Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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206 CHAPTER 6 Matrix Methods


Fig.6.14


Quadrilateral element subjected to nodal in-plane forces and displacements.


Asinthecaseofthetriangularelement,weselectadisplacementfunctionwhichsatisfiesthetotalof
eightdegreesoffreedomofthenodesoftheelement;again,thisdisplacementfunctionwillbeinthe
formofapolynomialwithamaximumofeightcoefficients.Thus,


u(x,y)=α 1 +α 2 x+α 3 y+α 4 xy
v(x,y)=α 5 +α 6 x+α 7 y+α 8 xy

}

(6.96)

Theconstantterms,α 1 andα 5 ,arerequired,asbefore,torepresentthein-planerigidbodymotionofthe
element,whilethetwopairsoflineartermsenablestatesofconstantstraintoberepresentedthroughout
theelement.Further,theinclusionofthexytermsresultsinbothu(x,y)andv(x,y)displacementshaving
thesamealgebraicformsothattheelementbehavesinexactlythesamewayinthexdirectionasitdoes
intheydirection.
WritingEqs.(6.96)inmatrixformgives


{

u(x,y)
v(x,y)

}

=

[

1 xyxy 0000
0000 1xyxy

]


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α 1
α 2
α 3
α 4
α 5
α 6
α 7
α 8


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(6.97)
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