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STUDY ON MATERIALSELECTION OF

FUSELAGE SKINProject Seminar

Aircraft Materials and Processes

By Y. Sharath Chandra Mouli

Roll No: 1511!"5

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Fuselage and fuselage Types#he fusela$e is the main structure or %ody of the &'ed()in$

aircraft.

*t +ro,ides s+ace for car$o- controls- accessories- +assen$ers-and other eui+ment. *n sin$le(en$ine aircraft- the fusela$ehouses the +o)er+lant.

#y+es of /usela$es: Truss Type

Monocoque Type

Semimonocoque Type

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Funct!ns !f Fuselage S"n

*t transmits the aerodynamic forces to the lon$itudinal andtrans,erse su++ortin$ mem%ers %y +late and mem%raneaction

*t de,elo+s shearin$ stresses )hich react to the a++lied

torsional moments and shear forces. *t acts )ith the lon$itudinal mem%ers in resistin$ the a++lied

%endin$ and a'ial loads.

*t acts )ith lon$itudinal in resistin$ the a'ial load )ith thetrans,erse mem%ers in reactin$ the hoo+ or circumferential

load )hen the structure is +ressuri0ed. *n addition to these- it +ro,ides an aerodynamic surface and

co,er for the contents of the ,ehicle.

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#$!pe$ty Re%u$e&ents f!$ Fuselage#he fusela$e can %e di,ided

into three areas: cro)n-sides and %ottom. Predominant loads durin$

i$ht are tension in thecro)n- shear in the sidesand com+ression in the

%ottom. #hese loads are caused %y

%endin$ of the fusela$e dueto loadin$ of the )in$sdurin$ i$ht and %y ca%in+ressure.

#a'iin$ causes com+ression

in the to+ and tension in the%ottom- ho)e,er thesestresses are less than the in(i$ht stresses.Stren$th- Youn$2s modulus- fati$ue initiation- fati$ue crac3

$ro)th- fracture tou$hness and corrosion are all im+ortant- %utfracture tou$hness is often the limitin$ desi$n consideration.

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T$ends n Alu&nu& All!y #$!duct De'el!p&ent

f!$ A$c$aft Fuselage S"nDuring 1903-1930s: Minimum )ei$ht )as the major criteria for

materials selection. 4!1"(# 6 !1(#7 has %een used durin$ this+eriod8

During 1930-1960s: *m+ro,ed +erformance )as the $oal andreduced )ei$ht )as a +rinci+al contri%utor. 9'+eriments led to the de,elo+ment of !!(#

;i$her yield stren$th than !1"(# Natural a$in$ and si$ni&cantly hi$her

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T$ends n Alu&nu& All!y #$!duct De'el!p&ent

f!$ A$c$aft Fuselage S"n

Afte$ ()*+,s- In Boeing 777evolutionary improvements of older

materials are utilized. Included 7150-T77 that has higher strength

and damage tolerance when compared with

7050- T7.

!lloy 7055-T77 that has higher strength than

7150-T along with similar fracture toughness

and fatigue crac" growth resistance.

!lloy #5#$-T% that has appro&imately 15'

#0( improvement in fracture toughness and

twice the fatigue crac" growth resistance when

compared with #0#$-T%.

The higher toughness and greater resistance tofatigue crac" growth of #5#$-T% helped in the

elimination of tear straps in a weight-efficient

manner on the Boeing 777.

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T.e need f!$ ad'anced &ate$als

)aterials with high specific strength *strength per unit of weight+ have long

,een popular with the aerospace industry as components made from such

materials provide the reuired strength with less weight there,y reducing fuel

,urn and operating cost.

C!&p!stes as Alte$nat'e-

The advantage of composite materials is that the properties they e&hi,it are different

to simply the sum of the properties of the constituent materials.

/enefts !f c!&p!stes-

/igh specific strength

!,ility to resist fatigue

orrosion esistance

)anufactura,ility

large comple& shapes

2evertheless composites have ,een enthusiastically em,raced ,y the

aerospace industry with aircraft manufacturers progressively increasing the

amount of composite material used in the airframe and in aircraft systems.

C.allenges ass!cated 0t. c!&p!ste desgn- 3ac" of design data.

/uge varia,ility ,etween composite materials

esponse to damage

4irect Impact 3oads

4etection and repair of damage remains difficult 3ightning stri"e protection *36+.

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se of omposites in aircrafts fuselage s"in

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se of omposites in aircrafts fuselage s"in

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References

>Pro$ress in structural materials for aeros+ace systems?-J.C. Williams, E.A. Starke, Jr. / Acta Materialia 51 (2003)57755799

>SBAC A,iation and 9n,ironment Brie&n$ Pa+ers?- SBAC-Ad,anced Aircraft Materials !!.

>A++lication of modern aluminum alloys to aircraft?- 9.A.Star3e- @r and @. #. Staley-r! 9. Aer!s"ace Sci. #!l. 32, "".131$172% 199&

>Challen$es for research and de,elo+ment of ne) aluminumalloys?-