大飞机典型货舱下部结构冲击试验及数值模拟-先进飞行器强度技术专刊投稿

解江; 牟浩蕾; 冯振宇

doi:10.7527/S1000-6893.2022.25890

航空学报 >

0 0 - 0

DOI: https://doi.org/10.7527/S1000-6893.2022.25890

大飞机典型货舱下部结构冲击试验及数值模拟-先进飞行器强度技术专刊投稿

解江 ,
牟浩蕾 ,
冯振宇

展开

中国民航大学

收稿日期: 2021-05-31

修回日期: 2022-03-08

网络出版日期: 2022-03-11

基金资助

航空基金;天津市教委科研项目

收起

Impact Tests and Numerical Simulation of Typical Civil Aircraft Sub-Cargo Structure

JIE Jiang ,
MOU Hao-Lei ,
FENG Zhen-Yu

Expand

Received date: 2021-05-31

Revised date: 2022-03-08

Online published: 2022-03-11

Fold

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3.95m/s和5.53m/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3.95m/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5.53m/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，能准确模拟机身框、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3.95m/s和5.53m/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4m/s至4.5m/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，研究成果可为民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; 数值模拟; 冲击速度; 变形模式; 冲击特性

本文引用格式

解江 , 牟浩蕾 , 冯振宇 . 大飞机典型货舱下部结构冲击试验及数值模拟-先进飞行器强度技术专刊投稿[J]. 航空学报, 0 : 0 -0 . DOI: 10.7527/S1000-6893.2022.25890

Abstract

The typical sub-cargo structures of three-frame sectional fuselage are adopted to investigate into their impact behaviors. The defor-mation mode and impact response characteristics are compared and analyzed numerically as well as experimentally at various vertical impact velocities. The finite element model is built up and validated by drop test with impact velocity of 3.95m/s and 5.53m/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 3.95m/s impact velocity. However, with the impact velocity is increased to 5.53m/s, the failure of those rivets are occurred, and the final compression displacement is in-creased by 221.0%, the peak acceleration is reduced by 19.9%, and the peak impact force is 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 the failure of rivets. The deviation of 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 impact velocity range of 4m/s to 4.5m/s. Consequently, the failure of those rivets results in a rapid increase in the overall compression of sub-cargo structure, 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; numerical simulation; impact velocity; deformation mode; impact characteristics

参考文献

[1] GUIDA M, MARULO F, ABRATE S. Advances in crash dynamics for aircraft safety[J]. Progress in Aero-space Sciences, 2018, 98: 106-123.
[2] MOU H L, XIE J, FENG Z Y. Research status and future development of crashworthiness of civil air-craft fuselage structures: An overview. Progress in Aerospace Sciences, 2020, 119: 1-22.
[3] 牟浩蕾, 解江, 冯振宇. 民机机身结构适坠性研究[J]. 交通运输工程学报, 2020, 20(3): 17-39.
MOU H L, XIE J, FENG Z Y．Research on crash-worthiness of civil aircraft fuselage structures [J]. Journal of Traffic and Transportation Engineering, 2020, 20(3): 17-39. (in Chinese)
[4] RICCIO A, SAPUTO S, SELLITTO A. An insight on the crashworthiness behavior of a full-scale compo-site fuselage section at different impact angles[J]. Aerospace. 2019, 6(72): 1-14.
[5] ERIC D, DAVID D. Highly-Nonlinear and transient structural dynamics: a review about crashworthiness of composite aeronautical structures[J]. Aeroelasticity and Structural dynamics, 2018, 14(11): 1-11.
[6] ADAMS A, LANKARANI H M. A modern aerospace modeling approach for evaluation of aircraft fuselage crashworthiness[J]. International Journal of Crash-worthiness, 2003, 8(4): 401-413.
[7] TAY Y Y, BHONGE P S, LANKARANI H M. Crash simulations of aircraft fuselage section in water im-pact and comparison with solid surface impact[J]. In-ternational Journal of Crashworthiness, 2015, 20(5):464-482.
[8] MATHIJSEN D. How safe are modern aircraft with carbon fiber composite fuselages in a survivable crash[J]. Reinforced Plastics, 2018, 62(2): 82-88.
[9] 刘小川, 郭军, 孙侠生, 等. 民机机身段和舱内设施坠撞试验及结构适坠性评估[J]. 航空学报, 2013, 34(9): 2130-2140.
LIU X C, GUO J, SUN X S, et al. Drop test and struc-ture crashworthiness evaluation of civil airplane fu-selage section with cabin interiors[J]. Acta Aeronauti-ca et Astronautica Sinica, 2013, 34(9): 2130-2140. (in Chinese)
[10] REN Y, XIANG J, MENG S，et al. Crashworthiness of civil aircraft subject to soft soil and concrete im-pact surface[J]. Procedia Engineering, Elsevier B.V., 2014, 80: 193–201.
[11] 任毅如, 向锦武, 罗漳平, 等. 客舱地板斜撑杆对民机典型机身段耐撞性能的影响[J]. 航空学报, 2010, 31(2): 271-276.
REN Y R, XIANG J W, LUO Z P, et al. Influence of cabin floor diagonal strut on crashworthiness of typi-cal fuselage section of civil aircraft[J]. Acta Aero-nautica et Astronautica Sinica, 2010, 31(2): 271-276. (in Chinese).
[12] 郑建强, 向锦武, 罗漳平, 等. 民机机身下部结构耐撞性优化设计[J]. 航空学报, 2012, 33(4): 640-649．
ZHENG J Q, XIANG J W, LUO Z P, et al. Crash-worthiness optimization of civil aircraft subfloor struc-ture[J]. Acta Aeronautica et Astroautics Sinca, 2012, 33(4): 640-649. (in Chinese)
[13] 何欢, 陈国平, 张家滨. 带油箱结构的机身框段坠撞仿真分析[J]. 航空学报, 2008, 29(3): 627-633.
HE H, CHEN G P, ZHANG J B. Crash Simulation of fuselage section with fuel tank[J]. Acta Aeronautica et Astroautics Sinca, 2008, 29(3): 627-633. (in Chi-nese)
[14] PUGLIESE S M. B-707 fuselage drop test report, Arv-in/Calspan report, 7252-1[R]. 1984.
[15] JOHNSON D, WILSON A. Vertical drop test of a transport airframe section, DOT/FAA/CTTN 86/34[R]. 1986.
[16] FASANELLA E L, WIDMAYER E, ROBINSON M P. Structural analysis of the controlled impact demon-stration of a jet transport airplane[J]. Journal of Air-craft, 1987, 24(4): 274-280.
[17] JACHSON K E, FASANELLA E L. Crash simulation of vertical drop tests of two Boeing 737 fuselage sec-tions, DOT/FAA/AR-02/62 [R]. 2002.
[18] JACKSON K E, LITTELL J D, Annett M S, et al. Fi-nite element simulations of two vertical drop tests of F-28 fuselage sections, NASA/TM–2018-219807[R]. 2018.
[19] LEPAGE F, CARCIENTE R. A320 fuselage section vertical drop test – part 2 test results, CEAT test report S95 5776/2 [R]. 1995.
[20] LIU X C, GUO J, BAI C, et al. Drop test and crash simulation of a civil airplane fuselage section[J]. Chi-nese Journal of Aeronautics, 2015, 28(2): 447-456.
[21] KUMAKURA I, MINEGISHI M, IWASAKI K, et al. Summary of vertical drop tests of YS-11 transport fu-selage sections[C]//2003 SAE World Aviation Con-gress. Montreal, Canada: SAE, 2003.
[22] HIROKAZU S, HIROMITSU M, KAZUO I, et al. Crashworthiness research on cabin structure at JAXA[C]//5th Triennial International Aircraft Fire and Cabin Safety Research Conference, Atlantic City, 2007.
[23] ARNAUDEAU F, MAHE M, DELETOMBE E, et al. Crashworthiness of aircraft composites structures[C]// ASME 2002 International Mechanical Engineering Congress and Exposition. New Orleans, Louisiana, USA. 2002: 31-40.
[24] DELSART D, PORTEMONT G, WAIMER M. Crash testing of a CFRP commercial aircraft sub-cargo fuse-lage section[J]. Procedia Structural Integrity, 2016, 2: 2198-2205.
[25] JACKSON K E. Analytical crash simulation of three composite fuselage concepts and experimental corre-lation[J]. Journal of the American Helicopter Society, 1997, 42(2): 116-125.
[26] JACKSON K E, FASANELLA E L. Crashworthy evaluation of 1/5 scale model composite fuselage concept, NASA/TM1999-209132[R]. 1999.
[27] 郑建强, 向锦武, 罗漳平, 等. 民机机身耐撞性设计的波纹板布局[J]. 航空学报, 2010, 31(7): 1396-1402.
ZHENG J Q, XIANG J W, LUO Z P, et al. Crashwor-thiness layout of civi1 aircraft using waved-plate for energy absorption[J]. Acta Aeronautica et Astronauti-ca Sinca, 2010, 31(7): 1396-1402. (in Chinese)
[28] HACHENBERG D, LAVINGE V, MAHE M. Crash-worthiness of fuselage hybrid structure[C]// 8th Triennial International Aircraft Fire and Cabin Safety Research Conference (8IARCSFC), Atlantic City, Oc-tober 24-27, 2016: 1-16.
[29] MOSTAFA R. Virtual test & simulation [C]// Engineer-ing, Operations & Technology, Los Angeles, Califor-nia, August 12-14, 2013: 1-24.
[30] WIGGENRAAD J F M, SANTORO D, LEPAGE F, et al. Development of a crashworthy composite fuselage concept for a commuter aircraft, NLR-TP-2001-108 [R]. 2001.
[31] WAIMER M, FESER T, SCHATROW P, et al. Crash concepts for CFRP transport aircraft - comparison of the traditional bend frame concept versus the devel-opments in a tension absorbers concept [J]. Interna-tional Journal of Crashworthiness, 2018, 23(2): 193-218.
[32] CAPRIO F D, IGNARRA M, MARULO F, et al. De-sign of composite stanchions for the cargo subfloor structure of a civil aircraft[J]. Procedia Engineering, 2016, (167): 88-96.
[33] 牟浩蕾, 赵一帆, 刘义, 等. 航空沉头铆钉动态加载试验及失效模式研究[J]. 航空科学技术, 2019, 30(4): 69-78.
MOU H L, ZHAO Y F, LIU Y, et al. Dynamic loading failure experiment and failure mode analysis of aer-onau-tic countersunk rivets [J]. Aeronautical Science & Tech-nology, 2019, 30(4): 69-78. (in Chinese)
[34] 冯振宇, 李恒晖, 刘义, 等. 中低应变率下7075-T7351铝合金本构与失效模型对比[J]. 材料导报, 2020.
FENG Z Y, LI H H, LIU Y, et al. Comparison of con-stitutive failure models of 7075-T7351 alloy at in-termediate and low strain rates[J]. Materials Reports, 2020. (in Chinese)
[35] 冯振宇, 解江, 李恒晖, 等. 大飞机货舱地板下部结构有限元建模与适坠性分析[J]. 航空学报, 2019, 40(2): 115-126.
FENG Z Y, XIE J, LI H H, et al. FE modeling and crashworthiness analysis of large aeroplane sub-cargo structure[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(2): 115-126. (in Chinese)
[36] 冯振宇, 程坤, 赵一帆, 等. 运输类飞机典型货舱地板下部结构冲击吸能特性研究[J]. 航空学报, 2019, 40(9): 208-220.
FENG Z Y, CHENG K, ZHAO Y F, et al. Study on impact energy-absorbing characteristics of typical sub-cargo fuselage section of transport aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(9): 208-220. (in Chinese)

Options

文章导航

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献