Abstract The stress-strain state of thin-walled aircraft structures such as a wing or fuselage made of composite materials is determined based on the beam theory. The laminated skin is orthotropic. The solution was obtained without using the centroidal principal section axes and subdividing the problem in shear and torsion. A calculation variant with skin discretization along the section contour was studied.
Analysis of thin-walled stiffened rods using the beam theory
Russian Aeronautics (Iz VUZ) ; 54 , 1 ; 49-55
2011-03-01
7 pages
Article (Journal)
Electronic Resource
English
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