Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

Problems 617

Wall Length (mm) Thickness (mm) Boom Area (mm^2 ) Cell Area (mm^2 )

12, 56 510 0.559 1, 6 645 I 93000

23, 45 765 0.915 2, 5 1290 II 258000

34 o 1015 0.559 3, 4 1935

34 i 304 2.030

25 304 1.625

Fig. P.22.7

P.22.8 Aportionofatapered,three-cellwinghassinglysymmetricalidealizedcrosssections1000mmapartas
showninFig.P.22.8.AbendingmomentMx=1800NmandashearloadSy=12000Nintheplaneoftheweb52
areappliedatthelargercrosssection.Calculatetheforcesintheboomsandtheshearflowdistributionatthiscross
section.ThemodulusGisconstantthroughout.Sectiondimensionsatthelargercrosssectionaregivenbelow.

Fig. P.22.8

Wall Length (mm) Thickness (mm) Boom Area (mm^2 ) Cell Area (mm^2 )

12, 56 600 1.0 1, 6 600 I 100000

23, 45 800 1.0 2, 5 800 II 260000

34 o 1200 0.6 3, 4 800 III 180000

34 i 320 2.0

25 320 2.0

16 210 1.5