Consider a Boeing 787 and assume the fuselage cross-section to be circular with a diameter d=5.9m, a skin thickness t=2mm, and isotropic material properties of E=60GPa and ν=0.28. The vertical tail plane applies a torsional moment of the rear fuselage, inducing a shear flow in the rear fuselage skin. Calculate the shear stress τ in the rear fuselage skin for the assumed fuselage diameter and thickness if a torsional moment of MT=1.8⋅106N⋅m is applied.
Consider a Boeing 787 and assume the fuselage cross-section to be circular with a diameter d=5.9m, a skin thickness t=2mm, and isotropic material properties of E=60GPa and ν=0.28. The vertical tail plane applies a torsional moment of the rear fuselage, inducing a shear flow in the rear fuselage skin. Calculate the shear stress τ in the rear fuselage skin for the assumed fuselage diameter and thickness if a torsional moment of MT=1.8⋅106N⋅m is applied.
Chapter2: Loads On Structures
Section: Chapter Questions
Problem 1P
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Consider a Boeing 787 and assume the fuselage cross-section to be circular with a diameter d=5.9m, a skin thickness t=2mm, and isotropic material properties of E=60GPa and ν=0.28.
The vertical tail plane applies a torsional moment of the rear fuselage, inducing a shear flow in the rear fuselage skin.
Calculate the shear stress τ in the rear fuselage skin for the assumed fuselage diameter and thickness if a torsional moment of MT=1.8⋅106N⋅m is applied.
Hint:Applu q=MT/2A.
Select whether the following statement is true or false: Damage tolerance is the structural ability to sustain environmental degradation to the extent that economically acceptable maintenance programs can control it.
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