The invention discloses a spacecraft attitude variable performance control method considering input saturation, and relates to the technical field of spacecraft attitude control. Establishing a spacecraft dynamic model by considering the spacecraft attitude control system with external environment interference and input saturation, and converting the spacecraft attitude control system into a spacecraft attitude model with preset performance by adopting an error conversion function; constructing a variable performance functional equation in combination with a saturation amplitude limiting function; and designing control input by combining the spacecraft attitude model with the preset performance and the variable performance function so as to design the anti-saturation auxiliary system. Based on preset performance control, external environment interference and input saturation amplitude limiting are considered, and a variable performance function is introduced, so that the problem of failure of spacecraft attitude preset performance control during saturation is solved.

    一种考虑输入饱和的航天器姿态可变性能控制方法,涉及航天器姿态控制技术领域。考虑存在外部环境干扰和输入饱和的航天器姿态控制系统建立航天器动力学模型,采用误差转换函数将航天器姿态控制系统变换为预设性能的航天器姿态模型;结合饱和限幅函数构造可变性能函数方程;结合预设性能的航天器姿态模型和可变性能函数设计控制输入,从而设计抗饱和辅助系统。基于预设性能控制,考虑外部环境干扰以及输入饱和限幅,通过引入可变性能函数,解决航天器姿态预设性能控制在饱和时的失效问题。


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    Title :

    Spacecraft attitude variable performance control method considering input saturation


    Additional title:

    一种考虑输入饱和的航天器姿态可变性能控制方法


    Contributors:
    ZHANG YING (author) / LONG FEIXIONG (author) / WU AIGUO (author)

    Publication date :

    2024-08-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS