大飞机典型货舱下部结构冲击试验及数值模拟

解江; 牟浩蕾; 冯振宇; 程坤; 刘义; 刘小川; 白春玉; 惠旭龙

doi:10.7527/S1000-6893.2021.25890

航空学报 >

2022 , Vol. 43 >Issue 6: 525890 - 525890

DOI: https://doi.org/10.7527/S1000-6893.2021.25890

论文

大飞机典型货舱下部结构冲击试验及数值模拟

解江 ,
牟浩蕾 ,
冯振宇 ,
程坤 ,
刘义 ,
刘小川 ,
白春玉 ,
惠旭龙

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1. 中国民航大学科技创新研究院, 天津 300300;
2. 中国民航大学安全科学与工程学院, 天津 300300;
3. 中国飞机强度研究所结构冲击动力学航空科技重点实验室, 西安 710065

收稿日期: 2021-05-31

修回日期: 2022-03-14

网络出版日期: 2022-07-07

基金资助

天津市教委科研计划（2019KJ135）；天津市自然科学基金

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Impact characteristics of typical sub-cargo structure of large aircraft: Tests and numerical simulation

XIE Jiang ,
MOU Haolei ,
FENG Zhenyu ,
CHENG Kun ,
LIU Yi ,
LIU Xiaochuan ,
BAI Chunyu ,
XI Xulong

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1. Science and Technology Innovation Research Institute, Civil Aviation University of China, Tianjin 300300, China;
2. College of Safety Science and Engineering, Civil Aviation University of China, Tianjin 300300, China;
3. Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics, Aircraft Strength Research Institute of China, Xi'an 710065, China

Received date: 2021-05-31

Revised date: 2022-03-14

Online published: 2022-07-07

Supported by

The Scientific Research Project of Tianjin Municipal Education Commission (2019KJ135); Tianjin Nortural Science Foundation

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摘要

针对大飞机全尺寸三框两段货舱地板下部结构，分别进行3.95 m/s和5.53 m/s的落重冲击试验，对比分析其变形模式和冲击响应特性。建立货舱地板下部结构有限元模型，通过仿真结果与试验结果的相关性分析来验证有限元模型，并进一步分析不同冲击速度对货舱地板下部结构变形模式和冲击响应特性的影响。结果表明：在3.95 m/s冲击下，中间支撑件与机身框连接区域铆钉未发生失效，在5.53 m/s冲击下，中间支撑件与机身框连接区域铆钉发生失效，且最终压缩位移量增大221.0%，最大加速度峰值降低19.9%，最大冲击力峰值降低2.9%。有限元模型能够很好地复现冲击试验过程，准确模拟机身框、中间支撑件及C型支撑件等变形情况，捕捉到中间支撑件与机身框连接区域的铆钉失效情况，在3.95 m/s和5.53 m/s冲击下，仿真与试验获得的最大加速度峰值偏差分别为4%和11.4%。中间支撑件与机身框连接铆钉在4.0~4.5 m/s的速度区间内发生失效，导致货舱地板下部结构整体压缩量迅速增大，中间支撑件吸能占比下降，机身框吸能占比上升。撞击区域铆钉失效对货舱地板下部结构变形模式、冲击响应和吸能特性有显著影响，研究成果可为运输类飞机机身结构适坠性设计、分析及验证提供支持。

关键词： 货舱地板下部结构; 冲击试验; 冲击速度; 变形模式; 冲击响应特性

本文引用格式

解江 , 牟浩蕾 , 冯振宇 , 程坤 , 刘义 , 刘小川 , 白春玉 , 惠旭龙 . 大飞机典型货舱下部结构冲击试验及数值模拟[J]. 航空学报, 2022 , 43(6) : 525890 -525890 . DOI: 10.7527/S1000-6893.2021.25890

Abstract

The typical sub-cargo structures of three-frame sectional fuselage are adopted to investigate their impact behaviors. The deformation mode and impact response characteristics are compared and analyzed numerically as well as experimentally at various vertical impact velocities. The finite element model of the structure is built up and validated by drop tests with impact velocity of 3.95 m/s and 5.53 m/s. The influence of different impact velocities on the deformation mode and impact response characteristics is further discussed. The results show that the rivets connecting the middle stanchions and fuselage frames remain sound at 3.95 m/s impact velocity. However, as the impact velocity is increased to 5.53 m/s, failure of those rivets occurs, with the final compression displacement being increased by 221.0%, the peak acceleration being reduced by 19.9%, and the peak impact force being reduced by 2.9%. The finite element model can well capture the dynamic behavior of sub-cargo structures observed in the impact test, and can predict the deformation of fuselage frames, middle stanchions and C-channel stanchions, as well as failure of rivets. The deviation of the maximum acceleration peak obtained by simulation and test is 4% and 11.4% at two drop test cases, respectively. The rivets in the connection areas between the middle stanchions and fuselage frames are found failed in finite element analysis around the impact velocity range of 4-4.5 m/s. Consequently, the failure of those rivets results in a rapid increase in the overall compression of sub-cargo structure and a decrease in the energy absorption ratio of middle stanchions, and the energy absorption fuselage frames is therefore dominant. The failure of rivets in the impact area can significantly affect the deformation mode, impact response and energy-absorbing characteristics of sub-cargo structure. This investigation provides insights and understanding for crashworthiness design, analysis as well as certification of transport category airplanes.

Key words： sub-cargo structure; impact test; impact velocity; deformation mode; impact response characteristic

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