Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

168 CHAPTER 5 Energy Methods

Fig. P.5.24

giventhat

(a) thetemperaturedistributionis

θ=θ 0 cos2ψ for−π/ 4 <ψ<π/ 4

θ=0 for−π/ 4 >ψ>π/ 4

(b) bendingdeformationsonlyaretobetakenintoaccount:

α =coefficientoflinearexpansionofframematerial

EI=bendingrigidityofframe

h =depthofcrosssection

r =meanradiusofframe.