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

寇剑锋, 徐绯, 纪三红, 张笑宇. 鸟体姿态对结构抗鸟撞性能的影响[J]. 爆炸与冲击, 2017, 37(5): 937-944. doi: 10.11883/1001-1455(2017)05-0937-08
引用本文: 寇剑锋, 徐绯, 纪三红, 张笑宇. 鸟体姿态对结构抗鸟撞性能的影响[J]. 爆炸与冲击, 2017, 37(5): 937-944. doi: 10.11883/1001-1455(2017)05-0937-08
Kou Jianfeng, Xu Fei, Ji Sanhong, Zhang Xiaoyu. Influence of bird yaw/pitch orientation on bird-strike resistance of aircraft structures[J]. Explosion And Shock Waves, 2017, 37(5): 937-944. doi: 10.11883/1001-1455(2017)05-0937-08
Citation: Kou Jianfeng, Xu Fei, Ji Sanhong, Zhang Xiaoyu. Influence of bird yaw/pitch orientation on bird-strike resistance of aircraft structures[J]. Explosion And Shock Waves, 2017, 37(5): 937-944. doi: 10.11883/1001-1455(2017)05-0937-08

鸟体姿态对结构抗鸟撞性能的影响

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

高等学校学科创新引智计划项目 B07050

详细信息
    作者简介:

    寇剑锋(1984—),男,博士研究生

    通讯作者:

    徐绯,E-mail:xufei@nwpu.edu.cn

  • 中图分类号: O383.3;V215.2

Influence of bird yaw/pitch orientation on bird-strike resistance of aircraft structures

  • 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。
  • 图  1  实验中鸟体俯仰旋转

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

    图  2  斜撞角和姿态角

    Figure  2.  Angle of oblique impact and bird orientation

    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

    图  4  鸟体撞击力

    Figure  4.  Impact force of bird-strike

    图  5  板吸收的能量

    Figure  5.  Energy absorbed by panel

    图  6  不同鸟体姿态的板的应力分布

    Figure  6.  Plate stress contour of different bird orientations

    图  7  应力监测点位置

    Figure  7.  Monitoring position of panel stress

    图  8  监测点最大应力值

    Figure  8.  Maximum stresses in monitoring positions

    图  9  雷达罩结构示意图

    Figure  9.  Structural diagram of radome

    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

    图  11  DM处位移

    Figure  11.  Displacement of DM

    图  12  不同姿态下雷达罩吸收的能量

    Figure  12.  Energy absorption by radome

    图  13  机翼前缘变形

    Figure  13.  Deformation of wing leading edge

    图  14  机翼前梁应变

    Figure  14.  Strain of front beam

    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/(°) ηmax/% ηA/% ηB/% ηC/% ηD/% ηE/%
    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
    下载: 导出CSV

    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
    X1c/MPa 309 -
    X1t/MPa 642.9 -
    X2c/MPa 363 -
    X2t/MPa 614 -
    S12/MPa 221 -
    X3c/MPa - 3.84
    X3t/MPa - 4.32
    X13/MPa - 2.14
    X23/MPa - 2.01
    下载: 导出CSV

    表  3  金属材料参数

    Table  3.   Parameters of metallic material

    材料 ρ/(kg·m-3) E /GPa σs/MPa εf
    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
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-01-22
  • 修回日期:  2016-05-11
  • 刊出日期:  2017-09-25

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