GEO卫星快速发射入轨定点控制方法  

Control method of fast launching and positioning for geostationary satellites

作　　者：陈记争 孙松涛 冯刚 肖余之[2] CHEN Jizheng;SUN Songtao;FENG Gang;XIAO Yuzhi(Aerospace System Engineering Shanghai,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)

机构地区：[1]上海宇航系统工程研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《中国空间科学技术》2019年第6期47-54,共8页Chinese Space Science and Technology

摘　　要：提出了一种GEO卫星快速发射入轨定点方法,运载火箭将卫星发射进入GTO轨道后,由上面级或卫星自身在48h内快速定点到GEO轨道任意指定定点位置。考虑时间、测控等约束,在选定变轨策略基础上,以燃料消耗最小为目标,优化给出了快速入轨定点标称轨迹。采用无奇异的春分点根数描述轨道运动,基于最小二乘法给出了航天器在有限推力条件下变轨的闭环显式制导方法,控制航天器沿标称轨迹飞行。仿真算例表明,采用该变轨策略、轨道优化设计方法和制导律,可以完成GEO卫星快速入轨定点控制。A method of fast launching and positioning for GEO satellites is proposed. After the satellite is launched into the GTO orbit, it is maneuvered into any designated position in the GEO orbit by the upper stage or by itself within 48 hours. Considering the constraints of time and Tele-Tracking & Controlling, the nominal trajectory of fast positioning is optimized for minimizing fuel consumption. Based on the nonsingular Equinoctial orbital elements, an explicit guidance is proposed for spacecraft maneuvering and positioning with finite thrust. The simulation shows that the fast launching and positioning control of GEO satellite can be achieved by using the proposed maneuvering strategy, trajectory optimization method and guidance law.

关 键 词：快速发射定点 轨道优化 春分点根数 显式制导 定点控制 飞行动力学与控制 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]