GEO卫星电推进与化学推进组合变轨方案研究  

Orbit Transfer Concept for GEO Satellite by Combination of Electric and Chemical Propulsion

作　　者：田百义 黄美丽[1] 冯昊[1] 赵峭[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2015年第3期28-33,共6页Spacecraft Engineering

摘　　要：针对GEO卫星采用电推进和化学推进系统进行变轨的问题,在给定轨道控制模型的基础上,给出实现轨道半长轴、偏心率和倾角3个参数单独调整和联合控制的控制律。结合假设的运载火箭发射能力约束,给出航天器不同入轨高度对应的初始质量。以此为约束,给出化学推进和电推进不同组合的6种GTO向GEO转移方案,并对比分析各方案完成变轨所需的时间、推进剂、速度增量以及完成变轨后的质量剩余情况,研究方法可为电推进系统在航天领域的应用提供参考。Based on the orbit control model, orbit transfer strategies for GEO satellites that using electric and chemical propulsion from GTO to GEO are analyzed in this paper. Firstly, the orbit laws for separated and combined control of changing semi-major axis, eccentricity, and inclination are investigated. Secondly, the satellite initial masses corresponding to altitude of injection are given according to the launcher restrictions, and six orbit transfer schemes for GTO to GEO are studied. At the end of this paper, the time of flight, propellant and velocity increment required for each scheme are presented. The research in this article is helpful to providing advice for the application of electric propulsion in space exploration.

关 键 词：电推进 化学推进 地球静止轨道 轨道转移 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]