The invention relates to a low-orbit giant constellation networking orbit control strategy method. The method comprises the following steps: S1, calibrating and forecasting constellation key parameters according to a previous group of orbit control ignition time sequence, GNSS telemetering and ground measurement orbit data; s2, according to the calibration result calculated in the step S1 and nominal constellation configuration parameters, constellation networking stage autonomous judgment is carried out, and an orbit control strategy is generated; and S3, according to the orbit control strategy generated in the step S2, calculating the post-control constellation configuration evolution condition in a period of time in the future, and verifying the control strategy. The method has the advantages that the method is suitable for configuring electric propulsion low-orbit giant constellation networking tasks, and the orbit control task requirements of existing giant constellations are met.
本发明涉及一种低轨巨型星座组网轨道控制策略方法,包括以下步骤:S1:根据上一组轨控点火时序、GNSS遥测及地面测定轨数据进行星座关键参数标定及预报;S2:依据步骤S1中计算的标定结果及标称星座构型参数进行星座组网阶段自主判断,并生成轨控策略;S3:依据步骤S2中生成轨控策略计算未来一段时间的控后星座构型演化情况,验证控制策略。优点在于:适用于配置电推进的低轨巨型星座组网任务,满足现有巨型星座轨控任务需求。
Low-orbit giant constellation networking orbit control strategy method
一种低轨巨型星座组网轨道控制策略方法
2024-06-04
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
European Patent Office | 2022
|European Patent Office | 2023
|European Patent Office | 2023
|