Transactions of Nanjing University of Aeronautics & Astronautics
机身整体壁板在轴压载荷下后屈曲计算及结构优化
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Abstract:
Buildup panels for the commercial aircraft fuselage subjected to the axial com pression load are studied by both experimental and theoretical methods. An integ ral panel is designed with the same overall size and weight as the buildup str ucture, and finite element models (FEMs) of these two panels are established. Ex perimental results of buildup panels agree well with the FEM results with the nonliearity and the large deformation, so FEMs are validated. FEM calculation results of these two panels indicate that the failure mode of the i ntegral panel is different from that of the buildup panel, and the failure loa d increases by 184％ up to postbuckling. Furthermore, the integral structure is optimized by using the multiisland genetic algorithm and the sequential quadratic progr amming. Compared with the initial design, the optimal weight is reduced by 87 ％ and the strength is unchanged.
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Project Supported:
Supported by the National Natural Science Foundation of China (60674100).
Clc Number:
CHINA AERO-SCIENCES
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