民用飞机加装辅助燃油箱坠撞试验及仿真分析

王嘉琪; 汪洋; 李琪; 吴志斌

doi:10.11883/bzycj-2024-0522

民用飞机加装辅助燃油箱坠撞试验及仿真分析

doi: 10.11883/bzycj-2024-0522

王嘉琪^1,,
汪洋^{1, 2, ,},
李琪¹,
吴志斌^{1, 3}

1.
上海飞机设计研究院，上海 201210
2.
西北工业大学民航学院，陕西西安710072
3.
西北工业大学航空学院，陕西西安710072

基金项目: 国家自然科学基金（U2433203）

详细信息

作者简介:
王嘉琪（1994－　），女，硕士，工程师，cixintn@163.com

通讯作者:
汪　洋（1988－　），女，硕士，研究员，wangyang3@comac.cc

中图分类号: O389; V271.1
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- 文章访问数: 133
- HTML全文浏览量: 17
- PDF下载量: 72
- 被引次数: 0
出版历程
- 收稿日期: 2024-12-31
- 修回日期: 2025-05-07
- 网络出版日期: 2025-05-07
- 刊出日期: 2025-07-05

Crash tests and simulation analysis for civil aircraft equipped with an auxiliary fuel tank

WANG Jiaqi^1
,,
WANG Yang^{1, 2
, ,},
LI Qi¹,
WU Zhibin^{1, 3}

1.
Shanghai Aircraft Design and Research Institute, Shanghai 201210, China
2.
School of Civil Aviation, Northwestern Polytechnical University, Xi’an 710072, Shaanxi, China
3.
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, Shaanxi, China

摘要

摘要: 针对典型民用飞机机身下部结构加装辅助燃油箱，开展了冲击速度为1.53、2.78和5.96 m/s的垂直坠撞试验，研究了辅助燃油箱对机身下部结构的触地冲击响应、结构变形和破坏模式的影响。对比仿真与试验结果，验证了加装辅助燃油箱的机身下部结构有限元模型的有效性，通过仿真分析了垂直坠撞过程中的结构吸能形式。结果表明：在冲击速度为1.53 m/s的工况下，机身下部结构以弹性变形为主，仅有轻微的塑性变形；在冲击速度为2.78 m/s的工况下，机身框、蒙皮及货舱地板T形支撑件以弯曲变形为主，整体结构压缩程度较小，货舱地板T形支撑件与左侧地板滑轨连接失效后翘起，未触及油箱；在冲击速度为5.96 m/s的工况下，机身下部结构压缩变形严重，左侧斜支撑受压发生断裂，辅助燃油箱下沉至货舱地板。仿真的坠撞触地撞击力和典型位置加速度变化趋势与试验结果吻合较好，能有效模拟坠撞过程中结构的变形和破坏情况。仿真结果表明，在加装辅助燃油箱的机身下部结构的坠撞试验中，机身框是主要的变形吸能部件，蒙皮和辅助燃油箱是次要的变形吸能结构；随着辅助燃油箱装油质量的增加，仿真得到的辅助燃油箱和机身下部结构组件的吸收冲击能量增加，破坏更严重。
- 民用飞机 /
- 辅助燃油箱 /
- 机身下部结构 /
- 坠撞试验 /
- 冲击响应 /
- 变形模式
Abstract: A study was conducted to investigate the crash impact response of the lower fuselage structure of a typical civil aircraft with an auxiliary fuel tank installed. The results of vertical crash tests conducted at impact velocities of 1.53, 2.78 and 5.96 m/s were obtained. These results include the influence of installing auxiliary fuel tanks on the impact response and the structural deformation and damage of the lower fuselage structure. The validity of the corresponding finite element model was verified through a correlation analysis between the simulation and test results. The impact energy absorption form during the vertical crash process was analyzed through simulation results. The results show that the structure mainly deforms elastically with only slight plastic deformation under the impact condition of 1.53 m/s. Under the impact condition of 2.78 m/s, the fuselage frames, skin, and T-shaped support components of the cargo floor are mainly deformed by bending, and the total structures were slightly compressed. The T-shaped support components connected to the left cargo floor slide rails extended upward and did not touch the fuel tank. Under the impact condition of 5.96 m/s, the lower fuselage structures were seriously compressed and the left diagonal brace was fractured under pressure. The auxiliary fuel tank sank to the cargo floor. The simulation analysis can effectively model the deformation and damage of the structure during the vertical crash process at different impact velocities. The impact force on the ground and the trend of acceleration at typical locations obtained by analysis are in good agreement with the test results. The analysis results show that the fuselage frame is the main deformation and energy absorption component in the crash of the lower fuselage structure equipped with auxiliary fuel tanks. The skin and auxiliary fuel tank are the secondary structures that participate in deformation and energy absorption. As the auxiliary fuel tank is filled with more fuel, the simulation results show that the energy absorption capacity of the auxiliary fuel tank and the lower fuselage structure components increases, i.e., the degree of damage becomes more serious. The research results can provide support for the anti-crash design, analysis, and verification of the fuselage structure of civil aircraft with auxiliary fuel tanks installed.
- civil aircraft /
- auxiliary fuel tank /
- lower fuselage structure /
- crash test /
- impact response /
- deformation mode

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图 1 试验件装配示意图

Figure 1. Assembly diagram of the test specimen

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图 2 典型机身下部结构试验件示意图

Figure 2. Schematic diagram of typical fuselage substructure test specimen

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图 3 坠撞试验方案示意图

Figure 3. Schematic diagram of crash test scheme

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图 4 试验件加速度传感器位置

Figure 4. Acceleration sensor locations on the test specimen

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图 5 试验1～3的冲击速度-时间曲线

Figure 5. Impact velocity-time curves of tests 1 to 3

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图 6 试验1～3的触地撞击力-时间曲线

Figure 6. Impact force-time curves of tests 1 to 3

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图 7 试验1中上部桁架假件的加速度-时间曲线

Figure 7. Acceleration-time curves of the upper truss components of test 1

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图 8 试验2中上部桁架假件的加速度-时间曲线

Figure 8. Acceleration-time curves of the upper truss components of test 2

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图 9 试验3中上部桁架假件的加速度-时间曲线

Figure 9. Acceleration-time curves of the upper truss components of test 3

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图 10 试验1中坠撞后的结构变形

Figure 10. Deformation of the structure after crash in test 1

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图 11 试验2中坠撞后的结构变形

Figure 11. Deformation of the structure after crash in test 2

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图 12 试验3中结构的坠撞变形过程

Figure 12. Deformation process of the structure during crash test 3

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图 13 试验3中坠撞后的结构变形

Figure 13. Deformation of the structure after crash in test 3

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图 14 加装辅助燃油箱机身结构的坠撞有限元模型

Figure 14. Finite element model of the fuselage structurewith an auxiliary fuel tank

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图 15 仿真和试验1～3的结构变形结果对比

Figure 15. Simulation results of the structural deformation of fuselage with an auxiliary fuel tank from tests 1 to 3

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图 16 仿真和试验1的触地撞击力对比

Figure 16. Comparison of the simulationbetween test impact forces for test 1

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图 17 仿真和试验2的触地撞击力对比

Figure 17. Comparison of the simulationbetween test impact forces for test 2

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图 18 仿真和试验3的触地撞击力对比

Figure 18. Comparison of impact force between simulation and test 3

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图 19 仿真和试验1的加速度对比

Figure 19. Comparison of the simulation between test accelerations for test 1

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图 20 仿真和试验2的加速度对比

Figure 20. Comparison of acceleration between simulation and test 2

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图 21 仿真和试验3的加速度对比

Figure 21. Comparison of acceleration between simulation and test 3

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图 22 试验2的仿真中，各组件的吸能对比

Figure 22. Comparison of energy absorption of each component in the simulation of test 2

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图 23 试验3的仿真中，各组件的吸能对比

Figure 23. Comparison of energy absorption of each component in the simulation of test 3

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图 24 不同冲击速度下辅助燃油箱吸能和机身下部结构吸能随装油量的变化

Figure 24. Energy absorption of the auxiliary fuel tank changing and the lower fuselage structure changingwith fuel mass at different impact velocities

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表 1 机身结构及辅助燃油箱的材料参数

Table 1. Material parameters of fuselage structure and auxiliary fuel tank

材料牌号	密度/(kg·m⁻³)	弹性模量/GPa	泊松比	屈服强度MPa	硬化模量/MPa	失效应变
2524-T3	2768	71	0.35	310	759	0.15
7075-T62	2796	71	0.33	427	744	0.09
7050-T7451	2823	71	0.33	434	826	0.09
7050-T76511	2823	71	0.33	469	978	0.07
15-5PH-固溶-H1025	7833	197	0.27	1000	600	0.12

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表 2 不同装油量工况下各组件的吸能分析

Table 2. Energy absorption of each component in the case of different oil capacities

装油量/kg	冲击速度/(m·s⁻¹)	吸能/J			吸能占比/%
装油量/kg	冲击速度/(m·s⁻¹)	机身下部结构组件	上部桁架	辅助燃油箱	机身下部结构组件	上部桁架	辅助燃油箱
124	2.78	2432	616	518	68.2	17.3	14.5
248		2970	507	674	71.5	12.2	16.3
372		3956	527	826	74.5	9.9	15.6
496（试验）		5684	596	976	78.3	8.2	13.5
124	5.96	13929	2062	1231	80.9	12.0	7.1
248		15483	2329	1768	79.1	11.9	9.0
372		16789	2649	2393	76.9	12.1	11.0
496（试验）		18067	2647	3260	74.5	12.1	13.4

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