摘要
离轨制动是确保天地往返飞行器安全、准确返回既定着陆场区的前提。文章借鉴载人飞船再入返回飞行的工程经验,对升力体再入飞行器的离轨制动总体方案进行分析,阐述了离轨制动任务剖面以及相关总体参数,依此确定离轨制动设计条件、设计约束。在此基础上,以典型升力体再入飞行器为例,仿真分析给出了升力体再入飞行器离轨制动时序设计和离轨制动策略方案,得到涵盖离轨制动策略、离轨制动时序的升力体再入飞行器的总体设计方案。最后,通过灵敏度分析确定了优化设计变量,开展了离轨制动多学科优化设计的关键技术研究。相关研究内容可为升力体再入飞行器离轨制动的具体工程实施提供技术参考。
The deorbit of the reentry vehicle is the premise of the safety and accuracy landing to the flight strip.In this paper,based on the flight engineering experience of the spacecraft,the deorbit study of general scheme design is investigated,including mission profile and reference general scheme parameters,which determines the design conditions and design restrictions.In the foundation of the deorbit study,the braking strategy and deorbit strategy for the general scheme design is proposed in numerical simulation analysis,taking the typical lifting reentry vehicle for example.The multidisciplinary design optimization of the deorbit design is also investigated as a key technology in this paper based on the definitely deorbit design by sensitivity analysis.The research results in this paper can provide a technical reference for the deorbit engineering design of the lifting reentry vehicles.
作者
左光
陈鑫
侯砚泽
吴文瑞
ZUO Guang;CHEN Xin;HOU Yanze;WU Wenr(Institute of Manned Space System Engineering,China Academy of Space Technology,Beijing 100094,China)
出处
《航天返回与遥感》
CSCD
2019年第1期1-10,共10页
Spacecraft Recovery & Remote Sensing
关键词
升力体
离轨制动
天地往返飞行器
航天返回
lifting reentry vehicle
deorbit
aerospace vehicle
spacecraft recovery
作者简介
左光,男,1971年生,1994年获天津大学学士学位,2001年获莫斯科航空学院硕士学位,硕士学位、研究员,中国航天科技集团学术技术带头人。研究方向为新型飞船返回舱气动设计、不同升阻比飞行器EDL技术。E-mail:lunar_cast@126.com。
