绕月微卫星精确撞月轨道设计

Design of Precise Lunar Impact Trajectory for Circumlunar Microsatellite

为实现约束条件下的精准可控撞月,提出了基于Lambert问题的精确撞月轨道设计方法。通过求解Lambert问题,可得到撞月轨道轨控时刻的速度脉冲初值解,然后通过打靶法迭代得到撞月轨道的精确解。以“龙江二号”微卫星轨道为例,对撞月点经纬度的覆盖性,以及燃料约束下同一撞月点可行的轨控弧段进行全面分析。最后,通过月球南极水冰探测的撞月轨道设计案例,以验证本文提出的轨道设计方法的有效性。

To achieve precise and controllable lunar impact under constrained conditions,this paper proposes a precise lunar impact trajectory design method based on the Lambert problem.By solving the Lambert problem,the initial value of the velocity pulse is obtained,and then the accurate solution of lunar impact trajectory is gained by iterative shooting method.Taking the“Longjiang-2”microsatellite trajectory as an example,the coverage of the latitude and longitude of the impact point as well as the feasible trajectory arc of the same impact point under fuel constraints are comprehensively analyzed.Finally,the validity of the trajectory design method is verified through a lunar impact trajectory design case for lunar south pole water ice detection.