摘要
对探测器定点在共线平动点附近的轨道控制提出了一种小推力方案,针对日-地(月)系的具体背景给出了数值模拟结果,并对其进行了相应的分析.
This paper proposes a low-thrust strategy for orbit control of spacecraft around collinear libration points. Numerical simulation results are given by taking the Sun-Earth ＋ Moon System as an example together with an analysis.
出处
《飞行器测控学报》
2005年第6期29-33,共5页
Journal of Spacecraft TT&C Technology
关键词
共线平动点
轨道控制
线性反馈
小推力控制
Collinear Libration Point
Orbit Control
Linear Feedback
Low-Thrust Control
