复合材料机身壁板的强度分析与试验验证

doi:10.7527/S1000-6893.2020.23688

固体力学与飞行器总体设计

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复合材料机身壁板的强度分析与试验验证

李真¹, 王俊¹, 邓凡臣², 于振波¹

1. 上海飞机设计研究院, 上海 201210;
2. 中国飞机强度研究所, 西安 710065

收稿日期:2019-11-27 修回日期:2020-01-04 出版日期:2020-09-15 发布日期:2020-01-19
通讯作者: 李真 E-mail:lizhen@comac.cc
基金资助:
民机科研项目（MJ-2015-F-038）

Strength analysis and test verification of composite fuselage panels

LI Zhen¹, WANG Jun¹, DENG Fanchen², YU Zhenbo¹

1. Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;
2. China Aircraft Strength Research Institute, Xi'an 710065, China

Received:2019-11-27 Revised:2020-01-04 Online:2020-09-15 Published:2020-01-19
Supported by:
Civil Aircraft Scientific Research Project (MJ-2015-F-038)

摘要/Abstract

摘要： 复合材料在大型客机机身主承力结构应用是近年来的发展趋势，通过分析与大型壁板试验结合的方式研究了复合材料机身壁板的静力承载能力，以及疲劳与损伤容限特性。采用理论公式、半经验公式、有限元模态分析研究了蒙皮的屈曲载荷、壁板的承载能力。依靠创新的机身壁板多轴载荷试验系统，模拟机身壁板的实际受载情况，实现充压载荷、拉伸/压缩、剪切载荷的独立施加与组合施加。通过静力试验验证蒙皮屈曲的工程及有限元分析方法和壁板的剩余强度承载分析方法。引入预埋缺陷、BVID、VID冲击损伤，通过试验研究了损伤对应变分布的影响，并通过疲劳、损伤容限试验，验证了壁板的设计以及损伤的无扩展特性。

关键词: 复合材料, 机身壁板, 稳定性, 疲劳, 损伤容限

Abstract: The application of composite materials in the main loading structure of the aircraft fuselage is the development trend in recent years. In this paper, the static loading capacity, fatigue and damage tolerance characteristics of composite fuselage panels are analyzed with large-scale panel test. The buckling load of skin and the loading capacity of panel are examined by adopting the theoretical formula, the semi empirical formula, and the finite element modal analysis. The advanced multi-load panel test rig is used to simulate the actual loads of fuselage panel, achieving the independent and combined application of the pressure, tension, compression, and shear load. The engineering and finite element analysis method of skin buckling and the residual strength loading analysis method of panel are verified by static tests. By introducing the embedded defect, BVID and VID damage, the influence of the damage on strain distribution is studied by experiment, and the non-expansion property of the damage is verified by fatigue and damage tolerance experiments.

Key words: composite material, fuselage panel, stability, fatigue, damage tolerance

中图分类号:

V223

李真, 王俊, 邓凡臣, 于振波. 复合材料机身壁板的强度分析与试验验证[J]. 航空学报, 2020, 41(9): 223688-223688.

LI Zhen, WANG Jun, DENG Fanchen, YU Zhenbo. Strength analysis and test verification of composite fuselage panels[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(9): 223688-223688.

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复合材料机身壁板的强度分析与试验验证

Strength analysis and test verification of composite fuselage panels

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