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某些低轨道航天器在执行任务时 ,需要通过姿态控制系统使其有效载荷 (如星载相机 )在一段时间里连续指向地面或空间的给定目标。文中研究了带 3个反作用飞轮的低轨道航天器的姿态跟踪开展问题。首先根据刚体运动学知识推导出航天器的参考姿态角、参考角速度和参考角加速度表达式 ,然后基于卫星航天器姿态动力学给出了 3个互相垂直安装的反作用飞轮的控制律 ,并利用 L yapunov稳定性理论证明了闭环系统的渐近稳定性。最后通过数值仿真计算验证了控制算法的正确性
Some low-orbit spacecraft require their payloads (such as on-board cameras) to be pointed continuously at a given target on the ground or space through the attitude control system during their mission. In this paper, the attitude tracking of low-orbit spacecraft with three reaction flywheels is studied. Firstly, the attitude, reference angular velocity and reference angular acceleration of the spacecraft are deduced based on the knowledge of rigid body kinematics. Then three control laws of the reaction flywheel mounted vertically to each other are given based on the attitude dynamics of the satellite spacecraft. The yapunov stability theory proves the asymptotic stability of the closed-loop system. Finally, the correctness of the control algorithm is verified by numerical simulation