Abstract
Optimal design of a typical fuselage cross section for civil aircraft is one of the most important aspects of overall aircraft design. In this paper, a typical cross section of a certain type of civil aircraft (referred to as model A) is taken as an example and compared with a similar model B of strength calculation and analysis of deformation, bending moment, stress and other structural bearing efficiency. The principle of the difference is explored and the principle of engineering design of a typical fuselage cross section is summarized. Then the design of the original cross section is optimized by integrating structural load-bearing efficiency, space arrangement and other factors. Strength evaluation is also carried out. Finally, the optimization plan of a typical fuselage cross section of model A is given.
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