基于扩张观测器的航天器无速度旋量信息姿轨一体化控制

针对在轨飞行期间无法精确获得速度信息（角速度与质心速度）的情况,设计了基于扩张状态观测器的航天器姿轨一体化控制器.首先给出了基于对偶四元数的航天器姿轨一体运动学与动力学模型；然后针对速度旋量信息缺失的情形并考虑模型参数误差与外界扰动设计了扩张状态观测器,并利用Lyapunov稳定性定理分析观测误差的有限时间收敛性；最后基于该扩张观测器设计航天器姿轨一体快速终端滑模控制器,分析该控制系统的有限时间收敛性,并进行数值仿真验证.

Integrated attitude-orbit control for spacecraft without velocity screw information based on extended state observer

An integrated attitude-orbit controller based on extended state observer (ESO) is designed for spacecraft to settle down the unavailability of angular velocity and centroid velocity during on-orbit flight.First,the spacecraft''s integrated attitude-orbit kinematics and dynamics model is presented based on dual quaternion.Second,an extended state observer is designed for the case of velocity screw information missing,which takes the model parameter error and external disturbance into account,and the finite time convergence of the observation error is analyzed by using Lyapunov stability theorem.Then a fast terminal sliding mode controller for integrated attitude-orbit control is designed based on the above extended state observer,and its finite time convergence is analyzed.Finally,a numerical simulation is given to verify the effectiveness of the control system.