Introduction to Aircraft Structural Analysis (Elsevier Aerospace Engineering)

Problems 613

Fig.22.26

Final shear flows in bay③(and bay①) of the wing box of Example 22.7.

Fig.22.27

Shear flows (N/mm) applied to the wing rib at station 3000 in the wing box of Example 22.7.

References

[1] Megson,T.H.G.,AircraftStructuresforEngineeringStudents,4thedition,Elsevier,2007.

Problems..............................................................................................

P.22.1 ThecentralcellofawinghastheidealizedsectionshowninFig.P.22.1.Iftheliftanddragloadsonthe
wingproducebendingmomentsof−120000Nmand−30000Nm,respectively,atthesectionshown,calculate
the direct stresses in the booms. Neglect axial constraint effects and assume that the lift and drag vectors are in
verticalandhorizontalplanes.

Boomareas:B 1 =B 4 =B 5 =B 8 =1000mm^2

B 2 =B 3 =B 6 =B 7 =600mm^2

Fig. P.22.1