冲击载荷作用下机身壁板破坏效应及结构优化

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Abstract Under the constraint of non-containment explosion-proof structure, the damage effect of shock wave and plug on the fuselage panel is studied. Taking the fuselage panel at the impact position of directional non-containment explosion-proof structure as the research object, through finite element numerical simulation, the failure mode and degree of shock wave and plug acting on the body panel at different positions under the constraint of non-containment explosion-proof structure are analyzed. Then, in order to limit the damage range of the fuselage panel, we optimize the structure of the fuselage panel at the impact position. The results show that the main failure modes of the fuselage panel under shock wave impact are skin shear plug, rib tearing along and perpendicular to the tendons, and rib fracture, while under plug impact, the skin is torn along and perpendicular to the tendons and the ribs are broken. The influence of impact position on the damage degree of fuselage panel under plug impact is more obvious than that of shock wave impact. The position of the plug impact bar has less damage to the fuselage panel as a whole, so it is a better impact scheme. Vertical reinforcement has obvious restraint effect on the crack expansion of fuselage panel under two impact modes, but the restraint effect is better under the action of end. When the plug hits the position of two bars or single bar, the damage area of vertical reinforcement panel is reduced by 56.0% and 39.0% respectively. The research results can provide guidance for the structural design of non-contained explosion-proof vessels for civil aircraft and the structural design of fuselage panels at the impact position.

Key words： least risk bomb location fuselage wall plate structural response numerical simulation 2020-T3 aluminum alloy

Received: 12 August 2022 Published: 28 July 2023

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	Articles by authors
	LI Yongpeng1
	XU Yuxin1
	2
	3
	YANG Xiang4
	LI Xudong5

Cite this article:

LI Yongpeng1,XU Yuxin1,2, et al. Failure effect and structure optimization of a fuselage panel under impact load[J]. JOURNAL OF VIBRATION AND SHOCK, 2023, 42(14): 40-47.

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http://jvs.sjtu.edu.cn/EN/ OR http://jvs.sjtu.edu.cn/EN/Y2023/V42/I14/40

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