月球着陆器着陆缓冲性能研究  

Research on Landing Impact Attenuation Performance of Lunar Lander

作　　者：曾福明[1] 杨建中[1] 朱汪[1] 陈天智[1] 满剑锋[1] 徐青华[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2010年第5期43-49,共7页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：首先基于MSC.Nastran/MSC.Adams软件建立了模拟月球着陆器的动力学模型,并利用模拟月球着陆器在地面冲击试验来验证仿真模型的正确性,重点关注缓冲机构与结构连接处的载荷,结构特征点的加速度响应,以及缓冲器的工作行程。然后利用模拟着陆器地面试验结果修正动力学分析模型,研究表明:着陆器结构和缓冲机构的柔性对缓冲性能具有较大的影响。最后,把动力学分析模型中的模拟结构更换成真实结构,进行着陆器在月球表面的着陆冲击仿真分析,从而获得模拟着陆器地面试验与着陆器在月面着陆的冲击缓冲性能差异。Lunar lander dynamic simulation model is built based on the MSC. Nastran/MSC. Adams softwares,and the simulation model is validated by single-landing-gear-assembly drop test and vehicle structural drop test data in the earth gravity environment. This research focuses on the load at connector between structure and landing gear,acceleration response of structure and buffer working strokes.The results show that the flexibility of lander structure and landing gear have a rather considerable influence on landing performance. Finally,the simulated lander structure in the lander landing dynamic model is substituted by areal lander structure,to perform landing analysis on lunar surface,then lander landing performance difference is achieved by comparing simulated lander ground test with lander soft-landing on lunar surface.

关 键 词：月球着陆器 缓冲机构 模拟结构 ADAMS软件 冲击载荷 

分 类 号：V476.3[航空宇航科学与技术—飞行器设计]