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。
The optimization methods for launch trajectory of low earth orbit are discussed, and the optimal control problems are converted into parameter optimization problems by multiple parameterized methods.
确定了近地轨道的发射轨道优化设计方法 ，采用多重参数化法将轨迹最优控制问题转化为参数优化问题。
The optimization methods for launch trajectory of low earth orbit are discussed, and the optimal control problems are converted into parameter optimization problems by multiple parameterized methods.
确定了近地轨道的发射轨道优化设计方法 ，采用多重参数化法将轨迹最优控制问题转化为参数优化问题。
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