卫星姿态的状态转移控制

State transition control of satellite attitude

中文关键词  卫星  反馈线性化  幂级数  模型预测  广义逆变换  状态转移  姿态控制

英文关键词  satellite  feedback linearization  power series  model prediction  generalized inverse transform  state transition  attitude control

中文摘要

      本文面向卫星的应用需求, 对卫星姿态的运动学和动力学进行了分析与建模. 利用反馈线性化, 将姿态运 动的高阶非线性项包含在姿态控制中, 通过局部动态线性化, 将动力学系统近似为定常系统. 通过幂级数法对系统 进行了状态转移过程的求解. 采用模型预测的方法获得姿态角和姿态角速度的预期偏差. 通过广义逆变换构造关 于偏差的最小范数、最小二乘控制器. 提出了一种基于状态转移的卫星姿态机动、跟踪与稳定控制的新方法. 控制 器的参数具有根据系统采样周期和当前状态时变自适应的特点. 考虑帆板挠性及多种偏差和噪声影响, 仿真验证 了方法的可行性和有效性.

英文摘要

      For the application requirements of satellite, the kinematics and dynamics of satellite attitude are analyzed and modeled. By using feedback linearization, the high-order nonlinear terms of attitude motion are included in attitude control, by local dynamic linearization, the satellite dynamical system is approximated as a time-invariant system. Method of power series is used to carry out approximate solution of the system state transition. The expected deviation of attitude angle and attitude angular velocity is obtained by using model prediction. By generalized inverse transform, a kind of full state feedback controller is designed based on the minimum norm and least squares of deviation. A high precision control method based on state transition for satellite attitude maneuver, tracking and stabilization is proposed. The parameters of the controller have the characteristics of time-varying adaptive according to the sampling period and the current state of the system. Considering the influence of solar panels flexible vibration and various noise and error, the feasibility and effectiveness of the method are verified by simulation.