The invention discloses a satellite rapid maneuvering control method based on a parallel system, and the method comprises the steps: constructing a satellite rapid maneuvering parallel system, and correcting a thrust parameter of an artificial model through employing a particle swarm algorithm in combination with on-orbit spacecraft telemetry data obtained in real time, thereby building the artificial model which is consistent with an actual system in real time. And on the basis, the air injection time of maneuvering control is optimally estimated through an artificial model simulation calculation test, and the air injection time with the minimum error with the target position after maneuvering under the actual condition is obtained and fed back to an actual system. The method can realize long-term consistency of an artificial system and an actual system, predicts and controls the actual system, has high precision and robustness, and is suitable for rapid maneuvering control of satellites.

    本发明公开了一种基于平行系统的卫星快速机动控制方法,构建了一种卫星快速机动平行系统,结合实时获取的在轨航天器遥测数据,采用粒子群算法修正人工模型的推力参数,以此建立与实际系统实时保持一致的人工模型,并在此基础上通过人工模型仿真计算试验对机动控制的喷气时间进行最优估计,获得实际情况下机动后与目标位置误差最小的喷气时间,并反馈给实际系统。本发明能够实现人工系统和实际系统保持长期一致性,并对实际系统进行预测与控制,具有较高的精度和鲁棒性,适用于卫星快速机动控制。


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    Title :

    Satellite rapid maneuvering control method based on parallel system


    Additional title:

    一种基于平行系统的卫星快速机动控制方法


    Contributors:
    GAO YOUTAO (author) / GUO JINGHE (author) / DONG HANGSHUO (author) / DONG ZEZHENG (author) / CHENG YI (author) / YOU ZHICHENG (author)

    Publication date :

    2023-11-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / G06N COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS , Rechnersysteme, basierend auf spezifischen Rechenmodellen



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