蜂窝夹芯板超高速碰撞仿真

蜂窝夹芯板是一种多用于航天器的特殊结构,采用光滑粒子流体动力学算法(SP H)对蜂窝夹芯板进行超高速碰撞研究时主要存在2个问题:蜂窝芯的几何建模过程复杂;蜂 窝芯层非常薄,为保证仿真精度采用相等的粒子间距必然生成超过计算容忍的粒子数量.结 合参数化程序设计语言(APDL)、用户界面设计语言(UIDL)进行结构建模,编制了APDL生成蜂 窝芯的程序,采用UIDL将该程序集成到ANSYS交互式界面中,能够方便快捷的生成任意尺度 的正六边形蜂窝芯.针对此方法得到的模型,采用SPH单元与壳单元相结合的方法,其中蜂 窝芯采用壳单元,入射体、蜂窝夹芯板的前、后面板采用SPH单元,对蜂窝夹芯板进行了超 高速碰撞仿真研究.仿真结果与相关试验进行了对比,仿真得到的后板破口尺寸与试验比较 接近,证实了该方法适用于蜂窝夹芯板的超高速仿真. 

Simulation of hypervelocity impact to honeycomb sandwich

Honeycomb sandwich is a special configuration which often used in spacecraft.The method of smoothing particle hydrodynamics(SPH) in the hypervelocity impact simulation to the honeycomb presents two questions: it is problematic to model the honeycomb,the distance between the neighboring particles should be equal, however,the honeycomb is so thin that the particles would be created too much to compute.The ANSYS parametric design language(APDL) and the ANSYS user interface design language(UIDL) were integrated to create the honeycomb core.The program was written in APDL,and the APDL program was integrated in the ANSYS user interface with the UIDL.Arbitrary hexagon honeycomb core can be created in this method expediently.The honeycomb core was simulated with shell element while the front facesheet and the rear facesheet was simulated with SPH element in the simulation.The hole size by the simulation was compared with the experiment which shows almost equal in size.It is confirmed that the method is suited to the simulation of hypervelocity impact to honeycomb sandwich.