带配平翼月球返回舱跳跃再入轨迹优化设计

Skip-Entry Trajectory Optimization Design for Lunar Return Vehicle with Trim-Flaps

为解决小升阻比月球返回舱再入大气层时安全性低、机动能力差的问题,提出采用一种带配平翼的中等升阻比返回舱做为月球采样返回舱,并对动压约束下轨迹优化问题进行了分析。首先介绍了一阶状态变量约束最优控制问题。然后采用庞德里亚金极大值原理以总吸热量最小为优化目标,对动压约束下再入轨道的初始再入段进行了优化设计,给出了升力系数的最优表达式。仿真研究表明,该方法能有效地降低返回舱再入过程中的动压。

A medium lift-to-drag ratio lunar sample return vehicle with trim-flaps is proposed to cope with problems of low safety and poor maneuverability when the vehicle lift-to-drag ratio is low.The trajectory optimization design for skip reentry lunar return vehicle is analyzed under dynamic pressure constraint.Firstly the optimization problem with a first-order state constraint is introduced.Secondly the trajectory is optimized by applying the Pontryagin maximum principle under the performance of minimum heat,and the optimal expression of lift coefficient is derived.The simulation studies show that this method can decrease the dynamic pressure effectively.