sme1- metallic materials

8/18/2019 Sme1- Metallic Materials

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Materials and sheet2

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Content of presentation

" Materials properties

" Constraints on materials

" Surface #nis!es

" coatings" $oining

" Corrosion testing

" Mec!anical testing

" Macroscopic e%amination

" Microscopic e%amination

" &on'destructive e%amination

" (ailure analysis


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Materials Properties

" Strengt!

" Elastic modulus

" (atigue

" (racture toug!ness

" Creep

" Micro'yielding

" Coe)cient of t!ermale%pansion and coe)cient ofmoisture e%pansion

" Stress corrosion

" Corrosion fatigue

" *ydrogen em+rittlement

" ,ear and fretting

" Surface #nis!es- Anodising

- Conversion

- pic.ling/etc!ing- mec!anical

" Coatings- !ard

- +arriers


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Metallic Materials used in space

" 0ig!t metals1 suc! as +eryllium1 magnesium1 aluminium andtitanium and t!eir alloys

" Steels1 suc! as lo2'alloy1 tool1 corrosion resistant1 precipitation!arda+le1 and maraging

" &ic.el and nic.el +ase alloys1 including pure nic.el1 Monelalloys1 Inconel alloys1 and ot!er nic.el' and co+ald'+asesuperalloys

" Refractory metals1 principally nio+ium and moly+denum

" Copper'+ase alloys1 including pure coppers1 +eryllium coppers1

+ron3es and +rasses" Precious metals

" ,elding1 +ra3ing and soldering alloys

" 4arious plating alloys


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Materials Properties cont55

" (racture Toug!ness- T!e fracture toug!ness is a measure of t!e

damage tolerance of a material containing

initial 6a2s or crac.s5 T!e fracture toug!nessin metallic materials is descri+ed +y t!e plain

strain value of t!e critical stress intensity

factor5 T!e fracture toug!ness depends on t!eenvironment5 7ic is t!e plain strain criticalstress intensity factor5 7iscc plain strain criticalstress intensity factor for a speci#edenvironment in 2!ic! environmentally induced

crac. gro2t! occurs5

" For homogeneous materials the Kic or

Kiscc shall be measured according toECSS- Q- 70- 45.

" Metallic materials for use in corrosiesurface enironments shall be tested for

fracture toughness under re!resentatieconditions

Typical su+critical crac. propagation rateversus stress intensity relations!ip5 Stressintensity 71 is de#ned as 78Aσ√9πC/;1 2!ere σ is t!e total tensile stress1 C is t!e crac. lengt!1and A and are geometrical constants


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Materials and sheet

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" Coe)cient of t!ermal e%pansion andcoe)cient of moisture e%pansion

- T!e di


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Materials and sheet!

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" Mec!anical contact surface e


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Materials and sheet"

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" Stress Corrosion Crac.ing- Stress corrosion may+e de#ned as t!e com+ined action of sustained tensile stress and

corrosion t!at may lead to t!e premature failure of materials5 Certain materials are moresuscepti+le t!an ot!ers5 If a suscepti+le material is placed in a corrosive environmentunder tension of su)cient magnitude1 and t!e duration of service is su)cient to permit

t!e initiation and gro2t! of crac.s1 failure 2ill occur at a stress lo2er t!an t!at 2!ic! t!ematerial 2ould normally +e e%pected to 2it!stand5 T!e corrosive environment need not+e severe in terms of general corrosive attac.5

- Service failures due to stress corrosion are freuently encountered in cases 2!ere t!esurfaces of t!e failed parts are not visi+ly corroded in a general sense5

- If failure is to +e avoided1 t!e total tensile strengt! in service must +e maintained at a

safe level5 T!ere is no a+solute t!res!old stress for stress corrosion1 +ut comparativestress'corrosion t!res!olds can +e determined for materials su+jected to controlled

conditions of test5 Estimates of t!e stress'corrosion t!res!old for a speci#c service

application must +e determined for eac! alloy and !eat treatment1 using a test piece1stressing procedure and corrosive environment t!at are appropriate for t!e intended

service5


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Materials and sheet#

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" Stress corrosion- Stress Corrosion Crac.ing 9SCC;1 de#ned as t!e com+ined action of a sustained tensile

stress and corrosion1 can cause t!e premature failure of metals5 T!e metallic

components proposed for use in most spacecrafts must +e screened to prevent failuresresulting from SCC5

- =nly t!ose products found to possess a !ig! resistance to stress'corrosion crac.ing may!ave unrestricted usage in structural applications5

- Materials intended for structural applications and li.ely to +e e%posed to a long'termterrestrial storage or 6o2n on t!e Space Transportation System1 fracture critical items1 allparts used or associated 2it! t!e fa+rication of launc! ve!icles s!all possess a !ig!

resistance to stress'corrosion crac.ing5

- Structural products of a metallic nature s!all +e selected from t!e preferred list in Ta+le I

of ECSS' >' ?@' B5


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Materials and sheet1$

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Specimen orientation and fracture plane identi#cation5 01 lengt!1 longitudinal1 principal directionof metal 2or.ing 9rolling1 e%trusion1 a%is of forging; T1 2idt!1longtransverse grain direction S1 t!ic.ness1 s!orttransverse grain direction C1 c!ord ofcylindrical cross section R1 radius of cylindrical cross section5 (irst letter: normal to t!e fractureplane 9loading direction; second letter: direction of crac. propagation in fracture plane5


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" SCC ta+le I- Materials t!at testing and e%perience !ave s!o2n to possess !ig! resistance to stress'

corrosion crac.ing5 T!eir use is given reference5

" SCC ta+le II- Alloys and tempers listed in ta+le II are moderately resistant to stress' corrosion

crac.ing5 T!ey s!ould +e considered for use only in cases 2!ere a suita+le alloy cannot+e found in Ta+le I5

" SCC ta+le III- Materials listed in ta+le III !ave found to +e !ig!ly suscepti+le to stress' corrosion

crac.ing5 T!ey s!ould +e considered for use only in applications 2!ere it can +edemonstrated conclusively t!at t!e pro+a+ility of stress corrosion is remote +ecause of

lo2 sustained tensile stress 92!atever its origin; in critical grain directions1 suita+leprotective measures or an innocuous environment5


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Constraints on materials

" Temperature

" 4acuum

" T!ermal cycling

" C!emical 9corrosion;

" alvanic compati+ility

" Atomic o%ygen" Moisture a+sorption/desorption

" (luid compati+ility


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Constraints on materials1 cont55

" Temperature- T!e range of temperatures e%perienced 2ill play a large part in t!e materials selection5

E%tremes are illustrated +y t!e e%amples of cryogenic tan.s and t!ermal protectionsystems for re'entry applications5 Temperatures +elo2 room temperature generallycause an increase in strengt! properties1 !o2ever t!e ductility decreases5 Ductility and

strengt! may increase or decrease at temperatures a+ove room temperature5 T!isc!ange depends on many factors1 suc! as temperature and time of e%posure5

- Materials s!all +e compati+le 2it! t!e t!ermal environment to 2!ic! t!ey are e%posed5

- Passage t!roug! transition temperatures 9e5g51 +rittle'ductile transitions or glasstransition temperatures including t!e e


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Constraints on materials cont55

" T!ermal cycling- T!ermal cycling can induce t!ermal stresses and due to t!e di


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" alvanic compati+ility- If t2o or more dissimilar materials are in direct electrical contact in a corrosive solution

or atmosp!ere galvanic corrosion mig!t occur5 T!e less resistant material +ecomes t!eanode and t!e more resistant t!e cat!ode5 T!e cat!odic material corrodes very little ornot at all1 2!ile t!e corrosion of t!e anodic material is greatly en!anced5

"Material com!atibilities shall be selected in accordance 'ith ECSS- Q-70-7()" Ma*imum !otential di$erences shall be in accordance 'ith ECSS- Q-70-7()

- In t!e construction of a satellite1 t2o metals t!at form a compati+le couple may !ave to

+e placed in close pro%imity to one anot!er5 Alt!oug! t!is may not cause anomalies ormalfunctions in t!e space environment1 it !as to +e +orne in mind t!at spacecraft often

!ave to +e stored on eart! for considera+le periods of time and t!at during storage t!eymay inadvertently +e e%posed to environments 2!ere galvanic corrosion can ta.e place5In fact1 t!is is .no2n to !ave ta.en place on several occasions and it is for t!is reasont!at t!e Agency !as +een studying t!e dangers involved5

" See also paragrap! a+out Corrosion


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" procedure- a simpli#ed procedure can +e used to estimate t!e

compati+ility of a +imetallic couple +y ta.ing into

account t!e di


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" Atomic o%ygen- Spacecraft in lo2 eart! or+it 90E=; at altitudes of +et2een H@@ .m and ?@@ .m are

e%posed to a 6u% of atomic o%ygen5 T!e 6u% level varies 2it! altitude1 velocity vector

and solar activity5 T!e 6uence levels vary 2it! t!e duration of e%posure5

" Moisture a+sorption/desorption- T!e properties of composite materials are suscepti+le to c!anges induced +y t!e ta.e'up

of moisture5 Moisture a+sorption occurs during production of components and launc! oft!e spacecraft1 desorption occurs in t!e space vacuum5

" (luid compati+ility- In some occasions materials are in contact 2it! liuid o%ygen1 gaseous o%ygen or ot!er

reactive 6uids or could come into contact 2it! suc! a 6uid during an emergency

situation5


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Materials and sheet1"

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Interfaces 9surfaces1 layers;

" Anodising

" C!emical conversion

" metallic coatings 9overlay and di


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Materials and sheet1#

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Surface #nis!es

" T!e surface #nis! of a component can in6uenceits mec!anical and environmental dura+ility5

" Anodising 9c!romic1 sulp!uric1 sulp!uricJo%alic;- Anodising is an electrolytic process for t!ic.ening and sta+ilising o%ide #lms on +ase metals

and anodising grade alloys5 It may +e used as a pre'treatment for painting and dying or as apassivation treatment for an electro'+rig!tened surface5

- *ard anodised layers are 2ear resistant and dura+le5

- lac. anodising 2it! co+alt sulp!ide and nic.el sulp!ide is used for controlling t!e optical

properties of surfaces5

" +igh solar absor!tance) high emmitnace

- T!e anodised layer is electrically non'conductive5

- T!e +at! constituents and process conditions may vary +et2een organisations5

- Caution s!ould +e e%ercised in anodising very t!in products suc! as foils

- Coatings are porous and needs sealing 9coating can release 2ater in vacuum;


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Surface #nis!es1 cont55

" C!emical conversion 9c!romate1 p!osp!ate; '- Commercial process 9alodine 1 irridite1 etc;

- C!emical conversion depends upon t!e a+sorption of a protective metal o%ide #lm into

an e%isting o%ide #lm +ut may include non'metals in some cases5- C!romating involves t!e formation of a mi%ed metal'c!romium o%ide #lm5 It !as a good

corrosion resistance and an e%cellent +ond to su+seuent organic coatings5

- P!osp!ating is primarily used as an underlayer for paint #nis!es5 It #nds little applicationfor corrosion protection5

- C!emical conversion coatings can +e eit!er electrically conductive or non'conductive5

- Temporary corrosion protection only

- simple and c!eap process

- may +e applied +y immersion1 praying1 +rus!ing1 2iping or any ot!er 2etting met!od


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Coatings1 cont55

" Metallic coatings 9overlay and di


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Coatings1 cont55

evaporation


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Coating1 cont55

,ear


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Coating1 cont55

" Moisture +arriers- Coatings can +e used to prevent moisture a+sorption or desorption of dimensionally sta+le

structures or to prevent t!e release of organic volatiles 2!ic! could a


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Coating1 cont55

" Depending on t!e design and service1 t!efollo2ing coatings are used:

- Paints

- p!osp!ate coatings

- c!romate coatings- electroless nic.el

- c!romium1 electroplated

- o%ides and +lac. o%ide

- nic.el/tin1 electroplated

- tin/lead

- electroless nic.el plus electroplated c!romium

- vapour'deposited aluminium

- metals1 suc! as gold1 silver1 palladium1 rodium

- lu+rication coatings suc! as +raycoat grease

- moly+denum disul#de

- car+ides and nitrides or com+ination


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$oining

" Mec!anical fastening

" onding

" Com+ined +onding and fastening

" (usion1 including 2elding1 +ra3ing1 solderingand di


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$oining cont55

" olted joints- olts o


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$oining cont55

" (usion tec!niues can +e grouped as:- soldering

- +ra3ing

- 2elding1 including di


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$oining cont55

" Soldering- Soldering is commonly referred to as soft soldering in 2!ic! lo2 melting point alloys suc!

as Tin'0ead or Indium +ased alloys are used5 Soldered joints are used for electrical andt!ermal conducting pat!s and for lo2 mec!anical strengt! joints5

- Soldering s!all not +e used for structural applications unless revie2ed and approved +yt!e Customer5

- See also ne%t session

" ra3ing- ra3ing is preferred to soldering in t!ose cases 2!ere a strong joint1 2!ic! is !eat

resistant is reuired5 As distinct from soft soldering +ra3ing usually refers to joining 2it!alloys of copper1 silver and 3inc

" ,elding- &umerous 2elding tec!niues are availa+le5 In t!e aerospace industry t!e follo2ingtec!niues are often used:

" ,ungsten nert as /, 'elding

" 1lasma-2rc 'elding

" Electron 3eam /E3 'elding ) laser 'elding

" esistance 'elding /induction) s!ot) seam 'elding) i$usion 'elding


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Corrosion Testing

" eneral Corrosion

" Stress Corrosion

" imetallic Corrosion

" Atomic =%ygen Corrosion

" Red Plague Corrosion


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eneral corrosion testing

Salt'spray'9foreground;and *umidity C!am+er'+ot! !ave temperatureand !umidity regulators


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Stress corrosion testing

Test setup for t!e alternate immersion testingof specimens in a 5FG &aCl solution

Al'0i stresscorrosion failure

Testing acc5 to ESAPSS'@'??


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imetallic corrosion testing

T!e +imetalliccorrosion +et2eent2o materials cantested in speci#cliuids and underany !umiditylevels5

T!e current and

voltage di


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Atomic =%ygen Corrosion

Materials for use in spaceapplications in lo2 eart! or+itand e%posed to t!e !ostilecom+ination of atomic o%ygenand t!ermal cycling !ave to +e

screened for t!eir suscepti+ilityto 2it!stand t!is environmentover very long periods


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Red plague testing

Red plague testing 9Ant!ony and ro2n test; is performed according toESA PSS'@'?H@

Test conditions: HL@ !rs at FO oC


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Mec!anical Testing

" *ardness testing

" Tensile Testing" Compression testing

" (atigue testing

" (racture Toug!ness

" T!ermal cycling


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Mec!anical Testing cont55

T!is euipment is more particularlydedicated to t!e testing of t!ermo'structural materials suc! as CMCmaterials5 It !as +een set up for

measuring tensile properties fromam+ient temperature up to B@@oC

under air5 Suc! a test is recognised to+e t!e most important for evaluatingmec!anical properties of CMC5

A ceramic matri% compositespecimen is clamped into self'aligning

2ater cooled grips5 It passes t!roug!a specially designed furnace a+le to!eat its cali+rated section to B@@oC5A !ig! temperature capacitive

e%tensometer made of ceramicspro+es permit strain measurements5


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Mec!anical Testing cont55

T2o units1 specially designed according

to to speci#cation ESA PSS'@'?@L1operate under vacuum5 T2o ot!er unitsoperate under atmosp!eric pressure5

T!e !eating and cooling is provided +ynitrogen gas5

=ne of t!e t2o systems fort!ermal cycling undervacuum 94MDI is s!o2n;5 T!esystem is provided 2it!vie2ing ports and electricfeed t!roug! connection5


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Macro/Microscopic E%amination

" Macroscopic 9 Q?F;

" 0ig!t microscopy

" Confocal microscopy

" Scanning Electron Microscopy


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Macroscopic E%amination

Magni#cation %?F- 4isual Inspection

- Stereo3oom

- Scanning Electron Microscopy at lo2

magni#cation

- P!otograp!y T!e diversity of samples su+mitted

for failure analysis is illustrated +y

t!is p!otograp!1 2!ic! featurespart of a defective spacecraft

antenna1 a nic.el cadmium +atterycell1 detector electrodes1 printed

circuit +oards1 fracture toug!nessspecimen1 part of a dip +ra3ed

2aveguide1 sections t!roug! asolar army !ydrogen em+rittled

springs and a composite structure

designed to 2it!stand t!e impactof particles travelling at B@ .m/s5


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Microscopic E%amination cont55

" 0ig!t Microscopy- metallurgical microscopy

" =ptical Microscopes Reic!ertMe(H: magn5 Q to QF@@1 Itincludes: interferometer1polarised lig!t illumination1micro'!ardness tester Reic!ertMe(a: magn5 Q to F@@ Itincludes: polarised lig!t

illumination1 dar. and +rig!t#eld illumination1 connection to

Cleme% Image analyser


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Confocal microscopy Confocal microscopy allo2s t!e us to

o+tain dept!'selective information on t!et!ree'dimensionial structure of amicroscopic o+ject5

0EICA TCS &T 2it! microscopeDM'RQE and galvanometerdriven K'stage5

T!e %/y resolution is @5O µm9(,*M; and a corresponding 3'resolution of +etter t!an @5F

µm 9(,*M; at LOO nm


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" In many situations even greater

magni#cations are useful5 T!iscapa+ility is provided +y t2o

Scanning Electron Microscopes

9SEM; 2!ic! can magnify to QH@@@@@ 2it! good resolution5 9$E=0

T@@ and Cam+ridge SB@;5 T!egreat dept! of #eld of t!ese

instruments and t!e large specimenc!am+er of one of t!ese SEMs !as

made t!em particularly useful ine%amining roug! fracture surfaces

to determine t!e cause of acomponent failure5

" 4ie2 on Scanning ElectronMicroscope Cam+ridge SB@


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&on'Destructive E%amination

" Scanning 0aser Acoustic Microscopy 9S0AM;

" C' Mode Scanning Acoustic Microscopy 9C'SAM;

" Radiograp!y 9in T=S'>C;


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&on'Destructive E%amination cont55

T!e Scanning 0aser Acoustic

Microscopy 9S0AM; produces images of

t!e internal structure of metals1

ceramics and even +iological tissues1

and t!ese are displayed in real time on

a T4 monitor5

T!e S0AM uses very !ig! freuency

ultrasound in a transmission mode to

produce images5 Acoustic 2aves aretransmitted into t!e +ottom face of t!e

cell sample +y means of a distilled'

2ater coupling medium5 sing t!is

instrument it 2as possi+le to assess

t!e uality of solar cell interconnectors

for t!e Space Telescope5


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(ailure Analysis

" Under control of Material Review Board(MRB)

" Collection of +ac.ground data

"visual e%amination" selection1 identi#cation1 preservation of specimens

" macroscopic e%amination and analysis

" microscopic e%amination and analysis

" metallograp!ic sections e%amination

" failure mec!anism" c!emical analysis

" simulated testing

" report


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Materials Properties

anne% cont55

" Corrosion fatigue- Corrosion fatigue indicates crac. formation and propagation caused +y t!e e


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Materials Propertiesanne% cont55

" Strengt!- Spacecraft design covers t!e survival of t!e structure under t!e 2orst feasi+le

com+ination of mec!anical and t!ermal loads5 All events of t!e complete lifetime of t!espacecraft are addressed +y t!is design5 T!e strengt! of a material is !ig!ly dependant

on t!e direction as 2ell as on t!e sign of t!e applied load1 e5g51 a%ial tensile1 transversecompressive1 and ot!ers5

" !ositie margin of safet# and shall include) if a!!licable) #ield load anal#sis)ultimate load anal#sis and buc"ing load anal#sis

" Elastic modulus- T!e elastic modulus de#ned as t!e ratio +et2een t!e unia%ial stress and t!e strain 9e5g51 oungNs modulus1 compressive modulus1 s!ear modulus; is for metals and alloys 2ea.ly

dependant on !eat'treatment and orientation5 *o2ever1 for #+re reinforced materials1t!e elastic modulus depends on t!e #+re orientation5

" For com!osites the re6uired elastic modulus shall be eried.


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Materials Propertiesanne% cont55

" (atigue- (atigue fracture can form in components 2!ic! are su+jected to alternating stresses5

T!ese stresses may lie far +elo2 t!e allo2ed static strengt! of t!e material5

"For com!onents e*!eriencing alternating stresses) demonstration of thedegradation of material !ro!erties oer the com!lete mission

" (racture toug!ness- T!e fracture toug!ness is a measure of t!e damage tolerance of a material containing

initial 6a2s or crac.s5 T!e fracture toug!ness in metallic materials is descri+ed +y t!e

plain strain value of t!e critical stress intensity factor5 T!e fracture toug!ness dependson t!e environment5 7ic is t!e plain strain critical stress intensity factor5 7iscc plain strain

critical stress intensity factor for a speci#ed environment in 2!ic! environmentallyinduced crac. gro2t! occurs5

" Metallic materials for use in corrosie surface enironments shall be tested for

fracture toughness under re!resentatie conditions


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Materials Properties anne% cont55

" Creep- Creep is a time'dependant deformation of a material under an applied load5 It usually

occurs at elevated temperature1 alt!oug! some materials creep at room temperature5 Ifpermitted to continue inde#nitely1 creep terminates in rupture5 E%trapolations from simple

to comple% stress'temperature'time conditions are di)cult5" ,esting under re!resentatie serice conditions is necessar# 'hen cree! is li"el# to

occur.

" Micro'yielding- Some materials may e%!i+it residual strain after mec!anical loading5 T!e micro'yield is t!e

force to +e applied to get a residual strain of %@'B m/m along t!e tensile or compressionloading direction5 In general1 t!e most severe mec!anical loading occurs during launc!5

" 8here dimensional stabilit# re6uirements hae to be met) micro-#ielding shall beassessed.

" 8hen it is li"el# to occur) testing and anal#sis in relation 'ith the mechanical loading

during the life c#cle of the hard'are shall be !erformed.


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Stress Corrosion Crac.ing1 cont

Mean +rea.ing stress versus e%posure time for s!orttransverse 5Hmm 9@5 HFin5; diam aluminium alloy?@?F tension specimens tested according to ASTM LL at various e%posure stress levels5 Eac! pointrepresents an average of #ve specimens5


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Stress Corrosion Crac.ing1 cont55

E


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SCC Ta+le I ' Steel Alloys

Alloy Car%on steel&1$$$ series'

(o) allo* steel&413$+434$ etc' &E' DAC+ ,-11

Msic )ire&ASTM 22"' ,.-"$ steel

,.-13$ steel

,.-14$ steel

1$#5 srin0 steel

3$$ series stainless steel&nsensitised'24$$ series erritic stainless steel

21--# stainless steel

Carenter 2$ C% Stainless steel

Carenter 2$$ C%-3 stainless steel

A2" stainless steel

AM35$ stainless steel

AM355 stainless steel

Alar 32 stainless steel

Csto 45$ stainless steel

Csto 455 stainless steel15-5 P, stainless steel

P, 14-" Mo stainless steel P, 15-! Mo stainless steel

1!-! P, stainless steel

itronic 33 &3' &E' Mara0in0 steel MAA( 612

Condition

7elo) 125 80/29 &1"$ 8si' :TS

7elo) 125 80/29 &1"$ 8si' :TS &1'

7elo) 14" 80/29 &21$ 8si' :TS

cold dra)n

Qenched and teered

Qenched and teered

Qenched and teered

Qenched and teered

AllAll

All

All

All

All

SCT 1$$$&4' and a%ove

SCT 1$$$ and a%ove

,1$$$ &5' and a%ove

,1$$$ and a%ove

,1$$$ and a%ove

,1$$$ and a%ove

C,#$$ and S,#5$ and a%ove &+!'

C,#$$

C,#$$

All

All

1' A sall n%er o la%orator* ailres o

seciens ct ro late ore than 2

inches thic8 have %een o%served at !5;

*ield+ even )ithin this ltiate stren0th

ran0e< The se o thic8 late shold

thereore %e avoided in a corrosive

environent )hen sstained tensile stress

in the short transverse direction is

e=ected<2' >ncldin0 )eldents o 3$4(+ 31(+

321 and 34!<

3' >ncldin0 )eldents<

4' SCT 1$$$ ? s%-@ero coolin0 and

teerin0 at 53"B1!9C &1$$$'

5' ,1$$$ ? hardened a%ove 53"C &1$$$'

' C,#$$ ? cold )or8ed and a0ed at

4"$C &1$$$9'

!' S,#5$ ? soltion treated and

teered at 51$C $'

&E' ESA classiication - not in ASA

MSC-SPEC-522A


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SCC Ta+le I ' &ic.el Alloys

Allo*

,astello* C

,astello* 6

>ncolo* "$$

>ncolo* #$1

>ncolo* #$3>nconel $$ &3'

>nconel 25

>nconel !1" &3'

>nconel 6-!5$

Monel -5$$

iSan -C #$2

ene 41

:nite 212

asalo*

3' >ncldin0 )eldents

Condition

All

All

All

All

All

Annealed

Annealed

All

All

All

All

All

All

All


58/64


SMEInitiative

SCC Ta+le I ' Aluminium Alloys

Alloy,

Wrought(1,2)

Allo*+ 1$$$ series

2$11

2$24+ rod %ar

221#

&E' 241#

&E' 21"

3$$$ series5$$$ series

$$$ series &E'!$2$

!$4#

!14#

!$5$

!$!5

!4!5

Condition

All

T"

T"

T+ T"

T"

T+ T"

All

All &4+5'

All

T &'

T!3

T!3

T!3

T!3

T!3

Cast (3)

355


59/64


SMEInitiative

SCC Ta+le I ' Copper Alloys/ Misc5 Alloys

CDA no (1)

11$

1!$

1!2

1#4

1#5

23$

422

443

51$

521

1#

1#

""

!$

!25

2"$+524+$

32+55+!$5

!1$+!15

&E'#1!+ &E'#3!

Condition (% cold rolled) (2)

3!

AT+ ,T &3'

AT+ ,T &3'

3!

#$

4$

3!

1$

3!

3!

4$ 7 hase'

4$ 7 hase'

4$

5$

5$+ annealed

$$

$

$

Alloy

7er*lli+ S-2$$C

,S 25 &($5'

,S 1""

MP35

Titani 3Al-2


60/64

Materials and sheet$

SMEInitiative

SCC Ta+le II ' Steel Alloys/Miscellaneous alloys

Alloy

Car%on steel &1$$$ series'

(o)-allo* steel &413$+434$ etc'

itronic 32

itronic $

4$$ series artensitic stainless steel &e=cet 44$'

P, 13-" Mo stainless steel

15-5 P, stainless steel1!-4 P, stainless steel

Condition

1225 to 13!$ MPa :TS

1225 to 13!$ MPa :TS

All

All

&1'

All

7elo) ,1$$$ &2'

All

1' Teerin0 %et)een 3!$ and $$C shold %e avoided %ecase corrosion and stress-corrosion resistance is lo)ered<

2' ,1$$$ ? hardened a%ove 53"C &1$$$'<

Alloy

Ma0nesi AF317

Ma0nesi F$A

Ma0nesi &E' F3

Condition

All

All

All


61/64


SMEInitiative

SCC Ta+le II ' Aluminium Alloys91H;

Alloy, wrough

2$24 rod+ %ar+ e=trsion

2$24 late+ e=trsions

2124 late

2$4" late

4$32

5$"3

5$"

545!$$1

&E' !$1$

!$4#

!$5$

!$!5

!1!5

!4!5

!1!"

&E' ssian Al-(i 142$+ 1421

Condition

T+ T2

T"

T"

T"

T

All &3'

All &3'

All &3'

T!5+ T!

T!4

T!

T!4+ T!

T! T!4+

T!

T!

T!

soln< treatGa0e

Alloy, cast

31#+ alini

allo*s< These allo*s are not recoended or hi0h-teeratre alications<

C &15$' and a%ove<

&E' ESA classiication - not in ASA MSC-SPEC-522A<


62/64


SMEInitiative

SCC Ta+le III ' Steel Alloys

Alloy

Car%on steel&1$$$ series'

(o) allo* steel&413$+434$ etc'

&E' DAC+ ,-11steel

44$C stainless steel

1" i Mara0in0 steel+ 2$$ 0rade

1" i Mara0in0 steel+ 25$ 0rade

1" i Mara0in0 steel+ 3$$ 0rade

1" i Mara0in0 steel+ 35$ 0rade

AM 35$ stainless steel

AM 355 stainless steel

Csto 455 stainless steel

P, 15-! Mo stainless steel

1!-! P, stainless steel C,#$$

&E' ovar

Condition

A%ove 13!$ Ma :TS

A%ove 13!$ Ma :TS

A%ove 13!$ Ma :TS

All

A0ed at #$$

A0ed at #$$

A0ed at #$$

A0ed at #$$

7elo) SCT 1$$$

7elo) SCT 1$$$

7elo) ,1$$$

All e=cet C,#$$

All e=cet C,#$$

All


63/64


SMEInitiative

SCC Ta+le III ' Aluminium Alloys

Alloy, Wrought (1,2)

2$11

2$14

2$1!

2$24

2$24 or0in0s

2$24 Plate

&E' Al-(i 2$"$

&E' 21"!$$1

!$$5

&E' !$2$

!$3#

!$!5

!1!5

!$!#

!1!"

!4!5&E' Al-(i "$#$

&E' 7S (#3

&E' ssian Al-(i 1441+ 14$

Condition

T3+ T4

All

All

T3+ T4

T+ T2+ T"

T2

T"

T3+ T4

T

All

eldents

All

T

T

T

T

T

All

T

All

Condition

T

T

T4

T

As cast

Alloy

2#5


64/64

SMEInitiative

SCC Ta+le III ' Copper Alloys/ Magnesium alloys

CDA no (1)

2$

353

443

!2

"!

!2

!

!!$

!"2

1' Coer Develoent

Association allo* n%er

2' atin0 %ased on listed

conditions onl*

Condition (% cold rolled) (2)

5$

5$

4$

5$+ annealed

1$+ 4$

A+ 25+ 5$

3"

3"+ 5$+ annealed

5$

Alloy Condition

Ma0nesi AF17 All

Ma0nesi AF"$A All

Ma0nesi E54 All

Ma0nesi FCM!11 All

sme1- metallic materials

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