The invention discloses a time optimal spacecraft attitude control method under pointing constraint. Comprising the steps of establishing an attitude model of a rigid spacecraft, establishing attitude constraints, establishing a time optimal spacecraft attitude control problem under attitude pointing constraints, performing constraint processing based on a control parameterization method and a constraint transcription method, and obtaining gradient information of a target function in the optimization problem. And solving a nonlinear programming problem by using the fmincon function of the MATLAB and gradient information to obtain the optimal maneuvering time and the optimal control sequence of the spacecraft. The method is a time-optimal attitude control scheme for the spacecraft attitude redirection problem under the pointing constraint, and realizes rapid attitude maneuver of the spacecraft while satisfying the attitude constraint; in addition, based on a constraint transcription method, an optimization problem of infinite dimension spacecraft attitude pointing constraint is converted into a parameter optimization problem of finite dimension constraint.

    本发明公开了一种指向约束下的时间最优航天器姿态控制方法,包括建立刚性航天器的姿态模型、建立姿态约束、建立姿态指向约束下的时间最优航天器姿态控制问题、基于控制参数化方法、基于约束转录方法约束处理、获取优化问题中目标函数的梯度信息,利用MATLAB的fmincon函数以及梯度信息求解非线性规划问题,得到航天器的最优机动时间以及最优控制序列。本发明是针对指向约束下航天器姿态重定向问题的时间最优的姿态控制方案,在满足姿态约束的同时实现航天器快速姿态机动;此外,基于约束转录法将无限维航天器姿态指向约束的优化问题转换为有限维约束的参数优化问题。


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    Title :

    Time optimal spacecraft attitude control method under pointing constraint


    Additional title:

    一种指向约束下的时间最优航天器姿态控制方法


    Contributors:
    LI BIN (author) / GUAN TAO (author) / LU YAO (author) / ZHONG XIAOQING (author) / ZHANG HAIBO (author) / WU YUNLI (author) / DONG FENG (author) / ZHANG SHUANGNA (author)

    Publication date :

    2024-05-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS