基于SPH法的飞机风挡鸟撞失效破坏研究

运用SPH方法模拟了鸟撞飞机风挡的过程,鸟体模型采用SPH法建立,风挡模型采用Lagrange法定义,鸟体以515km/h、562km/h和600km/h的速度分别撞击风挡对称线上前1/3点。通过仿真模拟,获取了鸟体撞击风挡的应变、位移、应力曲线,风挡失效损伤演化过程,并与试验结果对比,证明所建鸟撞风挡有限元模型可以准确预测风挡的鸟撞动态响应。研究表明：鸟体撞击风挡对称线前1/3点时,风挡最大变形发生在风挡中间部位；风挡在弯曲作用下首先会在内表面发生失效破坏；撞速为600km/h的风挡发生失效破坏后,在撞击区域形成多条与风挡对称线呈大约50°夹角的裂纹及少部分横向裂纹。

Failure analysis of aircraft windshield under bird impact based on SPH

There are some simulation of aircraft windshield under bird impact by using the smoothed particle hydrodynamics (SPH) method, modelling the bird by SPH method, modelling the windshield by lagrange method, the bird strikes the front 1/3 point of the windshield symmetrical line at a speed of 515km/h, 562km/h and 600km/h. The history curves of strain, displacement, stress and the failure process of windshield under bird impact, which are obtained through numerical simulation. And compared with the experimental results, it is proved that the finite element model can accurately predict the bird impact dynamic response of the windshield. The study indicate that the maximum deformation of the windshield occurs in the middle of the windshield when the bird hits the front 1/3 point of the windshield symmetrical line. The windshield will break down first on the inner surface under bending. When the windshield at the speed of 600km/h is damaged, a number of cracks with an angle of about 50 degrees from the symmetrical line of the windshield and a small amount of transverse cracks are formed in the impact zone.