爆炸冲击载荷下机身壁板的动态响应

doi:10.7527/S1000-6893.2021.25513

Abstract

Abstract: In order to meet the design requirements of the "Least Risk Bomb Location (LRBL)", it is necessary to conduct research on the dynamic response of the fuselage panel under the explosive impact load. In this paper, a finite element model of aluminum alloy fuselage panels is established with reference to the typical passenger aircraft fuselage structure, and the effects of pressurization, explosion impact position and charge on the deformation mode and failure behavior of fuselage panels are analyzed. The results show that when the fuselage panel skin does not fail, the effect of pressurization on the overall deformation mode is small; when the fuselage panel skin fails, the effect of pressurization on the overall failure behavior is severe; when the explosion impacts different positions, the opening damage caused by the impact of the long truss and the bulkhead position is less, but the structure produces longer crack damage. The results also show that as the amount of charge increases, the shock wave is transmitted to the structure faster, and the impact position obtains a greater deformation speed.

Key words: pressurization, fuselage panel, rivet, explosive response, impact load

CLC Number:

V223.2

FENG Zhenyu, FU Boyu, XIE Jiang, DUAN Zhuxuan, PAN Hanyuan. Dynamic response of fuselage panel under explosive impact load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525513.

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Dynamic response of fuselage panel under explosive impact load

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