Transfer Trajectory Optimal Design for Earth-Moon L2 Based on Invariant Manifolds
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摘要:
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。
Abstract:During the optimal design of transfer trajectory to translunar libration point，the payload launch capacity of Lunar Relay Satellite can be improved greatly if the electric thrusters which have high specific impulse and low thrust can be used as main propulsion. The optimal design of low-thrust transfer trajectory is studied which makes use of the invariant manifolds of Earth-Moon system based on the hybrid method. GEO is the initial orbit and halo orbit around translunar libration point L2 is the aim orbit of the transfer trajectory. The simulation result shows that thruster direction control strategy which consumes the least propellant for transfer trajectory has been obtained. The result is of great important engineering meaning.
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