基于冲量变轨原理的地球同步卫星有限推力变轨策略

空间控制技术与应用

基于冲量变轨原理的地球同步卫星有限推力变轨策略

彭坤, 徐世杰

北京航空航天大学宇航学院, 北京 100083

收稿日期:1900-01-01 修回日期:1900-01-01 出版日期:2008-12-26 发布日期:2008-12-26

Finite Thrust Maneuver Strategy for the Geostationary Satellite Based on Impulse Orbit Transfer

Peng Kun, Xu Shijie

School of Astronautics, BeiHang University, Beijing, 100083

Received:1900-01-01 Revised:1900-01-01 Online:2008-12-26 Published:2008-12-26

摘要/Abstract

摘要： 推力有限时，地球同步轨道卫星在远地点变轨的弧段很长，会导致较多的燃料消耗。基于冲量变轨原理，研究了地球同步轨道卫星远地点有限推力多次变轨问题，提出了具有星下点约束的最省燃料变轨方案，给出了每次变轨的推力方向和点火起止时刻及最优中间过渡轨道。仿真结果验证了该方案的有效性。

关键词: 冲量变轨, 地球同步卫星, 有限推力, 远地点变轨

Abstract: In the case of finite thrust apogee maneuver for the geostationary satellite, the fuel consumption increases due to the long burn arc. Based on the impulse orbit transfer principle, the finite thrust multi-impulse apogee maneuver for the geostationary satellite is studied in this paper. The minimum fuel multi-impulse apogee maneuver strategy with the constraint of subsatellite point is obtained. The thrust direction and firing time of each maneuver and the optimal intermediate transition orbits are given. Simulation results validate the effectiveness of the proposed method.

Key words: impulse orbit transfer, geostationary satellite, finite thrust, apogee maneuver

中图分类号:

v448

彭坤, 徐世杰.

基于冲量变轨原理的地球同步卫星有限推力变轨策略

[J]. 空间控制技术与应用, 2008, 34(6): 48-51.

Peng Kun, Xu Shijie. Finite Thrust Maneuver Strategy for the Geostationary Satellite Based on Impulse Orbit Transfer[J]. , 2008, 34(6): 48-51.