Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

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478 CHAPTER 15 Bending of Open and Closed, Thin-walled Beams


P.15.17ThebeamsectionshowninFig.P.15.17issubjectedtoatemperaturechangewhichvarieswithysuchthat
T=T 0 y/2a.Determinethecorrespondingchangesinthestressresultants.Young’smodulusforthematerialofthe
beamisE,whileitscoefficientoflinearexpansionisα.


Ans. NT=0,MxT= 5 Eαa^2 tT 0 /3,MyT=Eαa^2 tT 0 /6.

Fig. P.15.17
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