Geometric optimal control of elliptic Keplerian orbits
Geometric optimal control of elliptic Keplerian orbits
复制标题
DOI：
10.3934/dcdsb.2005.5.929
复制
发表时间：
2005-08
影响因子：
1.2
通讯作者：
B. Bonnard;Jean-Baptiste Caillau;E. Trélat
中科院分区：
文献类型：
--
作者：
B. Bonnard;Jean-Baptiste Caillau;E. Trélat
本文讨论卫星在开普勒轨道之间的转移。研究了系统的可控性特性，并利用极大值原理对时间最优控制进行了初步分析。还给出了二阶充分条件。最后，数值计算得出系统从初始大偏心率低轨道转移到终端地球静止轨道的时间最优轨迹。
This article deals with the transfer of a satellite between Keplerian orbits. We study the controllability properties of the system and make a preliminary analysis of the time optimal control using the maximum principle. Second order sufficient conditions are also given. Finally, the time optimal trajectory to transfer the system from an initial low orbit with large eccentricity to a terminal geostationary orbit is obtained numerically.