Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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122 CHAPTER 5 Energy Methods


FromCtoD,


M=

(

1

4

PB,f+

1

2

PC,f+

wL
2

)

(L−z)−

w
2

(L−z)^2

sothat


∂M
∂PB,f

=

1

4

(L−z)

∂M

∂PC,f

=

1

2

(L−z)

Substituting these values in Eqs. (iv) and (v) and remembering thatPB,f=PC,f=0, we have, from
Eq.(iv),


(^) B=


1

EI


⎪⎨

⎪⎩

∫L/^4

0

(

wLz
2


wz^2
2

)

3

4

zdz+

∫L/^2

L/ 4

(

wLz
2


wz^2
2

)

1

4

(L−z)dz

+

∫L

L/ 2

(

wLz
2


wz^2
2

)

1

4

(L−z)dz


⎪⎬

⎪⎭

fromwhich


(^) B=
119 wL^4
24576 EI
Similarly,
(^) C=
5 wL^4
384 EI
Thefictitiousloadmethodofdeterminingdeflectionsmaybestreamlinedforlinearlyelasticsystems
andisthentermedtheunitloadmethod;thisweshalldiscusslaterinthechapter.


5.4 ApplicationtotheSolutionofStaticallyIndeterminateSystems...............................


In a statically determinate structure, the internal forces are determined uniquely by simple statical
equilibriumconsiderations.Thisisnotthecaseforastaticallyindeterminatesysteminwhich,aswe
havealreadynoted,aninfinitenumberofinternalforceorstressdistributionsmaybefoundtosatisfy
the conditions of equilibrium. The true force system is, as we demonstrated in Section 5.2, the one
satisfyingtheconditionsofcompatibilityofdisplacementoftheelasticstructureor,alternatively,that
forwhichthetotalcomplementaryenergyhasastationaryvalue.Weshallapplytheprincipletoavariety
ofstaticallyindeterminatestructures,beginningwiththerelativelysimplesinglyredundantpin-jointed
frameshowninFig.5.8inwhicheachmemberhasthesamevalueoftheproductAE.
The first step is to choose the redundant member. In this example, no advantage is gained by the
choiceofanyparticularmember,althoughinsomecasescarefulselectioncanresultinadecreasein
the amount of arithmetical labor. Taking BD as the redundant member, we assume that it sustains a

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