火星探测器分离试验方法研究  

Method of separation test for Mars spacecraft

作　　者：董悫 郑圣余[1] 冯伟[1] 王临政 王辰星 陈启威[1] 王振 DONG Que;ZHENG Shengyu;FENG Wei;WANG Linzheng;WANG Chenxing;CHEN Qiwei;WANG Zhen(Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《航天器环境工程》2020年第4期361-368,共8页Spacecraft Environment Engineering

基　　金：国家重大科技专项工程。

摘　　要：火星探测器分离试验是火星探测器在总装测试阶段的重要试验项目之一,需要设计专门的试验系统模拟分离时的低重力环境。文章针对着陆器与环绕器分离工况中的瞬时失重问题和着陆器背罩分离工况中的非平衡系统缓冲吸能问题,提出基于拉伸弹簧组件和配重分离的解决方案,并使用模拟件进行试验,验证了所提出方法的有效性。The separation test is one of the important tests in the assembly and test phase of the Mars spacecraft,in which a special simulation system providing the low gravity environment is necessary.This paper proposes solutions based on the separation of the extension spring and the balance weight separation,to tackle the problem of instantaneous weightlessness in the separation between the lander and the orbiter,and the buffer energy absorption problem of the non-equilibrium system under the back cover separation condition.The effectiveness of the proposed method is verified by the experimental data for a dummy sample.

关 键 词：火星探测器 分离试验 低重力 拉伸弹簧 配重分离 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程] TB122[理学—工程力学]