An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
针对近距离相对运动的轨道控制问题，提出用常值小推力完成最优转移的方法。
Electrodynamic tethers with low thrust-to-weight ratios can only perform orbital transfers over a large number of revolutions, which poses a real challenge to short time scale optimal control methods.
电动力绳系卫星的推力幅值较小且方向固定，完成轨道机动任务的周期长，其最优控制问题的求解比较困难。
Then the paper applies EA and SPEA to an orbital transformation problem. - time-energy optimization o The paper also solve low thrust control problem of relative motion using fuzzy logic.
然后分别用一般的进化算法和改进的SPEA方法解决轨道转移的时间-能量优化问题，对于相对运动方程有限推力控制问题，本文用模糊控制的方法加以解决。
Then the paper applies EA and SPEA to an orbital transformation problem. - time-energy optimization o The paper also solve low thrust control problem of relative motion using fuzzy logic.
然后分别用一般的进化算法和改进的SPEA方法解决轨道转移的时间-能量优化问题，对于相对运动方程有限推力控制问题，本文用模糊控制的方法加以解决。
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