Static Strength and Buckling Analysis of an Aircraft Support

At the initial stage of design, structural strength and stability load-bearing members aircraft are mainly considered. In this paper, a support assembly analyzed. First, analysis, under design load 30.151 KN, numerical analysis shows that, in stress concentration area, peak value is 571.9 Mpa. The experimental strain sensor S6 position compared with results, error within 2.5%, which verifies validity model to meet requirements. Second, adopts method buckling analysis. Linear that first six order modes critical loads. 464.9 KN. Risk arc length used nonlinear Considering geometric imperfection support, 1% 10% values used. Nonlinear values—without considering imperfection—are obtained, 110.6 108.4 106.2 respectively. There little difference between three values, indicating not obvious buckling, they have stability. case no imperfection, maximum deformation main area reaches 21.4 mm, enters instability state. This paper comprehensively discusses results can provide reference for optimization bearing components.