUROPE

Accession no.582869

Item 472CROSS-LINKABLE FOAMABLE POLYOLEFIN RESIN COMPOSITION Patent Number US 5091435 Suzuki T; Kitagawa S; Nakayama T; Kuno T Tonen Chemical Corp.

This patent is a reissue (RE 34607). The composition described, capable of forming foams with excellent mechanical properties and heat resistance, is made of (a) 14-80 wt.% of a propylene-ethylene random copolymer having an ethylene content of 1.5-6 wt.%, (b) 10-60 wt.% of a propylene-ethylene random copolymer having an ethylene content of 0.2-1.0 wt.%, (c) 10-60 wt.% of a linear low-density polyethylene, and (d) 1-30 pbw, per 100 pbw of the above resin composition, of a foaming agent. JAPAN

Accession no.535371

Item 473Polymer35, No.23, 1994, p.4956IM7/LARC-ITPI POLYIMIDE COMPOSITESHou T H; Siochi E J; Johnston N J; St Clair T L Lockheed Engineering & Sciences Co.; US,NASA Langley Research Center

LARC-ITPI, an isomeric variation of LARC-TPI and based on 4,4’-isophthaloyldiphthalic anhydride and 1,3-phenylenediamine, was evaluated as a matrix for high performance composites. Five 30% poly(amide acid) solutions in N-methylpyrrolidone, with stoichiometric offsets of 2.0, 3.0, 4.0, 4.75 and 5.5% in favour of the diamine and end-capped with phthalic anhydride, were synthesised. Molecular weight and MWD data showed high concentrations of low molecular weight species in all the offset compositions. Solvent/volatile depletion rates were carefully determined on thermally imidised fi lms of the fi ve compositions and were an important part of the composite consolidation studies. All fi lms failed solvent resistance tests with acetone, MEK, toluene, dimethylacetamide and chloroform. Unidirectional IM7 prepreg was made from each of the fi ve resin solutions. A



workable composite consolidation cycle was developed for the 3% offset solution and used for all the compositions. Data are shown for moulding cycle optimisation, C-scans, shear, fl ex and compression failure, morphology, shear strength, fl exural modulus, fl exural strength, interlaminar fracture toughness, impact strength, resin-fi bre adhesion, compression strength after impact and open-hole compression testing. It was concluded that LARC-ITPI will be an excellent high temperature matrix material for aerospace applications where solvent resistance is not a key requirement. 36 refs. (Presented at ACS Polym. Chem. Div. 17th Biennial Symposium on Advances in Polymerisation and High Performance Polymeric Materials, Palm Springs, California, USA, 22nd-25th Nov. 1992).USA

Accession no.535040

Item 474Broadening Horizons with Advanced Materials & Processes. Proceedings of the 14th International European Chapter Conference, Birmingham, UK, 19th-20th Oct.1993, p.301ECONOMIC THERMOPLASTIC COMPOSITES FOR AEROSPACE AND ENGINEERING APPLICATIONSStepprath K; Broderick J; Leach DFiberite Europe GmbH; ICI Fiberite

Continuous fi bre-reinforced thermoplastic composites are being used in a wide range of applications, including aircraft, helicopter, space and submersible structures, machinery and other engineering components. Economic aspects of these materials are discussed, including new developments in lower cost materials, and the economics of fi nished parts and current applications are considered. Tabulated information is given on typical properties of matrix polymers (PEEK, polyphenylene sulphide, polyetherimide, polyethersulphone), mechanical properties of composites of these polymers with carbon fi bre, and interlaminar fracture toughness, compression strength and fl exural properties of the composites. 20 refs.EUROPEAN COMMUNITY; EUROPEAN UNION; GERMANY; USA; WESTERN EUROPE

Accession no.521908

Item 475Park Ridge,NJ, Noyes Publications, pp.ix,177HIGH PERFORMANCE THERMOPLASTIC RESINS AND THEIR COMPOSITESAuthors- Belend S National Research Council of Canada

This book describes recent developments in high performance thermoplastic resins and their composites, and evaluates the benefi ts and limitations of these materials for aerospace and other applications. An examination is made of the performance of neat and continuous fi bre reinforced thermoplastic resins in terms of their

properties and environmental/chemical resistance. The inter-relationships between morphology and properties of semicrystalline thermoplastic composites are addressed and the various techniques for combining fi bres and matrix are described. A penultimate section looks at the costs and typical applications of thermoplastic composites in the aerospace industry, while a fi nal summary presents general conclusions and recommendations for future research and development work in the fi eld.

USAAccession no.468658

Index


Index

AABRASION RESISTANCE 11ACOUSTIC EMISSION 93ACOUSTI-CAP HONEYCOMB CORE 23ACRYLIC RUBBERS 126ADHESIVE FILM, STRUCTURAL 3, 20, 47AERIAL VEHICLES, UNMANNED 97AEROGELS 33AEROSPACE APPLICATIONS 3, 5-8AEROSPACE FIBRES 3AIR AGEING 44AIRCRAFT CONSTRUCTION, GLUING 126ARALDITE ADHESIVES 112ARAMID FIBRE 5-6, 114 COMPOSITES 127ARRHENIUS’S METHOD 61ATMOSPHERIC PLASMA TREATMENT 49ATOMIC FORCE MICROSCOPY 105AURUM 70AUTOMATED TAPE LAYING, DESIGN TOOL 24AUTONOMIC HEALING 114AUXETIC MATERIALS 23

BBASOTECT TG 72, 74BENZOXAZINES 8, 64BIOCIDAL POLYMERS 49BIOCOMPOSITES 107BIONANOCOMPOSITES 45BIOT-FOURIER METHOD 56BISMALEIMIDES 8, 43 COMPOSITES 39 MATRIX PREPREG 22 PREPREG, CYCOM 5250-4 80 RESIN MATRIX COMPOSITE 43 THERMOSETTING RESIN 8BISPHENOL A DICYANATE RESIN 73BRABENDER PLASTICORDER 76BRABENDER-TYPE MIXING 15BRAGG GRATING PRINCIPLE 58BUTADIENE-ACRYLONITRILE,

CARBOXYL-TERMINATED LIQUID 73

CCARBON FIBRE-REINFORCED COMPOSITES 30CARBON FIBRE-REINFORCED EPOXY RESIN 29, 50 COMPOSITE LAMINATE PANEL 27CARBON FIBRE-REINFORCED PLASTICS 7, 72,

74-75, 79, 124 COMPOSITES 76

LAMINATES 71 THERMOPLASTIC PROFILES 22CARBON FIBRES 3-4 COMPOSITE TECHNOLOGY 31 SELF-HEALING 59 STOPPING POWER 41CARBON NANOFIBRES 14, 80CARBON NANOFILLERS 54CARBON NANOTUBES 13-44, 44-45, 65, 67, 105 FILLED RESIN 61 HYBRIDS 54 MULTIWALL 4 SKIN 45 SINGLE WALL 26, 70, 109CARBON/EPOXY PREPREGS 61CELLULAR FOAMS 96CETEX THERMOPLASTICS 53CLOSED MOULDING TECHNOLOGY 93-94COCKPIT ARMOUR PANELS 126COLD-BONDING 126COLLECTABLE VOLATILE CONDENSABLE

MATERIALS 79COMPOSITE FLAW DETECTION EXPERIMENTS 27COMPOSITE MATERIAL, AEROGEL-LIKE 29COMPOSITE STRUCTURES 44COMPOSITES, MARCEL FORMATION 107COMPOSITES, POLYIMIDE 56COMPOSITES, THERMOPLASTIC 129COMPRESSION AFTER IMPACT 51COMPRESSION MOULDING 12, 124COMPRESSION TESTING 82CONDUCTING POLYMER, INFRARED

ELECTROCHROMICS 102CONDUCTING POLYMERS 38, 44, 69COPOLYMERISATION 8CORONA PLASMA TREATMENT 49CORROSION 25 FILIFORM 25CORROSION-RESISTANT GLASS 4COUPLING AGENT 5, 6CRYOGENIC TEMPERATURE 66CRYOGENIC COMPOSITE 29CRYOGENIC FUEL TANK 57CRYOGENIC IZOD IMPACT TESTING 48CRYOGENIC STORAGE TANKS 52CRYOGENS 77CRYSTALS, OPAL PHOTONIC 30COEFFICIENT OF THERMAL EXPANSION 7CURE PROCESS 31-32 DUAL 47CYANATE EPOXY COMPOSITES 60CYANATE ESTER RESIN 123, 127CYANATE ESTERS 8, 66, 112, 115-116CYANOACRYLATE ESTERS 8

Index


DDAMAGE TOLERANCE ANALYSIS 125DARCY’S LAW 52, 90DELAMINATED CRACK OPENING

DISPLACEMENT 57, 90DIAPHRAGM FORMING 12DIAPHRAGM MOULDING 124DICYCLOPENTADIENE 80DIELS-ALDER CYCLOPOLYMERISATION 42DIFFERENTIAL SCANNING CALORIMETRY 19, 22,

28, 29, 40, 42, 61, 67, 81-83, 120, 123DIGITAL RADIOGRAPHY 84DIGLYCIDYLETHER-TERMINATED 60DISCOTEX 41, 47DISCRETISATION METHOD 21DISPLACEMENT COMPATIBILITY MODEL 125DOUBLE CANTILEVER BEAM TESTS 21, 48DROP WEIGHT IMPACT TESTING 44, 62DYNAMIC MECHANICAL ANALYSIS 46, 61, 81, 120

EEDDY-CURRENT TESTING 57EEONFOAMS 44E-GLASS 4ELASTOMERS 57 FRICTION 39ELECTRICAL POTENTIAL METHOD 71ELECTRIPLAST 75ELECTRON BEAM CURING 85ELECTROSPINNING 23, 76ELECTROSTATIC CHARGE DISSIPATION 109ELECTROMAGNETIC INDUCED SHIELDING

POLYMERS 54ENGINEERED SANDWICH CORES 44ETHYLENE-PROPYLENE DIENE TERPOLYMER 31, 43EPOXY ADHESIVE JOINTS 25EPOXY BONDING 39EPOXY HYBRID NANOCOMPOSITES 26EPOXY MATRIX 24 TOUGHENED SYSTEMS 60EPOXY OLIGOMERS 54EPOXY RESIN 9, 32, 38-39, 48, 54, 67, 102, 104, 121, 126 ADAPTIVE FOAMS 36 GLASS FIBRE-REINFORCED 81EPOXY SHAPE MEMORY POLYMER FOAM 37EPOXY THERMOSET 8EPOXY-BASED SYNTACTIC PASTE 3EPOXY-BASED SYSTEMS 35EPOXY-CARBON FIBRE COMPOSITES 26EXFOLIATION 15, 78EXTRUSION, ONE-STEP PROCESS 123

FFABRICATION METHODS 12FABRIC, NON-CRIMPED 30, 51

FINITE ELEMENT ANALYSIS, MODELLING 43FINITE ELEMENT ANALYSIS, 2D 90FIBRE BRAGG GRATING SENSORS 27, 81FIBRE DRAWING 6FIBRE METAL LAMINATES 101FIBRE REINFORCED ELASTOMERS 86FIBRE REINFORCEMENT 12FIBREGLASS 7FIBRE-METAL LAMINATES 96FIBRE TYPES 3 CARBON-BASED FIBRES 3 CARBON FIBRES 3 HYBRID FIBRES 6 RESIN-IMPREGNATED FIBRES

(PREPREGS) 12 THERMOGRAPHY 12 INORGANIC FIBRES 4 BORON FIBRE GLASS FIBRE 4 QUARTZ FIBRE 4 POLYMERIC FIBRES 5 ARAMID FIBRE 5 POLYARYL ETHER ETHER KETONE 6 POLYBENZOTHIAZOLE 5 POLYPHENYLENE-2,

6-BENZOBISOXAZOLE 5 ULTRAHIGH MOLECULAR WEIGHT

POLYETHYLENE 6FICKIAN DIFFUSION MODEL 117FILAMENT WINDING 9, 95 FILM, POLYCYANATE SYNTACTIC 57FIREPROOF INJECTION-MOULDING

THERMOPLASTICS 81FIRST-ORDER SHEAR DEFORMATION THEORY 21FIXED ARM PEEL TEST 88FLAME-RETARDANT EPOXY PASTE 3FLASH THERMOGRAPHY 57FLAX FIBRES 47 EPOXY PREPREGS 47FLUOROCARBON RUBBERS 50FLUOROELASTOMERS 31, 43, 95, 100, 103-104,

114-115, 128FLUOROPOLYMER COATINGS 102FLUOROPOLYMERS, HI-TECH 95FLUOROSILICONE ELASTOMER 20, 42FLUOROSILOXANE SEALANTS 50FOAMS 16FOURIER TRANSFORM INFRARED

SPECTROSCOPY 42, 46, 58, 60, 65, 75, 83, 122FOURIER TRANSFORM INFRARED ANALYSIS 9FRACTURE TOUGHNESS TESTS, INTERLAMINAR 48FRACTURE TOUGHENING 27

GGAS PERMEABILITY 52, 92GEL PERMEATION CHROMATOGRAPHY 42,

58GLASS FIBRES 6, 50 HOLLOW 59

Index


GLASS TRANSITION TEMPERATURE 28GLOBAL ENERGY-BALANCE ANALYSIS 82GRAPHITE-EPOXY LAMINATE SYSTEM 90GRAPHITE EPOXY MOTOR 32GRAPHITE-EPOXY RESIN COMPOSITES 36

HHALPIN-TSAI EQUATIONS 92HALPIN-TSAI MICROMECHANICAL MODEL 72HEAT DEFLECTION TEMPERATURE 65HEAT DISTORTION TEMPERATURE 6HELIUM FLOW DETECTION 93HEPHAISTOS 91HEXFORCE 42HEXMC 30HIGH STRAIN RATE LOADING 68HXPLY M50 95HYBRID POLYMERS 48HYBRID SILICONES 73HYBRID YARNS 62HYDROSILATION 48HYGROTHERMOELASTIC STRESS 43HYSOL EA9658 47

IIMI SPRAY MOULD PROGRAMME 120IMPACT TESTING 86INDENTATION DEBONDING TESTS 48INDIUM TIN OXIDE 13INFRARED SPECTRAL TRANSMISSION 23INFRARED SPECTROSCOPY 123, 126INJECTION MOULDING 101, 119INSTRON MECHANICAL TESTING MACHINE 51INTERLAMINAR SHEAR STRENGTH 51INTERPENETRATING POLYMER NETWORKS 123ION BOMBARDMENT 39ISOTHERMAL RHEOMETRIC ANALYSIS 19

KKAPTON 25KEVLAR 5 ARAMID FIBRE 106 FIBRE 49KYDEX THERMOPLASTIC SHEET PRODUCTS 61

LLAMB WAVE SENSING 81LAMINATE THEORY 21LAP SHEAR STRENGTH TESTING 66-67LAUNCH VEHICLES 31LAUNCH VEHICLES, EXPENDABLE 90LICOCENE 93LIFE PREDICTION TECHNIQUE 20

LIGHTNING STRIKE PROTECTION 68LIQUID COMPOSITE MOULDING PROCESSES 124LIQUID CRYSTAL POLYMERS 128LIQUID CRYSTALLINE POLYMERS 87LIQUID CRYSTALLINE THERMOSET 67LIQUID MOULDING PROCESSES 118LIQUID PERFLUOROETHER ELASTOMER 114LIQUID SILICONE RUBBER 20 FLUORINATED 33, 38-39, 42LIQUID-IMPACT TEST METHODS 111LOAD-DISPLACEMENT CURVE 70LOW EARTH ORBIT ENVIRONMENT 25

MMAGNESIUM ALUMINOSILICATE GLASS 4MANDREL PEEL TESTS 82MASKING TAPE 116MATCHED DIE MOULDING 12, 124MATHEMATICAL MODELLING 82MATLAB PROGRAM 52MATRIMID 11MATRIX POLYMER 7, 15MATRIX RESIN 12MATRIX SYSTEMS, BIFUNCTIONAL EPOXY-

AMINE 28MELAMINE RESIN FOAMS 72MELT MIXING 92MELT PROCESSING 15METAL SPRAY TOOLING 119METALLOCENE WAXES 93METAL-TO-METAL BONDING 3MICRO-COMPUTED TOMOGRAPHY SCANS 36MICROSPHERES 29MIYANO’S ACCELERATED TESTING

METHODOLOGY 20MODULAR TOOLING 111MONOMERS, ALKYNE-CONTAINING 35MORPHING 36, 38MOULDING, BLADDER 12MOULD PLATE, ALPASE M-1 118

NNANOCLAYS, MODIFIED MONTMORILLONITE

13-14NANOCOMPOSITES 13 CLAY-POLYIMIDE 128 SHAPE MEMORY POLYMER 70NANOFIBRE, ALUMINIUM-COATED

POLYVINYLALCOHOL 23NANOFIBRES, ELECTROSPUN 76NANOINDENTATION TESTING 70NANONET 25NANOPLATELETS, GRAPHITE 14NANO-REINFORCEMENTS, GRAPHITE 54NANO-SCALE MATERIAL 26NANOSILICA 14

Index


NANOSILICA CARBON NANOFIBRE 13NANOTECHNOLOGY 38NATURAL FIBRE 122NITRILE-BUTADIENE RUBBER 92ND:YAG LASER DEVICES 40ND-YAG LASER DRILLING 23NEURAL NETWORKS 112NEW GEN TECHNOLOGY 34NITRILE RUBBER 31, 39NOMEX 5NON-DESTRUCTIVE INSPECTION METHODS 27NON-DESTRUCTIVE TESTING 12NORYL POLYPROPYLENE OXIDE, FLEXIBLE 84NUCLEAR MAGNETIC RESONANCE

SPECTROSCOPY 58, 74, 83

OOPTICAL ANISOTROPY 113OPTICAL IMAGE CORRELATION 89OPTICAL MICROSCOPY 86OUTGASSING 46, 64OXYDIANILINE-MODIFIED CLAY 16

PPARMAX SRP 87, 94, 102, 104PEEL AND WEDGE TESTS 89PEEL TESTS 49, 66-6786, 88PERMAPOL P3.1 POLYMERS 102PHENOLIC POLYMER 98PHENOLIC RESIN 9, 30, 46, 121,127PHENOLICS 8PHENYLETHYNYL-TERMINATED

POLYETHERIMIDE (ULTEM) 63PHENYLETHYNYL-NAPHTHALIC ANHYDRIDE 69PHENYL VINYL METHYL SILICONE 55PHOTOCURING 42PHTHALIC ANHYDRIDE 121PHTHALONITRILE RESINS 8-9 OLIGOMERIC 19, 104PHYSICAL VAPOUR DEPOSITION 23PIEZOCOMPOSITE ACTUATORS 36PLASMA ETCHING 5PLASMA TREATMENT 3, 5, 7PLASTICISATION 25PLASTICS, FIRE RESISTANT, NON-HALOGEN 28PLASTICS, SELF-HEALING 114PMR-15 RESIN 20, 73POLYACRYLONITRILE PRECURSORS 4POLYAMIDEIMIDES 12POLYAMIDES, AROMATIC 5POLYANILINE COMPOSITES 46POLYARYL ETHER KETONE KETONE 7, 11POLYARYL ETHER KETONES 117, 121POLYARYLATES 10POLYAZOMETHINES 33POLYBENZIMIDAZOLE 3, 8, 65

POLYBENZOTHIOZOLE 5POLYBENZOXAZOLES 8POLYCHLOROPRENE 31, 39POLYCHLOROTRIFLU-OROETHYLENE 31, 56POLYCONDENSATION 9-10POLYCYANATE FILM ADHESIVE 57POLYCYANATE RESIN 57POLYDIMETHYLSILOXANE 31POLYESTER CARBONATES, AROMATIC 10POLYESTER YARN 24, 30POLYETHERAMIDE ELASTOMER,

THERMOPLASTIC 39POLYETHERIMIDE 11, 25POLYETHER ETHER KETONE 11POLYETHER KETONE KETONE 7, 11, 19, 63-64, 66,

71, 87, 107-108, 121, 128, 130POLYETHER KETONE, THERMOPLASTIC 27POLYETHERS, AROMATIC 120POLYETHYLENE 31POLYHEDRAL OLIOGOMERIC SILSESQUIOXANE

13-14POLYIMIDES 3, 7-9, 11, 95, 122 AROMATIC 113 CARBON NANOTUBE COMPOSITE FILMS 52 CLOSED-CELL FLUORINATED 30 COMPOSITES 128-129 ELECTROACTIVE 26 FILMS 58 HIGH-TEMPERATURE 92PREFORM JOINTS 24 RESINS 10 THERMOPLASTIC 11POLYKETANILS 33, 60POLYMER BLENDS 118POLYMER-CLAY NANOCOMPOSITES 48-49, 61-62POLYMER COATING 29POLYMER COMPOSITES 129POLYMER FOAMS 99POLYMER FOAM, ADAPTIVE 36POLYMER MATRIX 13, 31, 43, 52, 57, 106, 128 COMPOSITES 85 COMPOSITES, HIGH-TEMPERATURE 73POLYMER NANOTECHNOLOGY 28POLYMER, RIGID-ROD 101POLYMER, SELF-REINFORCED 87, 94POLYMERS, AROMATIC 117POLYMERS, AROMATIC KETONE 7POLYMERS, FIRE RESISTANT 83POLYMERS, HYDROPHILIC 106POLYMERIC NANOCOMPOSITES 96, 125POLYMERISATION 8, 19, 83-84, 105, 114, 123 CONDENSATION 5, 8 DRY 61 IN SITU 14, 92 IN SITU, INTERCALATIVE 48 WET 61POLYMER-MATRIX COMPOSITE 90POLYMERS, LOW-DIELECTRIC 126POLYMETHACRYLAMIDE 16, 78, 112

Index


POLYMETHACRYLIMIDE FOAMS 78, 98, 112POLYOXYMETHYLENE 31POLYPHENYLENE-BENZOBISOXAZOLE 3, 5 BRAIDED CORD 53 FIBRES 5, 129POLYPHENYLENE SULFIDE 12 THERMOFORMING 84POLYPROPYLENE, FIRE RETARDANT 59POLYQUINOLINES 8POLYSULFIDES 3POLYSULFONES 12 NANOCOMPOSITES 16POLYTETRAFLUOROETHYLENE 31, 51 COMPOSITE 54POLYTRIAZOLE RESIN 59POLYUREA 90POLYURETHANE 50 FLEXIBLE FOAM 88 RETICULATED FOAM 37 SILYLATED 40POLYURETHANE ELASTOMER, THERMOPLASTIC 39POWDER INJECTION MOULDING 114PREPREG SYSTEM, SELF-ADHESIVE 95PREPREGS 9, 115PRESS-FORMING 12, 79PRESSURE-STRAIN MONITORING 93PRESSURE VESSELS, CRYOGENIC COMPOSITE

OVER-WRAPPED 29PRESSURISATION TEST 93PROCESSING OUT-OF-AUTOCLAVE 58PROMETA RESINS 80PROPARGYL ETHER NOVOLAC RESIN 46PULTRUSION 6, 12 RESIN TRANSFER MOULDING PROCESS 84PYROLYSIS 14, 46

RRADIO FREQUENCY INTERFERENCE 3RADIOGRAPHY 12RESIN FILM INFUSION 27, 64, 94, 123RESIN INFUSION 30, 58, 65, 113RESIN INJECTION LIQUID COMPOSITE

MOULDING PROCESSES 74RESIN INJECTION PROCESS 24RESIN TRANSFER MOULDING 9, 12, 31, 64, 72, 79-

80, 92, 94, 99, 110-111, 113, 124, 128-129 EX SITU 27RESINS, ELECTRON BEAM CURED 85RESINS, THERMOPLASTIC 10, 130REUSABLE LAUNCH VEHICLE 90, 121R-GLASS FIBRE (HIPER-TEX) 37RHEOMETRY 81ROHACELL FOAM 45 STRUCTURAL FOAM CORES 92 STRUCTURAL SANDWICH CORES 78ROTATIONAL MOULDING INDUSTRY 80

SSAEFIX 42SAERTEX 42SCANNING ELECTION MICROSCOPY 23, 46, 63,

66-67, 74, 76, 94, 65, 120, 125SCHAPPE TECHNIQUE 41, 47SEALANTS 104SENSOR PAINTS 23S-GLASS 4SHAPE MEMORY ALLOY, 25, 34, 94 FOIL ACTUATORS 124SHAPE MEMORY POLYMERS 22, 36, 58, 67, 88SHEAR MIXING 14SHEAROGRAPHY 57SHEAR-TENSION TESTS 126SHEET MOULDING 9SILICON-CONTAINING COUPLING AGENTS 7SILICONE RESINS 3SILICONE RUBBER 39, 55SKIN-FOAM-SKIN COMPOSITE 48SKYDROL HYDRAULIC FLUID 11SMALL ANGLE X-RAY SPECTROSCOPY 48SNAP CURE SYSTEMS 66, 91SOLAR SELECTIVE COATINGS 109SOL-GEL METHODS 40, 66SPECTROSCOPY, BROADBAND DIELECTRIC 38SPECTROSCOPY, ELECTROCHEMICAL

IMPEDANCE 107SPLIT HOPKINSON PRESSURE BARS 51, 117STRUCTURAL REACTION INJECTION MOULDING 93STYRENE-BUTADIENE RUBBER 31, 92SUPERSONIC VEHICLES, EXO-ATMOSPHERIC 43SURFACE CLEANING 71SURFACE OXIDATION 5SURFACE TREATMENT TECHNIQUE 88SURFI-SCULPT 88SYNTACTIC FOAMS 46

TTAKAYANAGI’S TWO-PHASE MODEL 119TAPE LAYING 12TAPE PEEL TEST 21TENSILE LOADING 93TEXTILE COMPOSITES, SINGLE LAYER 123T-GLASS 4THERMAL AGEING 75THERMAL CYCLING 117THERMAL IMAGING 28THERMAL TRANSPORT PHENOMENA 19THERMO-FOLDING 79THERMOFORMABLE SANDWICH PANELS,

FOAMED IN SITU 72THERMOFORMING 12THERMOGRAPHY 84THERMOGRAVIMETRIC ANALYSIS 8, 19, 42, 46,

61, 67, 83, 94, 100, 117, 120, 127,

Index


THERMOGRAVIMETRY/FOURIER TRANSFORM INFRARED 122

THERMOMECHANICAL ANALYSIS 42THERMO-OXIDATIVE AGEING 10THERMOPLASTIC COMPOSITE TECHNOLOGY 41THERMOPLASTIC MATRICES 10THERMOPLASTIC POLYMERS 8THERMOPLASTIC RESINS 7-8THERMOPLASTIC, SELF-REINFORCING 104THERMOSET COMPOSITES 113THERMOSET MELAMINE FOAM 74THERMOSET RESIN SYSTEM 115THERMOSETS 8THERMOSETTING MATRICES 8THERMOSETTING RESINS 13, 19THREE-DIMENSIONAL BRAIDED PRODUCTS 41THREE-DIMENSIONAL CRACK TIP ELEMENT

ANALYSIS 81THREE-DIMENSIONAL FIBRE-REINFORCED

POLYMER COMPOSITES 93TITANATE COUPLING AGENTS 7TORSION BRAID ANALYSIS 67TOUGHENING 47TOUGHENING AGENTS 9TOW PATH OPTIMISATION 24TRANSMISSION ELECTRON MICROSCOPY 23, 48,

74, 92, 127-128TRIPLE-PLY TAPE 59TUBULAR BRAIDING 79TUFFOAM 70

UULTEM RESINS 50, 99ULTRA HIGH MOLECULAR WEIGHT

POLYETHYLENE 5, 7ULTRASONIC TESTING 57UPILEX 25URETHANE RESIN 29

VVACUUM ASSISTED RESIN TRANSFER

MOULDING 27, 31, 54, 65-66, 75, 80, 85, 101, 103, 108, 118, 124

VACUUM INFUSION PROCESS 93, 98 MOULDING 99VACUUM INJECTION MOULDING 103VANE CASCADE EROSION RIG TESTS 85VAPOUR-GROWN CARBON FIBRE 4VARIABLE ANGLE FIXED ARM PEEL 82VIBRATION DAMPING 21 MEASUREMENTS OF 81VISCOSITY, BROOKFIELD 129

WWATER JET TEST METHOD 111WATER VAPOUR TRANSMISSION 23WATER-BASED NON-CHROMATE PRIMER 55WAVELET MAPS 112WIDE ANGLE X-RAY DIFFRACTION 19

XX-COR 62X-RAY PHOTOELECTRON SPECTROSCOPY 49X-RAY DIFFRACTION 46, 92, 94, 125, 127-128X-RAY RADIOGRAPHY 57XYTREX 53YAKAYANAGI’S MODEL 119

YYOUNG’S MODULUS 72

ZZENITE 127ZERILLI-ARMSTRONG MODEL 51ZYLON 5

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