鸟体姿态对结构抗鸟撞性能的影响

寇剑锋; 徐绯; 纪三红; 张笑宇

doi:10.11883/1001-1455(2017)05-0937-08

摘要: 低于现行标准规定能量的大量鸟撞事故中，航空结构仍然发生实质性破坏的情况，说明只考虑鸟体的质量和速度不足以保证飞机安全。本文中针对弹性平板、雷达罩及机翼前缘等飞机典型结构，开展了不同姿态鸟体的鸟撞分析研究。分析结果发现，鸟体姿态对结构的抗鸟撞性能有比较显著的影响，不同的结构特点反映的响应规律也不同：对吸能结构，姿态角越大，吸收的能量越多，被保护的结构就越安全；而对承力结构，姿态角越大，高应力区域越大，结构就越危险。因此，在结构的抗鸟撞安全性评估中，除了完成特定姿态鸟体的鸟撞实验，针对危险工况还应通过数值分析评估不同鸟体姿态的结构撞击响应，进一步确保结构的抗鸟撞能力。

关键词:

Abstract: There have been numerous bird-strike accidents in which substantial damage to the airframe occurred even though the striking force involved did not reach the energy standard currently required, showing that only taking mass and velocity into account in bird-strike prevention cannot guarantee airframe safety. In order to find out the effect of the bird yaw/pitch orientation on the safety of different aircraft structures, the dynamic responses on the panel, the radome, and the plane wing's leading edge were investigated. The results show that the bird-strike resistance of the structure is significantly affected by the bird's yaw/pitch orientation, and different structural characteristics lead to different dynamic responses. The greater the attitude angle, the more energy absorbed for the energy-absorbing structure, and accordingly the safer the protected structure; for the load-bearing structure, the greater the attitude and the larger the high stress area on the structure, the more vulnerable the structure. Therefore, in the evaluation of aircraft structures' bird-strike resistance capability, apart from doing the bird-strike experiment, it is also necessary to investigate different responses of various bird yaw/pitch orientations to the hazardous parts of aircraft structures through numerical simulation.

Key words:

图 1 实验中鸟体俯仰旋转

Figure 1. Pitch rotation of bird in bird-strike experiment

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图 2 斜撞角和姿态角

Figure 2. Angle of oblique impact and bird orientation

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图 3 不同俯仰姿态的鸟体撞击模型

Figure 3. Numerical models of bird-strike ofdifferent bird pitch angles

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图 4 鸟体撞击力

Figure 4. Impact force of bird-strike

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图 5 板吸收的能量

Figure 5. Energy absorbed by panel

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图 6 不同鸟体姿态的板的应力分布

Figure 6. Plate stress contour of different bird orientations

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图 7 应力监测点位置

Figure 7. Monitoring position of panel stress

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图 8 监测点最大应力值

Figure 8. Maximum stresses in monitoring positions

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图 9 雷达罩结构示意图

Figure 9. Structural diagram of radome

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图 10 不同姿态下计算结果与实验结果对比

Figure 10. Comparison of numerical and experimental results

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图 11 DM处位移

Figure 11. Displacement of DM

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图 12 不同姿态下雷达罩吸收的能量

Figure 12. Energy absorption by radome

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图 13 机翼前缘变形

Figure 13. Deformation of wing leading edge

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图 14 机翼前梁应变

Figure 14. Strain of front beam

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表 1 不同鸟体姿态在监测点应力与0°的偏差

Table 1. Deviation of panel stress between 0° orientation and the others

α/(°)	η_max/%	η_A/%	η_B/%	η_C/%	η_D/%	η_E/%
22.5	-4.1	2.0	-0.6	2.6	-1.5	-1.3
45.0	-2.5	0.8	1.0	11.7	6.1	0
67.5	1.4	8.5	4.0	28.9	19.2	18.7
90.0	3.6	25.5	7.3	109.7	75.8	55.0

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表 2 非金属材料参数

Table 2. Parameters of non-metallic material

量和单位	玻璃纤维增强材料	蜂窝材料
ρ/(kg·m^-3)	1 900	64
E₁₁/MPa	27 300	-
E₂₂/MPa	26 500	-
E₃₃/MPa	-	71.68
G₁₂/MPa	4 390	-
G₁₃/MPa	-	76.11
G₂₃/MPa	-	35.44
X_1c/MPa	309	-
X_1t/MPa	642.9	-
X_2c/MPa	363	-
X_2t/MPa	614	-
S₁₂/MPa	221	-
X_3c/MPa	-	3.84
X_3t/MPa	-	4.32
X₁₃/MPa	-	2.14
X₂₃/MPa	-	2.01

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表 3 金属材料参数

Table 3. Parameters of metallic material

材料	ρ/(kg·m^-3)	E /GPa	σ_s/MPa	ε_f
7050-T7451	2 820	70	448	0.095
LY12-CZ	2 780	71	424	0.127
2024-T351	2 780	70	310	0.089
7075-T7351	2 800	72	395	0.086

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