Spacecraft reentry trajectory optimization is a kind of optimal control problem.
飞行器再入轨迹优化是一类最优控制问题。
The optimal design of the trajectory for the standard twice reentry of mooncraft under the conditions of the trajectory endpoint set and multiply objective constraints in this paper.
对登月飞船在指定轨道终点及多约束条件下两次再入轨道的优化设计进行了研究。
The physical causation of the optimal trajectory and the corresponding angleofattack profile are presented. It is a good reference for schematic trajectory design for gliding type reentry vehicles.
分析了沿最优轨迹飞行的物理原因和基本迎角控制规律，可为滑翔式再入飞行器的最优轨迹方案设计提供依据。
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