利用太阳帆定点探测器在地—月系共线平动点附近的探讨

On Orbit Control of Spacecrafts with Solar Sail around the Earth-Moon Collinear Libration Point

共线平动点附近的运动仅仅是条件稳定的,探测器的轨道需要经过控制才能维持在其附近。以地—月系L1点和L2点附近大振幅晕轨道的控制为例,探讨了太阳帆在定点这类探测器中的应用。首先,考虑了月球轨道的偏心率和太阳辐射的影响,给出了太阳帆对日定向的探测器轨道的低阶分析解,并在此基础上构造了在太阳系真实引力模型下一段时间内维持在共线平动点附近的拟周期轨道。然后,给出了两种利用太阳帆的控制方案,一是固定面质比而改变太阳帆法线的方向,另一是固定太阳帆对日定向而改变面质比,并对两种方案分别作了数值模拟。最后,文章探讨了测控误差及地、月影对轨道控制的影响。

Collinear libration points of the Earth-Moon system are unstal）le, so spaceerafts need orbit control to stay around them. Taking large amplitude halo orbits around L1 and L2 points of the Earth-Moon system as an example, orbit control with solar sail was studied. First, low-order analytical solution considering moon＇s eccentricity and solar radiation was given out, and quasi-periodic orbits in the real solar system based on this analytical solution were computed. Then, two control strategies with solar sail were proposed. One is to change the direction of the solar sail keeping the area fixed, and the other is opposite. Numerical simulations were made. At last, the effects of measurement and control error were studied, along with effects of earth＇s and moon＇s shadow.