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.
作者
陈记争
孙松涛
冯刚
肖余之
CHEN Jizheng;SUN Songtao;FENG Gang;XIAO Yuzhi(Aerospace System Engineering Shanghai,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)
出处
《中国空间科学技术》
EI
CSCD
北大核心
2019年第6期47-54,共8页
Chinese Space Science and Technology
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
fast launching and positioning
orbit optimizing
equinoctial orbital element
explicit guidance
positioning control
flight dynamics and control
