Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

Problems 631

Fig. P.23.2

P.23.3 Athree-flangewingsectionisstiffenedbythewingribshowninFig.P.23.3.Iftheribflangesandstiffeners
carryallthedirectloads,whiletheribpanelsareeffectiveonlyinshear,calculatetheshearflowsinthepanelsand
thedirectloadsintheribflangesandstiffeners.

Ans. q 1 =4.0N/mm q 2 =26.0N/mm q 3 =6.0N/mm

P 2 in12=−P 3 in43=1200N(tension) P 5 in154=2000N(tension)

P 3 in263=8000N(compression) P 5 in56=12000N(tension)

P 6 in263=6000N(compression).

Fig. P.23.3