摘要
为寻找适合近地轨道上使用的航天器离轨技术,文章对目前各种离轨策略的基本原理及优缺点作了分析与对比,重点对电动力绳系离轨装置进行了深入研究,建立了数学模型,推导出离轨时间预估公式,对离轨的过程进行了数学仿真,结果证实电动力阻力能使近地轨道上航天器的轨道高度迅速降低,电动力绳系离轨策略具有很高的工程实用性。
This paper studies different methods of spacecraft de-orbiting in order to find a proper way for de-orbiting spacecrafts in the low earth orbit(LEO).Advantages and shortcomings of these de-orbiting methods were analyzed to show that the Electro-dynamic Tether de-orbiting system was the most economical and efficient.A mathematic model is proposed for Electro-dynamic Tether, and is used to estimate de-orbiting time.The simulation with MATLAB shows that a fast decay is effected by the electro-dynamic drag for LEO spacecrafts.
出处
《航天器环境工程》
2009年第4期378-382,404,共5页
Spacecraft Environment Engineering
基金
长江学者和创新团队发展计划资助项目(IRTO520)
关键词
离轨策略
电动力绳系
离轨时间
数值仿真
空间碎片
de-orbiting scheme
electro-dynamic tether
de-orbiting time
numerical simulation
space debris
