摘要
对利用小推力发动机将月球探测器从双曲线轨道转移到圆轨道的燃料最省转移问题 ,进行了研究 .首先 ,将问题分解为从双曲线到椭圆的转移和从椭圆到目标圆轨道的转移两步 .然后 ,分别利用遗传算法解决了冲量假设下的最优转移、小推力加速情况下从双曲线到椭圆的转移轨道优化 ,以及转移时间有约束情况下的从椭圆到目标圆轨道的转移轨道优化问题 .
The minimum fuel consumption problem of low thrust orbit maneuver from a hyperbolic orbit to a circular orbit is studied. At first, the problem is divided into two parts: orbit maneuver from a hyperbolic orbit to an elliptic orbit and orbit maneuver from an elliptic orbit to a circular orbit. Then, a genetic algorithm is used to solve the optimization problem in the cases of impulse assumption, low thrust orbit maneuver from a hyperbolic orbit to an elliptic orbit, and low thrust orbit maneuver from an elliptic orbit to a circular orbit with transfer time constraint.
出处
《天文学报》
CSCD
北大核心
2000年第3期289-299,共11页
Acta Astronomica Sinica
基金
863资助项目! 协议号 863 2 5 3 .3
