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

Abstract

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

CLC Number:

V223

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.

References 23

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Strength analysis and test verification of composite fuselage panels

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