Zhang Gaowang, Wang Feng, Chen Jian, Li Huayi
Research Center of the Satellite Technology, Harbin Institute of Technology, Harbin 150080, China.
Math Biosci Eng. 2022 Jan 4;19(3):2286-2309. doi: 10.3934/mbe.2022106.
This study focuses on the attitude control of a flexible spacecraft comprising rotating appendages, magnetic bearings, and a satellite platform capable of carrying flexible solar panels. The kinematic and dynamic models of the spacecraft were established using Lagrange methods to describe the translation and rotation of the spacecraft system and its connected components. A simplified model of the dynamics of a five-degrees-of-freedom (DOF) active magnetic bearing was developed using the equivalent stiffness and damping methods based on the magnetic gap variations in the magnetic bearing. Next, a fixed-time sliding mode control method was proposed for each component of the spacecraft to adjust the magnetic gap of the active magnetic bearing, realize a stable rotation of the flexible solar panels, obtain a high inertia for the appendage of the spacecraft, and accurately control the attitude. Finally, the numerical simulation results of the proposed fixed-time control method were compared with those of the proportional-derivative control method to demonstrate the superiority and effectiveness of the proposed control law.
本研究聚焦于由旋转附件、磁轴承以及能够承载柔性太阳能板的卫星平台组成的柔性航天器的姿态控制。利用拉格朗日方法建立了航天器的运动学和动力学模型，以描述航天器系统及其连接部件的平移和旋转。基于磁轴承中磁隙的变化，采用等效刚度和阻尼方法建立了五自由度主动磁轴承动力学的简化模型。接下来，针对航天器的各个部件提出了一种固定时间滑模控制方法，以调节主动磁轴承的磁隙，实现柔性太阳能板的稳定旋转，为航天器的附件获得高惯性，并精确控制姿态。最后，将所提出的固定时间控制方法的数值模拟结果与比例-微分控制方法的结果进行比较，以证明所提出控制律的优越性和有效性。
