The invention discloses a method and device for controlling constellation satellite deorbit, electronic equipment, a medium and a product. The method comprises the steps that current orbit parameters and target orbit parameters of a constellation satellite are obtained, the current orbit parameters comprise the current semi-major axis and the current eccentricity rate of a current orbit, and the target orbit parameters comprise the target semi-major axis and the target eccentricity rate of a target orbit; based on the current orbit parameter, the target orbit parameter, the semi-major axis weight and the eccentricity ratio weight, constructing a target function about the deorbit direction of the constellation satellite; the semi-major axis weight and/or eccentricity weight in the target function are/is adjusted at a plurality of discrete nodes where the constellation satellites deorbit, the target deorbit direction of the constellation satellites at each discrete node is obtained, and the target deorbit direction is a track enabling the deorbit duration of the constellation satellites to be shortest; and controlling the constellation satellite to deorbit along the target deorbit direction. According to the scheme provided by the invention, the complexity of calculating the satellite deorbit trajectory can be reduced, so that the deorbit efficiency of the satellite is improved.
本申请公开了一种控制星座卫星离轨的方法、装置、电子设备、介质及产品。该方法包括:获取星座卫星的当前轨道参数及目标轨道参数,当前轨道参数包括当前轨道的当前半长轴及当前偏心率,目标轨道参数包括目标轨道的目标半长轴及目标偏心率;基于当前轨道参数以及目标轨道参数,及半长轴权重和偏心率权重,构建关于星座卫星的离轨方向的目标函数;在星座卫星离轨的多个离散节点处,调整目标函数中的半长轴权重和/或偏心率权重,得到星座卫星在每个离散节点处的目标离轨方向,目标离轨方向为使星座卫星的离轨时长最短的轨迹;沿目标离轨方向控制星座卫星离轨。本申请所提供的方案能够降低计算卫星离轨轨迹的复杂度,进而提升卫星的离轨效率。
Method and device for controlling constellation satellite deorbit, electronic equipment, medium and product
控制星座卫星离轨的方法、装置、电子设备、介质及产品
2024-05-03
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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