民机机身框段和全机坠撞响应对比

doi:10.7527/S1000-6893.2025.31597

Abstract

Abstract:

The crashworthiness of an aircraft is the focus of its structural safety design and evaluation， and the relationship between the fuselage frame segment and the full-aircraft structure in terms of crash response has been one of the unresolved issues. In this paper， a vertical drop test with a fuselage frame segment with cabin door and a typical full-scale civil aircraft were conducted， and the results were compared. Then， a dynamic model of the full-aircraft crash was established and validated based on the experimental data from the full-aircraft crash. Furthermore， the model trimming method was used to obtain the crash dynamics models of the fuselage frame segment with a cabin door， the forward fuselage， and aft fuselage， and simulations were conducted under the experimental conditions. Based on the simulation results， differences between the crash responses of different fuselage frame segments and the full-aircraft structure were explored. The results show that the established full-aircraft crash dynamics model has high predictive accuracy， the predicted dynamic response of the structure is consistent with the experimental， and the deformation and movement process of the structure are consistent the experimental results， proving the accuracy of the model trimming method. The deformation of the floor structure and the floor acceleration of the fuselage frame segment with a cabin and the aft fuselage are less than those of the full-aircraft structure， the maximum deviation of the acceleration peak is 13.6%， and the damage modes are significantly different. For forward fuselage， the deformation is greater than that of the full-aircraft structure， but the floor acceleration is still less than that of the full-aircraft structure， with a maximum deviation of the acceleration peak reaching 17.2%. This reveals that the boundary conditions and energy input of the full-aircraft and the fuselage frame segment experiment pieces are fundamentally different， leading to significant differences in crash response. the verification and evaluation of aircraft crashworthiness， different verification methods and objects should be used for different verification targets. Using the full-aircraft structure for crashworthiness verification provides the most realistic results， while using the fuselage frame segment can verify the crash simulation model to support the simulation-based aircraft crashworthiness assessment. Additionally， fuselage segment with a cabin door and the aft fuselage are greatly affected by the contraction of the aircraft’s nose and tail during a crash， and thus are not suitable as verification objects for aircraft crashworthiness. When using the forward fuselage as the verification object for aircraft crashworthiness， the end frame of the experiment needs to be strengthened to simulate actual boundary stiffness conditions as closely as possible.

Key words: impact dynamics, civil aircraft, full-scale crash, fuselage sectional crash, crash response

CLC Number:

V271.1

Xulong XI, Xiaochuan LIU, Chunyu BAI, Hezhao HAN, Xinyue ZHANG, Xiaocheng LI, Pu XUE, Rangke MU, Xianfeng YANG. Comparison of crash response between fuselage section and full-scale civil aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(15): 231597.

Figures/Tables 46

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 1

Fig.9

Fig.10

Table 2

Fig.11

Table 3

Table 4

Fig.12

Fig.13

Fig.14

Table 5

Fig.15

Table 6

Fig.16

Fig.17

Fig.18

Table 7

Table 8

Fig.19

Fig.20

Fig.21

Table 9

Table 10

Fig.22

Fig.23

Fig.24

Fig.25

Table 11

Fig.26

Fig.27

Fig.28

Fig.29

Table 12

Fig.30

Fig.31

Fig.32

Fig.33

Table 13

References 26

[1]	刘小川，白春玉，惠旭龙，等. 民机机身结构耐撞性研究的进展与挑战［J］. 固体力学学报， 2020， 41（4）： 293-323.
	LIU X C， BAI C Y， XI X L， et al. Progress and challenge of research on crashworthiness of civil airplane fuselage structures［J］. Chinese Journal of Solid Mechanics， 2020， 41（4）： 293-323 （in Chinese）.
[2]	LOGUE T V， MCGUIRE R J， REINHARDT J W， et al.Vertical drop test of a narrow-body fuselage section with overhead stowage bins and auxiliary fuel tank system on board：DOT/FAA/CT-94/116［R］.Washington，D.C.：FAA， 1995.
[3]	ABRAMOWITZ A， SMITH T G， VU T. Vertical drop test of a narrow-body transport fuselage section with a conformable auxiliary fuel tank onboard ： DOT/FAA/AR-00/56［R］. Washington， D.C.： FAA， 2000.
[4]	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 structure crashworthiness evaluation of civil airplane fuselage section with cabin interiors［J］. Acta Aeronautica et Astronautica Sinica， 2013， 34（9）： 2130-2140 （in Chinese）.
[5]	张欣玥，惠旭龙，刘小川，等. 典型金属民机机身结构坠撞特性试验［J］. 航空学报， 2022， 43（6）： 526234.
	ZHANG X Y， XI X L， LIU X C， et al. Experimental study on crash characteristics of typical metal civil aircraft fuselage structure［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（6）： 526234 （in Chinese）.
[6]	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 crashworthiness of civil aircraft fuselage structures［J］. Journal of Traffic and Transportation Engineering， 2020， 20（3）： 17-39 （in Chinese）.
[7]	KUMAKURA I， MINEGISHI M， IWASAKI K， et al. Summary of vertical drop tests of YS-11 transport fuselage sections［C］∥2003 SAE World Aviation Congress. 2003.
[8]	LIU X C， BAI C Y， XI X L， et al. Impact response and crashworthy design of composite fuselage structures： An overview‍［J］. Progress in Aerospace Sciences， 2024， 148： 101002.
[9]	MOU H L， XIE J， FENG Z Y. Research status and future development of crashworthiness of civil aircraft fuselage structures： An overview‍［J］. Progress in Aerospace Sciences， 2020， 119： 100644.
[10]	刘小川，张欣玥，惠旭龙，等. 结构修理对民机机身耐撞性的影响［J］. 航空学报， 2023， 44（10）： 227517.
	LIU X C， ZHANG X Y， XI X L， et al. Influence of structural repairs on crashworthiness of civil aircraft fuselage［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（10）： 227517 （in Chinese）.
[11]	TANG H， ZHU S H， LIU X C， et al. Impact of crash environments on crashworthiness of fuselage section［J］. Transactions of Nanjing University of Aeronautics and Astronautics， 2022， 39（S01）： 1-8.
[12]	邹田春，牟浩蕾，任健，等. 滚转角度对民机机身结构耐撞性能的影响［J］. 机械强度， 2014， 36（1）： 139-143.
	ZOU T C， MOU H L， REN J， et al. Effects of roll angles on civil aircraft fuselage crashworthiness［J］. Journal of Mechanical Strength， 2014， 36（1）： 139-143 （in Chinese）.
[13]	牟浩蕾，谢威威，解江，等. 坠撞环境下乘员伤害分析及飞机适坠性评估［J］. 航空学报， 2024， 45（3）： 228786.
	MOU H L， XIE W W， XIE J， et al. Occupant injury analysis and aircraft crashworthiness evaluation under crash scenarios［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（3）： 228786 （in Chinese）.
[14]	石霄鹏，钟欣言，牟浩蕾，等. 垂向冲击下的民机乘员腰椎载荷研究［J］. 航空学报， 2024， 45（8）： 229108.
	SHI X P， ZHONG X Y， MOU H L， et al. Lumbar load of seated occupant under vertical impact［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（8）： 229108 （in Chinese）.
[15]	施萌，汪洋，吴志斌，等. 民机货舱下部复合材料结构抗坠撞吸能特性试验研究［J］. 复合材料科学与工程， 2021（9）： 83-88.
	SHI M， WANG Y， WU Z B， et al. Study on the anti-crash energy absorption characteristic of composite structure in the sub-cargo structure［J］. Composites Science and Engineering， 2021（9）： 83-88 （in Chinese）.
[16]	XI X L， XUE P， LIU X C， et al. Energy absorption and failure modes of different composite open-section crush elements under axial crushing loading‍［J］. Materials， 2024， 17（13）： 3197.
[17]	YU Z F， ZHOU X， ZHOU X， et al. Crashworthy subfloor structure of civil aircraft inclined inward-folding composite tubes‍［J］. Composites Part B： Engineering， 2020， 189： 107887.
[18]	朱鲜飞，冯蕴雯，薛小锋，等. 基于乘员响应的民机典型机身段结构适坠性分析与评估［J］. 机械强度， 2020， 42（3）： 617-630.
	ZHU X F， FENG Y W， XUE X F， et al. Analysis and evaluation fuselage section’s crashworthiness of typical civil airplane based on passenger response‍［J］. Journal of Mechanical Strength， 2020， 42（3）： 617-630 （in Chinese）.
[19]	JACKSON K E， LITTELL J D， ANNETT M S， et al. Finite element simulations of two vertical drop tests of F-28 fuselage sections： NASA/TM-2018-219807‍［R］.Washington， D.C.： NASA， 2018.
[20]	LITTELL J D. A summary of results from two full-scale F28 fuselage section drop tests： NASA/TM-2018-219829 ［R］. Washington， D.C.： NASA， 2018.
[21]	KAREN E J， JACOB B P. Development of a full-scale finite element model of the fokker F28 fellowship aircraft and crash simulation predictions‍［C］‍∥Earth & Space Conference. 2018.
[22]	KAREN E J， JACOB B P.Simulation of a full-scale crash test of a fokker F28 fellowship aircraft： NASA/TM-2020-220435 ［R］. Washington， D.C.： NASA， 2020.
[23]	ABRAMOWITZ A， SMITH T G， VU T， et al. Vertical drop test of an ATR42-300 airplane： DOT/FAA/AR-05/56 ［R］. Washington， D.C.： FAA， 2006.
[24]	JACKSON K E， FASANELLA E L. Crash simulation of a vertical drop test of a commuter-class aircraft［J］. International Journal of Crashworthiness， 2005， 10（2）： 173-182.
[25]	KAREN E J， EDWIN L F. Development of an LS-DYNA model of an ATR42-300 aircraft for crash simulation［C］∥ Proceedings of the Eighth International LS-DYNA Users Conference， 2004.
[26]	刘小川，惠旭龙，张欣玥，等. 典型民用飞机全机坠撞实验研究［J］. 航空学报， 2024， 45（5）： 529664.
	LIU X C， XI X L， ZHANG X Y， et al. Full-scale crash experimental study of typical civil aircraft［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（5）： 529664 （in Chinese）.

时间/s	框段正面	框段背面	框段侧面	全机结构
0
0.03
0.06
0.25
0.8

位置	含舱门机身框段	全机结构
舱门结构
客舱前端内饰隔板
地板结构
地板下部隔框
机身下部蒙皮

材料牌号	密度/（10^-9 t∙mm^-3）	泊松比	屈服强度/MPa	弹性模量/GPa	硬化模量/MPa	失效应变
2A12	2.77	0.33	370	72	830	0.15
2024	2.7	0.33	345	71	777	0.16
2A50	2.75	0.33	360	71	450	0.13
7A04	2.7	0.33	460	70	700	0.14

关键参量	实验结果/kN	仿真结果/kN	误差/%
初始载荷峰值	2 350	2 520	7.2
平台载荷均值	835	875	4.8
脉宽	225	200	11

测试点	M9	M13	M15	M17	M27	M34
实验变形量/mm	76	101	154	212	290	353
仿真变形量/mm	64	98	159	222	282	324
误差/%	18.8	3.0	3.1	4.5	2.8	9.0

Comparison of crash response between fuselage section and full-scale civil aircraft

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 46

References 26

Related Articles 15

Recommended Articles

Metrics

Comments

机身位置	实验结果	仿真结果
驾驶舱段下部蒙皮
含舱门段下部蒙皮
前机身等直段下部蒙皮
中央翼段下部蒙皮
后机身等直段下部蒙皮
后舱门段下部蒙皮

建模方法	具体建议
模型简化	机体结构采用精细模型，座椅和假人可用集中质量模拟，发动机和起落架可采用集中质量模拟，需确保简化后有限元模型与实验件质量和惯量的一致。对于带有行李箱、辅助油箱、应急舱门等特殊机身段，需进行等效建模，确保其与机身连接刚度一致，附加质量相同。
边界条件	对机身段端框进行刚度等效模拟，通过机身段和全机仿真分析进行对比验证，确保端框处的变形模式一致。
数据处理	仿真分析模型的数据采样设置与坠撞实验的采样率保持一致，对加速度、坠撞载荷等动响应的滤波方法也保持一致。
模型验证	通过机身段坠撞实验数据对有限元模型进行验证，对比的动响应至少包括实验件运动过程、坠撞载荷、地板加速度、地板下部结构变形、局部结构的损伤破坏等。

[1]	Junfu LI, Qing CHEN, Wei WANG, Zhonghua HAN, Yuting TAN, Yulin DING, Lu XIE, Jianling QIAO, Ke SONG, Junqiang AI. Design of low sonic boom high efficiency layout for advanced supersonic civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629613-629613.
[2]	Xiaochuan LIU, Xulong XI, Xinyue ZHANG, Chunyu BAI, Yabin YAN, Xiaocheng LI, Rangke MU. Full⁃scale crash experimental study of typical civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529664-529664.
[3]	Rui SI, Yong CHEN. Application trends of additive manufacturing technology for civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529677-529677.
[4]	Haolei MOU, Weiwei XIE, Jiang XIE, Zhenyu FENG, Lanhui LIN. Occupant injury analysis and aircraft crashworthiness evaluation under crash scenarios [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 228786-228786.
[5]	Chengjun SHAN, Tianyu GONG, Lizhe YI, Haohui YANG, Yaosong LONG. High-efficiency and high-reliability sonic boom/aerodynamic multidisciplinary optimization method for supersonic civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(24): 630573-630573.
[6]	Meng LI, Xingyi CHEN, Jichang CHEN, Bin WU, Mingbo TONG. Numerical analysis of civil aircraft ditching performance in wave condition [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 28-43.
[7]	Yongjie ZHANG, Jingpiao ZHOU, Lei SHI, Dong LI, Binqian ZHANG. Optimization design method of central fuselage spherical deficient surface frames in blended⁃wing⁃body civil aircraft based on PRSEUS structure [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(12): 229331-229331.
[8]	Chunpeng LI, Zhansen QIAN, Xiasheng SUN. Trailing edge deformation matrix aerodynamic design for long-range civil aircraft variable camber wing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 127335-127335.
[9]	Xuhan ZHANG, Yi CAO, Jingnan SUN, Shunzhi PAN. Comparative study on weight analysis methods of cabin air parameters in civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(20): 228480-228480.
[10]	Di WANG, Yan LENG, Long YANG, Zhonghua HAN, Zhansen QIAN. Atmospheric turbulence effects on sonic boom propagation based on augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626318-626318.
[11]	Yunwen FENG, Xinyi LIN, Xiaofeng XUE, Xiang YANG, Jiaqi LIU. Design of civil aircraft explosion-proof structure for high reliable one-way blasting [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 228297-228297.
[12]	Qing GUO, Deming GUAN. Human factor reliability prediction model for civil aircraft maintenance task analysis [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(16): 228051-228051.
[13]	Xiaochuan LIU, Xinyue ZHANG, Xulong XI, Yabin YAN, Juntai MA. Influence of structural repairs on crashworthiness of civil aircraft fuselage [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(10): 227517-227517.
[14]	Wenhao BI, Qiucen FAN, Delin LI, An ZHANG. Modeling approach for forward design of civil aircraft based on multiple perspectives [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(10): 227536-227536.
[15]	Xiong HUANG, Shiru QU, Heng ZHANG, Xiantiao CHEN. Stall performance of high-lift configuration of large civil aircraft with slat de-icing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627077-627077.

时刻/s	实验结果（侧视图）	仿真结果（侧视图）	仿真结果（仰视图）
0
0.012
0.016
0.130

时刻/s	舱段正面	全机正面	全机侧面
0
0.03
0.06
0.40

时刻/s	舱段正面	全机正面	舱段侧面	全机侧面
0
0.03
0.06
0.4

时刻/s	舱段正面	舱段侧面	全机正面	全机侧面
0
0.03
0.06
0.40