A fuselage with a circular cross section has 16 stringers, which 4 stringers were fitted at the axes of symmetry. The fuselage is idealized into boom structures and the area of each boom is similar, B = 215 mm². The distances measured from the x-axis are as follows: Y₁ = 380 mm, Y₂ = 350 mm, Y₁ = 270 mm, Y₂ = 146 mm The symmetrical cross section fuselage is subjected to a bending moment Mx = 190 kNm. If all direct stresses are carried by the booms, calculate the average direct stress in each boom. Present your answers in a table. Draw the illustration of the idealized fuselage cross section, with all the booms fitted at the respective distances.

Mechanics of Materials (MindTap Course List)
9th Edition
ISBN:9781337093347
Author:Barry J. Goodno, James M. Gere
Publisher:Barry J. Goodno, James M. Gere
Chapter5: Stresses In Beams (basic Topics)
Section: Chapter Questions
Problem 5.7.2P: .2 A ligmio.irc ii supported by two vorlical beams consistins: of thin-walled, tapered circular...
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A fuselage with a circular cross section has 16 stringers, which 4 stringers were fitted at the axes of
symmetry. The fuselage is idealized into boom structures and the area of each boom is similar, B = 215
mm². The distances measured from the x-axis are as follows:
Y₁ = 380 mm, Y₂ = 350 mm, Y₁ = 270 mm, Y₁ = 146 mm
The symmetrical cross section fuselage is subjected to a bending moment Mx = 190 kNm. If all direct
stresses are carried by the booms, calculate the average direct stress in each boom. Present your
answers in a table. Draw the illustration of the idealized fuselage cross section, with all the booms
fitted at the respective distances.
Transcribed Image Text:A fuselage with a circular cross section has 16 stringers, which 4 stringers were fitted at the axes of symmetry. The fuselage is idealized into boom structures and the area of each boom is similar, B = 215 mm². The distances measured from the x-axis are as follows: Y₁ = 380 mm, Y₂ = 350 mm, Y₁ = 270 mm, Y₁ = 146 mm The symmetrical cross section fuselage is subjected to a bending moment Mx = 190 kNm. If all direct stresses are carried by the booms, calculate the average direct stress in each boom. Present your answers in a table. Draw the illustration of the idealized fuselage cross section, with all the booms fitted at the respective distances.
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