The invention discloses a track splicing method for transferring low thrust of an earth-moon three-body track to a moon-surrounding track, and belongs to the field of aerospace. The implementation method of the invention comprises the following steps: selecting splicing points suitable for an earth-moon circular restrictive three-body model and a lunar center two-body model according to a transition orbit by adopting the earth-moon circular restrictive three-body model and the lunar center two-body model; dividing a low-thrust orbit solving process into three solving stages, namely a three-body transfer stage, a two-body transfer stage and a matching stage according to the spatial positions of the splicing points, and solving a low-thrust transfer trajectory in a segmented manner by taking the shortest time as an optimization target for the three solving stages through a mixing method; and splicing the tracks of the three solving stages to obtain the shortest-time small-thrust track from the initial track to the target track. According to the method, accurate docking is realized in spatial position and speed, smooth transition of the spacecraft between different orbit sections can be ensured, the calculation error of the geocentric two-body dynamic model is reduced, and the safety and task success of the spacecraft are ensured.
本发明公开的从地月三体轨道小推力转移至环月轨道的轨迹拼接方法,属于航空航天领域。本发明实现方法为:采用地月圆型限制性三体模型和月心二体模型,根据过渡轨道选取适用于圆型限制性三体模型与二体模型的拼接点;依据拼接点空间位置将小推力轨道求解过程划分为三体转移段、二体转移段和匹配段三个求解阶段,并通过混合法对三个求解阶段以最短时间为优化目标,分段求解小推力转移轨迹,将三个求解阶段的轨迹拼接得到由初始轨道向目标轨道的最短时间小推力轨迹。本发明通过在空间位置和速度上实现精准对接,能够确保航天器在不同的轨道段之间平滑过渡,减少地心二体动力学模型的计算误差,进而确保航天器安全和任务成功。
Track splicing method for transferring small thrust from earth-moon three-body orbit to moon-surrounding orbit
从地月三体轨道小推力转移至环月轨道的轨迹拼接方法
2024-10-18
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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