回归大椭圆轨道卫星轨迹保持策略与仿真  

Strategy and Simulation of Recursive HEO Orbit Maintenance

作　　者：杨悦[1] 吴功友[2] 白沁园[3] 杨永安[2] 

机构地区：[1]四川大学软件学院,成都610064 [2]西安卫星测控中心宇航动力学国家重点实验室,西安710043 [3]上海卫星工程研究所,上海200000

出　　处：《科学技术与工程》2013年第26期7711-7715,共5页Science Technology and Engineering

基　　金：国家自然科学基金项目(11273072)资助

摘　　要：为了实现大椭圆轨道卫星星下点在一定经度范围内回归,保持对特定区域的长时间观测,对优化轨迹保持策略进行了深入研究。首先提出了必须根据共振大椭圆卫星的轨道演变规律进行轨迹保持。同时分析了大椭圆轨道卫星满足回归条件的轨道约束;其次分析了主要动力学模型的摄动规律,建立了轨道摄动对升交点赤经、半长轴以及轨迹漂移影响的计算模型;最后结合工程应用实际,给出了具体的回归大椭圆轨道的轨迹保持周期和保持策略。通过仿真实验及结果分析,表明了该策略的正确性和有效性,为回归大椭圆轨道卫星的轨道设计和测控实施提供技术参考。To keep sub-point of High Eccentric Orbit （HEO） recursive within a certain range of longitude, as well as to perform long time observation to the particular region, the orbit maintenance strategy was studied. Firstly, it was necessary to maintain orbit according to the orbital evolution law of resonant HEO. Meanwhile, the HEO orbit constraints which could meet the recursive condition were analyzed. Secondly, the perturbation law of the main dynamical model was introduced. And the calculation model of the perturbation and its influence on fight ascension of ascending node, semi-major axis and orbital drift was founded. Last, the orbit maintenance strategy of HEO orbit and its period were concluded. Through the simulation experiments, this strategy was proved to be feasible and valid, which could provide technical reference for orbit design and control of HEO orbit satellites.

关 键 词：卫星 回归大椭圆轨道 轨迹保持 轨道演变 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]