摘要
采用计算流体动力学(CFD)数值仿真和飞行动力学耦合的方法,对月球取样返回器伞舱盖弹射分离过程的安全性进行了仿真研究。同时利用月球取样返回器回收系统工作过程的动力学仿真系统,对舱盖伞—伞舱盖与降落伞—返回器组合体下降过程中的安全性进行了分析。研究结果表明:月球取样返回器回收系统伞舱盖的弹射分离速度的设计是合理可行的,伞舱盖的分离是安全的;伞舱盖分离后,舱盖伞—伞舱盖组合体和降落伞—返回器组合体之间不存在碰撞的可能性,下降过程也是安全的。本文工作为月球取样返回回收系统的工程设计提供了理论依据。
Adopting the CFD numerical simulation and flight dynamics coupled method, the safety of the parachute container cover ejection separation process is studied in the paper. At the same time, the dynamics simulation system of the working process for the sample return recovery system, is used to analyze the safety of the combined parachute container cover-parachute and parachute-return capsule in the descent process. The results show that the ejection separation velocity design is reasonable and the separation process of the parachute container cover is safe. After parachute container cover separation, the parachute container cover recovery system and the return capsule recovery system do not have the possibility of collision, the descent process is safe. It is provided a theory basis for recovery system engineering design of the lunar sample return.
出处
《宇航学报》
EI
CSCD
北大核心
2014年第5期499-505,共7页
Journal of Astronautics
关键词
月球取样返回
回收系统
弹射分离
安全性
Lunar sample return
Recovery system
Ejection separation
Safety
作者简介
高树义（1973-），男，博士生，主要从事航天器回收技术总体设计。通信地址：北京5142信箱299分箱（100094）电话：（010）68113668 E-mail：gaosy197313@sina．com
