连续小推力条件下星座轨道机动方法研究

基于连续小推力条件下星座轨道机动的动力学特性分析，研究了其入轨的布局置入和离轨机动方法。地球轨道上的大型星座数量巨大，传统的轨迹优化方法较难应用。针对多星入轨的星座布局置入任务，求解了分时序抬轨的相位调整问题，并在轨道抬升过程中，利用轨道倾角偏置补偿升交点赤经漂移。针对星座中卫星的离轨任务，设计了半长轴和偏心率的联合调整方法。在保证卫星快速离轨的同时，能够有效减少燃料的消耗。考虑到连续小推力机动的弧段效应，控制策略需要围绕控制效应的曲线积分进行优化。

Study on maneuver methods of satellites constellation with continual small-thrust propulsion

Based on the orbit dynamic characteristics, orbit maneuver methods of satellites constellation with continual small-thrust propulsion are studied in this paper. Because of the huge scales of constellations, orbit maneuver of constellation in near-earth orbit can hardly be managed by traditional method as trajectory planning. Orbit insertion for constellation configuration is considered as a relative semi major axis control problem in time delay maneuver sequence. Meanwhile, offset control of inclination is considered for drift of right ascension of ascending node(RAAN) during arising orbit maneuver. For consideration of orbit discarded problem, a united control for combination of semi major axis and eccentricity is designed for a rapid orbit decay with energy-saving. Because of the curve effect for continual small thrust propulsion, curvilinear integral of orbit control should be investigated for all the strategy optimizations.