连续小推力条件下星座轨道机动方法研究  

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

作　　者：杨盛庆 王禹 王丹娜 林荣峰 杜耀珂 钟超 YANG Shengqing;WANG Yu;WANG Danna;LIN Rongfeng;DU Yaoke;ZHONG Chao(Shanghai Institute of Spaceflight Control Technology,Shanghai 201109,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China)

机构地区：[1]上海航天控制技术研究所,上海201109 [2]上海市空间智能控制技术重点实验室,上海201109

出　　处：《中国空间科学技术》2020年第4期69-77,共9页Chinese Space Science and Technology

基　　金：上海市青年科技启明星计划(17QB1401400)。

摘　　要：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。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.

关 键 词：星座 连续小推力 轨道机动 轨道布局置入 离轨 弧段效应 曲线积分 

分 类 号：V474.1[航空宇航科学与技术—飞行器设计]