大型运输类飞机典型机身框段坠撞特性分析

doi:10.7527/S1000-6893.2022.27512

Abstract

Abstract:

To study the crashworthiness characteristics and failure mode of large transport aircraft and develop the finite element modeling and crashworthiness simulation technology of fuselage structures， a three-frame and two-span full-scale fuselage section with two sets of triple seats installed and four FAA Hybrid III Anthropomorphic Test Devices （ATD） placed is firstly designed and manufactured； the crash deformation and response characteristics are then obtained by carrying out a drop test of the typical fuselage section； Finally， a finite element model of fuselage section is established and verified by the drop test results， and the crashworthiness characteristics are evaluated when hitting different grounds （concrete ground and soft grounds）. The results show that at the vertical impact velocity of 6.02 m/s， the upper area of the cabin floor remains basically intact， and the sub-cabin structures are significantly deformed and damaged， resulting in three plastic hinges； the cargo floor beam breaks on one side where it joins the fuselage frame， resulting in a significantly faster peak acceleration of the cabin floor on the same side than on the other side， and the maximum acceleration peak value and impact force are 427.7 m/s² and 290.8 kN， respectively. The finite element model can accurately simulate the three plastic hinges and the failure of the connection between the cargo floor beam and the fuselage frame， and it is in good agreement with the test results in terms of impact velocity and acceleration. The fuselage frame is the main energy-absorbing component， accounting for 40.7% of the total absorbed energy； when hitting different grounds， the partial impact energy is absorbed by the soft ground， resulting in slightly different failure modes of the fuselage section and a reduction in the peak acceleration transmitted to the occupants.

Key words: fuselage section, crashworthiness characteristics, failure mode, drop test, transport aircraft

CLC Number:

V223

Haolei MOU, Jiang XIE, Zhenyu FENG, Kun CHENG, Yi LIU. Crashworthiness characteristics analysis of typical fuselage section of large transport aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 227512-227512.

Figures/Tables 26

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序号	国家或地区	试验对象	试验年份	撞击速度/ （m·s^-1）	撞击面
1	美国	707机身框段	1980	6.10	刚硬地面
2	美国	707机身框段（含辅助油箱）	1993	9.14	刚硬地面
3	欧盟	A320机身框段	1993	7.00	刚硬地面
4	欧盟	A320机身框段	1995	6.70	刚硬地面
5	美国	737-200机身框段（含辅助油箱）	1999	9.14	刚硬地面
6	欧盟	A320机身框段	1999	6.78	刚硬地面
7	美国	737-100机身框段（含货舱货物）	2000	9.14	刚硬地面
8	美国	F-28机身框段	2001	9.20	刚硬地面
9	日本	YS-11机身框段	2001	6.10	刚硬地面
10	日本	YS-11机身框段（含货舱货物）	2002	7.40	刚硬地面
11	美国	波音787机身框段	2007	9.14	刚硬地面
12	中国	支线客机机身框段	2012	6.85	刚硬地面
13	美国	F-28机身框段（机身翼盒）	2017	8.90	砂石土面
14	美国	F-28机身框段（含货舱货物）	2017	8.87	软土地面
15	美国	Hawker 4000机身框段	2017	9.14	刚硬地面
16	欧盟	复合材料飞机机身框段	2017	9.14	刚硬地面
17	中国	大型运输类飞机机身框段	2019	6.02	刚硬地面
18	中国	典型金属民机机身框段	2020	5.91	刚硬地面
19	美国	挑战者601机身框段（中央翼盒段）	2021	9.14	刚硬地面

部件	材料	密度 ρ /（10^-6 kg·mm^-3）	弹性模量 E /GPa	泊松比 μ	屈服应力 σ_y /MPa	极限应变 ε
机身框（含剪切角片）	2024-T42	2.67	72.4	0.33	275.000	0.18
长桁	2099-T83	2.63	78.6	0.31	475.755	0.10
蒙皮	2024-T3	2.67	72.4	0.33	324.065	0.16
货舱纵梁	2196-T8511	2.63	76.5	0.31	510.230	0.10
地板连接角片，立柱	7075-T7351	2.70	72.4	0.33	623.000	0.10
上部桁架	钢	7.80	210.0	0.30

牌号	材料	密度 ρ /（10^-6 kg·mm^-3）	弹性模量 E /GPa	泊松比 μ	屈服应力 σ_y /MPa	极限拉伸载荷 T_u /N	极限剪切载荷 N_u /N
MS20470AD5-6	7050-T73	2.82	72.4	0.33	441.3	5 093	3 738
NAS1097KE5-6	7050-T73	2.82	72.4	0.33	441.3	3 665	5 051
MS20470E5-6	2017-T4	2.70	72.4	0.33	379.2	6 300	4 389
NAS1465-03	合金钢	7.80	210.0	0.33	500.0	7 702	9 359
CFBL1001AG5-2	钛合金	4.50	117.0	0.33
CFBL1002AG5-2	钛合金	4.50	117.0	0.33
CFBL1003AG5-2	钛合金	4.50	117.0	0.33

地面类型	HWS	LDD	SOIL B	HDI
密度/（10^-9t·mm^-3）	1.46	1.28	1.29	1.60
剪切模量G/MPa	1.84	1.39	3.17	3.25
卸载模量K/MPa	68.95	224.00	168.00	110.87
常数 a₀/MPa²	0	0	6.18×10^-6	6.52×10^-5
常数 a₁/MPa	0	0	5.14×10^-3	1.29×10^-2
常数 a₂	0.300 0	0.504 2	1.068 0	0.636 8

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Crashworthiness characteristics analysis of typical fuselage section of large transport aircraft

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