The invention discloses a low-orbit satellite orbit recovery method with low fuel consumption, and belongs to the technical field of satellite orbit recovery. The invention aims to solve the problem that an existing orbit maneuvering method needs frequent orbit adjustment and is not beneficial to low-fuel-consumption in-orbit long-term operation of a satellite. Comprising the following steps: establishing an orbit kinetic equation considering earth oblateness perturbation; solving the initial number of transition orbits with low fuel consumption according to the current orbit and the target orbit of the satellite by using a semi-analytical method; calculating drifting time required by the satellite for drifting without fuel consumption on the transition orbit by utilizing the earth oblateness perturbation and the final number of the transition orbit at the transition end moment by combining the orbit kinetic equation; based on the Pontryagin maximum principle, thruster fuel optimal control rate sequences of the satellite from the current orbit to the transition orbit and from the transition orbit to the target orbit are calculated, and a thruster is controlled to achieve satellite orbit recovery. The method is used for satellite orbit recovery.
一种低燃料消耗的低轨卫星轨道恢复方法,属于卫星轨道恢复技术领域。本发明针对现有轨道机动方法需要频繁进行轨道调整,不利于卫星的低燃料消耗在轨长期运行的问题。包括:建立考虑地球扁率摄动的轨道动力学方程;利用半解析法根据卫星的当前轨道和目标轨道求解低燃料消耗的过渡轨道初始轨道根数;同时结合所述轨道动力学方程,计算卫星在过渡轨道上利用地球扁率摄动进行无燃料消耗漂移所需的漂移时间及过渡结束时刻的过渡轨道最终轨道根数;再基于庞特里亚金极大值原理,计算卫星由当前轨道到过渡轨道以及卫星由过渡轨道到目标轨道的推力器燃料最优控制率序列,并控制推力器实现卫星的轨道恢复。本发明用于卫星轨道恢复。
Low-orbit satellite orbit recovery method with low fuel consumption
低燃料消耗的低轨卫星轨道恢复方法
2024-05-14
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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