The invention discloses a spacecraft attitude redirection control method based on a potential function under complex constraints, belongs to the technical field of spacecraft attitude maneuver planning control and adjustment, solves the attitude planning and control problems of a spacecraft under multi-constraint conditions, and provides a simple and effective solution for a GNRON problem existing in a traditional potential function. The method comprises the following steps: firstly, establishing a spacecraft kinematics and dynamics model described by an error quaternion, and defining an attitude prohibition area and an attitude forcing area by using a unit quaternion; secondly, constructing a strictly convex inverse proportion type potential function by utilizing convex parameterization of the forbidden region and the forced region so as to avoid generation of a local minimum value point; and then an effective solution is given for the GNRON problem existing in the potential function method, and a spacecraft attitude maneuver control law is designed based on the thought of a backstepping method. And finally, two groups of simulation results are given to verify the planning capability of the potential function for a multi-constraint region and a GNRON problem respectively.
本发明公开复杂约束下基于势函数的航天器姿态重定向控制方法,属于涉及航天器姿态机动规划的控制、调节技术领域,解决多约束条件下航天器的姿态规划与控制问题,并针对传统势函数存在的GNRON问题提出简单有效的解决方法。首先建立误差四元数描述下的航天器运动学与动力学模型,并使用单位四元数定义姿态禁止区域和姿态强制区域;然后利用禁止区和强制区的凸参数化构造严格凸的反比例型势函数,以避免局部极小值点的产生;接着针对势函数法存在的GNRON问题给出有效的解决方法,并基于反步法的思想设计了航天器姿态机动控制律。最后给出两组仿真结果分别验证势函数面对多约束区域和GNRON问题时的规划能力。
Spacecraft attitude redirection control method based on potential function under complex constraint
复杂约束下基于势函数的航天器姿态重定向控制方法
2023-05-23
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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European Patent Office | 2023
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