飞机前风挡非对称结构的鸟撞数值模拟

Simulating Aircraft's Asymmetrical Windshield Subjected to Bird Impact

1.
College of Equipment Engineering, Shenyang Ligong University, Shenyang 110168;
2.
College of Power Engineering, Nanjing University of Science and Technology, Nanjing 210094

摘要: 利用ANSYS/LS-DYNA非线性动力分析程序,对一种非对称结构飞机前风挡的鸟撞动态响应进行了三维数值模拟。计算得到非对称结构风挡内部单元的最大主应力、位移、应变等分布规律。与完整对称风挡相比,尽管撞击过程中非对称边缘处首先产生较高的应力值,接近0.8σmax,但持续时间短,并未造成材料破坏;这种非对称结构设计并不使鸟撞风挡临界速度产生明显的降低。另外,撞击点位置偏差对风挡鸟撞临界速度也有较大影响。
- 动态响应 /
- 鸟撞 /
- 风挡 /
- 非对称结构
Abstract: We employ the ANSYS/LS-DYNA nonlinear dynamic analysis software to simulate the dynamic response of the asymmetrical windshield subjected to bird impact and calculate the maximum principal stress,strain and displacement of its internal units,thus obtaining their distribution results.The principal stress at the fringe of the asymmetrical windshield subjected to bird impact is as high as nearly 0.8σmax but lasts only a short time and does not cause any damage to the asymmetrical windshield.This design of asymmetrical windshield does not reduce its critical velocity when it is under bird impact.Besides,the dispersion for the position of bird impact has some effect on the critical velocity of the asymmetrical windshield.
- dynamic response /
- bird impact /
- windshield /
- dissymmetry structure

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