研究了一种应用非线性规化求解有限推力作用下异面最优轨道转移问题的方法。
A method of applying nonlinear program to solve nonplanar optimal orbital transfer under finite thrust is studied.
针对圆(近圆)轨道航天器相对运动的固定时间状态转移问题，提出了一种基于导航点的多脉冲优化轨迹生成策略。
An optimal trajectory generation strategy based on way-points is presented to solve the fixed-time state transition for spacecraft relative motion in a circular orbit.
针对星际探测任务中燃料最省小推力转移轨道问题，提出一种基于标称轨道的快速设计方法。
A novel rapid method to design optimal-fuel interplanetary trajectory for low-thrust propulsion is presented based on normal trajectory approach.
本文研究了在共面圆轨道HEO-LEO的过程中，气动辅助轨道转移飞行器（AOTV）在大气内飞行的极小时间控制问题。
This paper considers the minimum-time control of aeroassisted orbital transfer vehicle (AOTV) which arises in the study of coplanar HEO-LEO orbital transfer.
研究了伪光谱方法在空间飞行器有限推力轨道转移最优化问题中的应用。
The problem of rapid Lunar soft-landing trajectory optimization by using a Legendre pseudospectral method was studied in this paper.
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.
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。
An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
对于轨道拦截问题，给出了一种基于速度增益制导和状态转移矩阵的精确初制导方法。
In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed.
对于轨道拦截问题，给出了一种基于速度增益制导和状态转移矩阵的精确初制导方法。
In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed.
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