机身整体壁板在轴压载荷下后屈曲计算及结构优化

孙为民; 郭亮; 童明波; 董登科

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机身整体壁板在轴压载荷下后屈曲计算及结构优化

更新时间：2026-10-06

- 机身整体壁板在轴压载荷下后屈曲计算及结构优化
- 机身整体壁板在轴压载荷下后屈曲计算及结构优化
- 南京航空航天大学学报（英文版） 2010年第4期
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- 纸质出版：2010
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孙为民, 郭亮, 童明波, 等. 机身整体壁板在轴压载荷下后屈曲计算及结构优化[J]. 南京航空航天大学学报（英文版）, 2010,(4).

孙为民, 郭亮, 童明波, et al. 机身整体壁板在轴压载荷下后屈曲计算及结构优化[J]. Transactions of Nanjing University of Aeronautics and Astronautics, 2010, (4).
孙为民, 郭亮, 童明波, 等. 机身整体壁板在轴压载荷下后屈曲计算及结构优化[J]. 南京航空航天大学学报（英文版）, 2010,(4). DOI：

孙为民, 郭亮, 童明波, et al. 机身整体壁板在轴压载荷下后屈曲计算及结构优化[J]. Transactions of Nanjing University of Aeronautics and Astronautics, 2010, (4). DOI：

摘要

Abstract

Buildup 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 buildup str ucture

and finite element models (FEMs) of these two panels are established. Ex perimental results of buildup 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 buildup panel

and the failure loa d increases by 184％ up to postbuckling. Furthermore

the integral structure is optimized by using the multiisland genetic algorithm and the sequential quadratic progr amming. Compared with the initial design

the optimal weight is reduced by 87 ％ and the strength is unchanged.

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