Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

Problems 323

iflocalinstability,skinbuckling,andpanelstrutinstabilityalloccuratthesamestress.NotethatinFig.P.9.7(a),
onlytwoofseveralstringersareshownfordiagrammaticclarity.Also,thethinskinshouldbetreatedasaflatplate,
sincethecurvatureissmall.Foraflatplatesimplysupportedalongtwoedges,assumeabucklingcoefficientof
3.62.TakeE=69000N/mm^2.

Ans. b=56.5mm,L=700mm.

Fig. P.9.7