爆炸冲击载荷下机身壁板的动态响应

doi:10.7527/S1000-6893.2021.25513

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爆炸冲击载荷下机身壁板的动态响应

冯振宇^1,2, 傅博宇^1,2, 解江^1,2, 段竹煊^1,2, 潘汉源^1,2

1. 中国民航大学安全科学与工程学院, 天津 300300;
2. 中国民用航空局民航航空器适航审定技术重点实验室, 天津 300300

收稿日期:2021-03-17 修回日期:2021-08-17 出版日期:2022-06-15 发布日期:2021-08-17
通讯作者: 冯振宇,E-mail:mhfzy@163.com E-mail:mhfzy@163.com
基金资助:
航空科学基金（201941067001）；中国民航大学研究生科研创新资助项目（2020YJS049）

Dynamic response of fuselage panel under explosive impact load

FENG Zhenyu^1,2, FU Boyu^1,2, XIE Jiang^1,2, DUAN Zhuxuan^1,2, PAN Hanyuan^1,2

1. College of Safety Science and Engineering, Civil Aviation University of China, Tianjin 300300, China;
2. Key Laboratory of Civil Aircraft Airworthiness Technology, Civil Aviation Administration of China, Tianjin 300300, China

Received:2021-03-17 Revised:2021-08-17 Online:2022-06-15 Published:2021-08-17
Supported by:
Aeronautical Science Foundation of China (201941067001);Graduate Research and Innovation Funding Project of Civil Aviation University of China (2020YJS049)

摘要/Abstract

摘要： 为了满足"最小风险炸弹位置（LRBL）"的设计要求，有必要针对爆炸冲击载荷下机身壁板的动态响应开展研究。参考典型客机机身结构建立了铝合金机身壁板有限元模型，分析了增压、爆炸冲击位置与药量对机身壁板变形模式与失效行为的影响。研究结果表明，当机身壁板蒙皮未发生失效时，增压对整体变形模式的影响较小。当机身壁板蒙皮发生失效时，增压对整体失效行为的影响剧烈；爆炸冲击不同位置时，冲击长桁及隔框位置造成的开口损伤较小，但是结构产生了更长的裂纹损伤；随着药量的增加，冲击波更快传递到结构，冲击位置获得了更大的变形速度。

关键词: 增压, 机身壁板, 铆钉, 爆炸响应, 冲击载荷

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

中图分类号:

V223.2

冯振宇, 傅博宇, 解江, 段竹煊, 潘汉源. 爆炸冲击载荷下机身壁板的动态响应[J]. 航空学报, 2022, 43(6): 525513-525513.

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): 525513-525513.

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E-mail：hkxb@buaa.edu.cn

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爆炸冲击载荷下机身壁板的动态响应

Dynamic response of fuselage panel under explosive impact load

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