引用本文:
【打印本页】   【HTML】   【下载PDF全文】   查看/发表评论  【EndNote】   【RefMan】   【BibTex】
←前一篇|后一篇→ 过刊浏览    高级检索
本文已被:浏览 1494次   下载 998 本文二维码信息
码上扫一扫!
分享到: 微信 更多
有限推力变轨的月球探测器发射轨道设计
陈新民1, 周天帅2, 朱冬阁2, 王建明2
1.中国运载火箭技术研究院, 北京 100076;2.北京宇航系统工程研究所, 北京 100076
摘要:
月球探测器的发射是一个多体问题,也是严格的轨道交会问题。发射轨道方案从理论上有很多种形式,但在工程应用中,受到火箭能力、发射场和测控条件等多种因素制约,方案选择限制非常严格。利用现有火箭,采用有限推力从停泊轨道转移发射是最常用的一种发射方式。本文以某典型火箭为例,对采用有限推力变轨方案的奔月轨道设计流程、发射方案、轨道设计方法、精度分析、发射窗口设计进行了详细分析和研究。
关键词:  有限推力;月球探测;发射轨道设计
DOI:10.15982/j.issn.2095-7777.2016.03.009
分类号:
基金项目:
Launch Trajectory Design for Lunar Probes with Finite Thrust Maneuver
CHEN Xinmin1, ZHOU Tianshuai2, ZHU Dongge2, WANG Jianming2
1.China Academy of Launch Vehicle Technology, Beijing 100076, China;2.Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
Abstract:
To launch a lunar probe is a multi-celestial body problem, and also a strict orbit rendezvous problem. Many launch trajectory plans can be obtained theoretically, but selctions are strictly limited for enginnering applications with many constarints, such as launch capacity, launch site, telemetry and control conditions etc. The most conventional method is to transfer from the parking orbit with finite thrust. This paper takes a typical launch vehicle as an example, the Earth-lunar transfer scheme with constraints are analyzed and studied.
Key words:  finite thrust;lunar exploration;launch trajectory design