微纳卫星L1点Halo轨道转移轨道设计

针对地月空间探测任务的高风险、高成本,提出了利用微纳卫星完成地月空间环境监测、未知空间探索及地月空间动力学验证的方案,从而为未来建立地月空间运输系统建立良好基础。借助地月空间三体动力学和小推力轨道设计中的直接法,设计了针对微纳卫星的低能耗地月转移方案。结果表明:微纳卫星借助火箭上面级,从GEO轨道出发飞向L1点Halo轨道,所需速度增量为1.033 km/s,转移时间为40.02 d;不借助火箭上面级,所需速度增量为1.397 5 km/s,转移时间为48.7 d。

Transfer Orbit Design for L1 Halo Orbit Based Nanosats

Nanosats have been demonstrated the capability of deep space exploration with the availability of onboard control systems, such as propulsion, active attitude control, navigation as well as communication, thermal or other subsystems design required for deep space. Nanosats are usually launched as second ary payloads into different orbits. In this paper, aiming at lunar exploration with nanosats, the concepts that nanosats transfer to the moon from the deployments in geosynchronous transfer orbit(GTO) or released by the upper stage were put forward and the heteroclinic connection between L1 and L2 Lyapunov orbit was designed. In the orbit design, both the dynamical system approach and the low thrust model were used to realize low energy cost orbit transfer in order to satisfy the limited condition of propulsion subsystems.