空间飞行器姿态控制器设计与仿真  

Design and Simulation of Spacecraft Attitude Controller

作　　者：华莹[1] 王青[1] 

机构地区：[1]北京航空航天大学自动化与电气科学学院自动控制系

出　　处：《计算机仿真》2006年第7期52-55,共4页Computer Simulation

摘　　要：该文对空间飞行器姿态系统设计了一种变结构控制器。首先,应用误差四元数法描述空间飞行器姿态运动。同时,在考虑结构摄动和外界扰动的界未知情况下,其基本方法是采用模糊规则优化滑模变结构控制的设计,并且能够在线对结构摄动和外界扰动的界进行估计,使得系统轨迹既能快速趋近滑动面又能降低抖振,从而提高了变结构控制系统的品质。仿真结果表明,该系统对模型不确定性和外来干扰具有较强的鲁棒性,同时避免了变结构系统固有的抖振问题,性能令人满意。The dynamics of the attitude based on the error unit quaternion by the description of the attitude parameter is given, which reduces the singularity of Euler angle during flying. First, the characteristic of the attitude control system is analyzed. Furthermore, an improved variable control approach is proposed under the condition of structure perturbation and unknown external boundary disturbances. The design of the sliding mode control is optimized by fuzzy rules, and the structure perturbation and the boundary of the unknown external disturbances are estimated. So the system trajectory can quickly approximate the sliding plane and the chattering is weakly. Thus the performance of the variable control systenl is improved. Simulation results show that the system is robust to model uncertainties and external disturbances, and it smoothes the system chattering phenomenon. The performance is satisfactory.

关 键 词：空间飞行器 姿态控制 变结构控制 模糊控制 自适应性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]