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在地–月L2点月球中继卫星轨道转移设计中,采用高比冲、小推力的电推进器可以大大增加卫星的有效载荷比,但会增加轨道设计的难度。基于地球GEO轨道为初始轨道,地–月L2点的halo轨道为目标轨道,通过最优控制中的混合法及平动点轨道的不变流形,研究了作为拓展任务的利用地月系统不变流形的小推力变轨方案,可以有效简化转移的轨道设计。仿真结果表明:得到了任意推力情况下最节省推进剂燃料的推力方向控制方案,对月球中继卫星的轨道设计及其平动点轨道设计具有工程意义。
In the ground-lunar L2 satellite orbit transfer design, using high specific impulse and small thrust electric thruster can greatly increase the satellite payload ratio, but it will increase the difficulty of orbit design. Based on the Earth orbit GEO orbit and the halo track at the Earth-Moon L2 point as the target orbit, the ground-moon system as the extension task is studied by the hybrid method in the optimal control and the invariant manifold of the orbiting point orbit Variable-thrust small-thrust orbit planning, can effectively simplify the transfer of track design. The simulation results show that the thrust control scheme of the most fuel-efficient propellant under any thrust condition is obtained, which is of engineering significance for the orbit design of the lunar relay satellite and the design of its translational-point orbit.