AIR CRAFT MATERIAL COMPOSITION

AVIATIONMATERIAL COMPOSITION PREPARED BY :GUNJAN TRIVEDIM.TECH DESIGN ENGINEERING

PASSANGER AIRCRAFT

http://www.1001crash.com/index-page-composite-lg-2.html2PASSANGER AIRCRAFTNONAME OF PARTMATERIAL USEDPROPERTIES REASON 1.FUSELAGEAlMgSiCu (AA6013) T6WeldableIncreased Yield Strength Reduced Fatigue Crack Growth Rate Higher Toughness Lower DensityWeight Reduction ,High value of specific Strength2.RUDDER, WINGS,AILERONS, TAIL CONE, FLAP TRACK PANEL , LANDING GEAR DOORS , WING RIBS , CENTER WING BOX , ENGINE COWLINGS , REAR PRESSURE BULK HEADCarbon fiberreinforced polymer

strength and rigidityhigh initial strength-to-weight ratioextremely light and rigidlighter and stronger than their metal counterparts3.HORIZONTAL AND VERTICAL STABILIZER Aluminium 7075 T6density of 2.810 g/cmUtm 74,00078,000 psiyield strength of at least 63,00069,000 psiHighly Stress Structure4.FLOOR PANELS , FUEL TANKS S-2 Glass fiberSoftening point: 1056C (1932F) , Annealing point: 816C (1500F) , Strain point: 766C (1410F)Greater fiber tensile strength and stability at elevated temperatures in thermoset and thermoplastic applications5.Engine Titanium , Inconel 65highstrength,stiffness,toughness, low density, and goodcorrosion resistancehigh strength-to-weight ratio.6.Wind Shield PLEXIGLASGS 241UV transmittance less than 1 %,high optical standardsBetter Visibility and Toughness 3MILIATRY AIRCRAFT

http://www.tejas.gov.in/MILITARY AIRCRAFTSR. NO.NAME OF PARTMATERIAL USEDPROPERTIES Reason1.Leading and Trailing edgeS 2 Glass Fiberhigh strength, modulus and durability under conditions of extreme temperature of corrosive environmentsFor radar absorption2.Wing , Fuselage and Tail skinAS4/3501 06 Carbon -Epoxy

Density 1.265 gm/cc Tg dry 6 hr 350F (177C) cure 410F (210C) Tg wet 6 hr 350F (177C) cure 304F (151C) Tensile strength 6.6 ksi Tensile modulus 0.615 msiConsidering Higher Tensile Strength ,

Test result on Cessna 180Result : 3.8 KsiF.O.S. 1.733.Engine Bay RegionBMI RM 3010Cured Resin Density 1.25 g/cc Glass Transition Tg (G) 72 hr, 180F immersion Dry: 534F Wet: 485F Resin Flex Strength 18 ksi Resin Flex Modulus 665 ksi Resin Flex Strain to Failure 2.5%High Temperature Resistance 4.Fuel Tank , Frame , WallsRTM method Inner liner of synthetic rubber or rubber-coated fabric, Ballistic nylon barrier, Sealant, and a Retainer of woven nylon cord. Lightweight Bladder, Self-Sealing, and Crash Resistant.

Fuel Resistance , High Pressure Sustain in Speed, Crash Resistance 5.NoseFibre GlassE Glass ,S - Glasshigh strength, modulus and durability under conditions of extreme temperature of corrosive environments

performance over narrow frequency bands,high-quality RF performance

http://www.faqs.org/patents/app/20140197280UnmannedAerialVehicleUnmannedAerialVehicleSR. NO.NAME OF PARTMATERIAL USEDReason UAV TypesTarget and decoy- providing ground and aerial gunnery a target that simulates an enemy aircraft or missileReconnaissance- providing battlefield intelligenceCombat- providing attack capability for high-risk missions (see Unmanned Combat Air Vehicle)Research and development- used to further develop UAV technologies to be integrated into field deployed UAV aircraftCivil and Commercial UAVs- UAVs specifically designed for civil and commercial applications.1Body / Frame , Wings Wood , Form , Plastic , Aluminium , G10 , Carbon Fibre , Carbon Fiber Skin ,Depends Upon Size and DesignHELICOPTER

https://commons.wikimedia.org/wiki/File:Merlin_Airframe_Material.jpgHELICOPTERSR. NO.NAME OF PARTMATERIAL USEDPROPERTIES REASON1.ROTOR BLADESandwich Design with GFRP , CFRP , FORM , GREEN NOMEX HONEYCOMB CORE , SS EROTION SHEILD , WOVEN GLASS OUTER SHIELD ductile, relatively soft and with quite a high plasticityTo provide high stiffness under rotation tip velocity of 200m/s and Flipping also in Environmental condition such humidity and temperature , it provide better vibration characteristics of blade 2Airframes, empennageCFRP Sandwich panelsductile, relatively soft and with quite a high plasticity

Light Weight3.Nose, Exhaust, Wind Shield

Kevlar 49 / epoxy Nomex/PolycarbonateHigh modulus / High Temp Resistance , Density 1.44 g/cc , UTS 3000MPA , Tensile Modulus 112 GPA ,

For better visualization and bullet proof , Ultra High Temperature

4.CabinWeldalite 049 /Alloy 2090 /Alloy 2091 / Alloy 8090 Alloy Frames Higher stiffness , Superior fatigue crack growth resistance , Reduced ductility For Minimizing Vibration And Damping5.Tail BoomWeldalite 049 /Alloy 2090 /Alloy 2091 / Alloy 8090 Alloy Frames Higher stiffness , Superior fatigue crack growth resistance , Reduced ductilityTo resist exhaust impingement temps and reduce empty weight fraction GLIDER

https://en.wikipedia.org/wiki/Glider_(aircraft)GLIDER SR. NO.NAME OF PARTMATERIAL USEDSPECIFIC USE1.Frame, Wing Span Basla Wood ,A Grain ,B Grain ,C GrainMaking Light Weight2. Frame CoverThin sheet of Basla or Thick Plastic FilmProviding bending and torsional strength , Desired airfoil shape3.CoreDow Styrofoam High load 60 insulationFor good Compressive strength4.Skinfibreglass cloth , carbon-fiber clothAerodynamic ShapeHOT AIR BALOONhttps://en.wikipedia.org/wiki/Hot_air_balloon

HOT AIR BALOONSR. NO.NAME OF PARTMATERIAL USEDPROPERTIES Reason1.Balloon Envelope , Gores , Parachute Valve Nylon / Polyester / Nomex (Near Gas Burner )Polyester good aging resistance at high temperaturesNylon superior elasticity, stronger rip resistance and the durability,UV stability, colour brilliance, fungus resistance or dirt resistanceNo UV Radiation when heated 2.Wicker Basket woven from Kooboo and Palambang cane , Aluminiumextremely sturdy, flexible and relatively lightweightLight weight ConstraintSUPER SONIC AND HYPERSONIC AIRCRAFT

https://en.wikipedia.org/wiki/Supersonic_speedhttp://seit.unsw.adfa.edu.au/ojs/index.php/Hypersonics/article/viewFile/21/12

HYPERSONIC AIRCRAFTSR. NO.NAME OF PARTMATERIAL USEDPROPERTIES SPECIFIC USE1.Inward Turning Inlet of Scam Jet EngineTZM Molybdenum

0.50% Titanium, 0.08% Zirconium and 0.02% Carbon with the balance Molybdenumhigh strength/high temperature applications, especially above 2000F2.truss structures Rene 41 super alloy temperature strength up to 980CHeat Absorption3.Body PartsTitanium-Aluminium alloy above 650C, the alloy has a high solubility with oxygenWeight Reduction4.thermal protection systems Hafnium Diboride and Zirconium Diboride high melting point of approximately 3200Coxidation resistance at temperatures up to 2000CFor Protection of system under high temperature5.Complex Body StructureCarbon/Silicon Carbide ceramic matrix compositeconstant strength to weight ratio up to 1600CDesign Complex body parts 6.NoseTAZ-8A Cermet minute oxidation build up of 1.8 milligrams per square centimetre of alloy when exposed to 1900 F Nose cone7.Propulsion SystemTitanium Metal Matrix Composite withstanding thousands of hours of cyclic loading in an oxidative environmentPropulsion temperature up to 3000CSUMMARY Composite parts used for aircraft applications are defined by Material, process, and manufacturing specifications. Material allowable (engineering definition).

All of these have a basis in regulatory requirements.Most efficient use of advanced composites in aircraft Most efficient use of advanced composites in aircraft structure is in applications with Highly loaded parts with thick gages. High fatigue loads (fuselage and wing structure, etc). Areas susceptible to corrosion (fuselage, etc). Critical weight reduction (empennage wings fuselage etc) Critical weight reduction (empennage, wings, fuselage, etc).

Use must be justified by weighing benefits against costs.References: PASSANGER AIRCRAFT

FUSELAGE :-

http://www.mat.ethz.ch/news_events/archive/materialsday/matday01/pdf/TempusMD.pdf http://www.wiley-vch.de/books/sample/3527313605_c01.pdf http://www.aluminiumleader.com/en/around/transport/aircraft

RUDDER, WINGS,AILERONS, TAIL CONE, FLAP TRACK PANEL , LANDING GEAR DOORS , WING RIBS , CENTER WING BOX , ENGINE COWLINGS , REAR PRESSURE BULK HEAD :-

http://www.ndt.net/article/aero2010/papers/tu1a4.pdf https://en.wikipedia.org/wiki/Carbon-fiber-reinforced_polymer#Properties http://www.carbonfiber.gr.jp/english/field/craft.html http://www.ndt.net/article/ecndt98/aero/015/015.htm http://www.carbonfiber.gr.jp/english/field/craft.html http://www.tapplastics.com/product_info/why_use_carbon_fiber

Continue...References: STABILIZER:-

http://www.ijirset.com/upload/2014/april/15_Static.pdf http://asm.matweb.com/search/SpecificMaterial.asp?bassnum=MA7075T6 https://en.wikipedia.org/wiki/7075_aluminium_alloy

FLOOR PANELS , FUEL TANKS :-

http://www.agy.com/wp-content/uploads/2014/03/449_S-2-Aerospace.pdf http://www.scielo.br/scielo.php?pid=S1516-14392013000500024&script=sci_arttext

ENGINE:-

http://www.iom3.org/materials-world-magazine/feature/2013/may/09/materials-through-ages-materials-aeroplane-engines http://link.springer.com/article/10.1007/BF00136790

WINDSHIELD :-http://www.plexiglas.de/product/plexiglas/en/products/solid-sheets/aircraft-materials/pages/default.aspxContinue... MILITARY AIRCRAFT:

LEADING AND TRAILING EDGE:-

http://www.agy.com/wp-content/uploads/2014/03/Mechanical_Properties_of_Polymeric_Composites-Technical.pdf https://books.google.co.in/books?id=5SPAIKFmFjcC&pg=PA436&lpg=PA436&dq=military+aircraft+fix+trailing+edge+material&source=bl&ots=KFJouzrSu2&sig=-I1-1urQCQW261f6vrZdZi3eXCE&hl=en&sa=X&ved=0CB4Q6AEwAGoVChMI1oytiaatxwIVynKOCh3DWw_C#v=onepage&q=military%20aircraft%20fix%20trailing%20edge%20material&f=false

WING , FUSELAGE AND TAIL SKIN :-

http://www.hexcel.com/Resources/DataSheets/Prepreg-Data-Sheets/3501-6_eu.pdf https://books.google.co.in/books?id=JLogBQAAQBAJ&pg=PA237&lpg=PA237&dq=FATIGUE+VALUE+RECOMMENDED+ON+AIRCRAFT+WING&source=bl&ots=V6h63OkUQJ&sig=B9s8vYxrS2tqavmmLqAFTRPILtA&hl=en&sa=X&ved=0CC4Q6AEwA2oVChMI79GTtK-txwIVRAiOCh0i8wnZ#v=onepage&q=FATIGUE%20VALUE%20RECOMMENDED%20ON%20AIRCRAFT%20WING&f=false Continue...

References: Engine Bay Region :-

http://www.compositesworld.com/articles/resin-infused-ms-21-wings-and-wingbox

FUEL TANK , FRAME , WALLS :-

http://www.ffcfuelcells.com/aircraftfueltanks1.asp

NOSE :-

http://www.azom.com/article.aspx?ArticleID=12107 http://www.selkirk-aviation.com/nosebowls.html

Continue...References: UNMANNEDAERIALVEHICLE

BODY / FRAME , WINGS

http://www.robotshop.com/blog/en/make-uav-lesson-2-platform-14448 http://www.theuav.com/

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References: HELICOPTER

http://classroom.materials.ac.uk/caseRoto.php https://books.google.co.in/books?id=e1id9bKG100C&pg=PA31&lpg=PA31&dq=kevlar+nomex+for+helicopter+nose&source=bl&ots=Vi4de1JRzJ&sig=qdYKggCcYRO68mX9xXTPowt2-74&hl=en&sa=X&ved=0CDUQ6AEwA2oVChMIi4Lvru6txwIVwxqOCh3NUQF2#v=onepage&q=kevlar%20nomex%20for%20helicopter%20nose&f=false http://www.ncn-uk.co.uk/uploads/michael%20Overd.pdf http://esaform2008.insa-lyon.fr/proceedings/MS12/p_Du_473.pdf http://www.metalwebnews.com/howto/alloys/alloys.pdf

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References: References: GLIDER

http://www.modelaviation.com/freeflightmaterials

HOT AIR BALOON

http://www.schroederballon.de/en/dates-impressions/schroeder-news/nylon-or-polyester.html \http://www.eballoon.org/balloon/basket.html http://www.eballoon.org/balloon/how-it-works.html

SUPER SONIC AND HYPERSONIC AIRCRAFT

http://seit.unsw.adfa.edu.au/ojs/index.php/Hypersonics/article/viewFile/21/12

LESSON LEARNT Able to know what design approach should be made for selection of materialUnderstood the requirement of specific material for specific applicationLearned about the how important is case study for using specific material Able to understand about the Composite sandwich , how they are useful in different loading , force and thermal situation.Able to understand what are the constraint for selection of material . i.e. Cost , Manufacturing , Availability etc.Learned about different parts of aviation i.e. Aircraft parts , Hot air balloon parts.Learned about new material.