欠驱动刚体航天器姿态稳定的时变控制方法  

Time-varying Control Method for Attitude Stabilization Control System of Underactuated Rigid Spacecraft

作　　者：郑彦琴[1] 戈新生[1] 

机构地区：[1]北京信息科技大学自动化学院,北京100192

出　　处：《系统仿真学报》2010年第4期951-956,共6页Journal of System Simulation

基　　金：国家自然科学基金(10702020)

摘　　要：研究欠驱动刚体航天器姿态控制系统的稳定性问题。首先给出欠驱动刚体航天器的姿态动力学方程和用(w,z)参数描述的姿态运动学方程,根据所建系统模型的特点,设计相应的连续时变控制律,在控制律的设计中引入辅助变量v、v1和v2,利用平均方法对系统模型方程进行简化,基于退步控制设计v、v1和v2的控制律,利用两个轴角速度与失控轴角速度的交叉耦合关系对失控轴的姿态进行控制。数值仿真验证了所设计控制律的有效性。The problem of stabilization was studied for an underactuated rigid spacecraft. First of all,the system dynamic and kinematic equations were given,and the kinematic equation was described by the （w,z） parameterization. Some continuous time-varying control laws were then designed based on the characteristic of the system model. The accessorial variables v 、v1 and v 2were imported in the designing course of the control laws. The equations of the system model were predigested using the averaging method,then the control laws of the v 、 v1 and v 2were contrived via backstepping method. The cross coupling relation of angular velocity was utilized to regulate the uncontrollable attitude component. Simulating results validate the availability of the proposed control algorithm.

关 键 词：航天器 欠驱动系统 姿态稳定 退步控制 时变控制 

分 类 号：TP391[自动化与计算机技术—计算机应用技术]