基于光滑粒子流体动力学法的飞机风挡鸟撞失效破坏模拟  

Failure Simulation of Aircraft Windshield under Bird Impact Based on Smoothed Particle Hydrodynamics

作　　者：陈贺贺[1] 原梅妮[1] 李立州[1] 史明东 何小晶 CHEN He-he;YUAN Mei-ni;LI Li-zhou;SHI Ming-dong;HE Xiao-jing(College of Mechanical and Electrical Engineering,North University of China,Taiyuan 030051,China)

机构地区：[1]中北大学机电工程学院,太原030051

出　　处：《科学技术与工程》2018年第7期62-67,共6页Science Technology and Engineering

基　　金：国家自然科学基金(51201155);山西省自然科学基金(2012011019-1);教育部新教师基金(20101420120006)资助

摘　　要：运用光滑粒子流体动力学(Smoothed Particle Hydrodynamics,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515 km/h、562 km/h和600 km/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600 km/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。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 515 km/h,562 km/h and 600 km/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 600 km/h is damaged,a number of cracks with an angle of about 50°from the symmetrical line of the windshield and a small amount of transverse cracks are formed in the impact zone.

关 键 词：光滑粒子流体动力学(SPH) 飞机风挡 鸟撞 数值模拟 失效破坏 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]