微纳卫星姿态机动的变论域模糊PID控制

Variable Universe Fuzzy PID Control for Attitude Maneuver of Nanosat

为了简化计算,满足实时处理的要求,建立了微纳卫星的姿态角动力学模型,并应用欧拉角参数描述运动学模型。针对微纳卫星系统的时变、环境外力矩干扰等因素,同时考虑到系统参数不确定性问题,设计了变论域模糊PID控制律的姿态控制器。不考虑解耦运算,分析了控制器的动态变化参数对姿态稳定控制性能的影响。基于MATLAB/SIMULINK对该系统进行了仿真验证。仿真结果表明,在卫星姿态控制方面,该控制方法具有稳定性好、响应快速、系统超调量小的特点,能够使微纳卫星完成对目标姿态的机动控制,实现对系统姿态的有效控制。

In order to simplify the calculation and satisty the requirement of real - time processing,the attitude angle dynamics model of nanosat is established, and the kinematics model is described by using Euler angle parameters. Aiming at the time varying and environment external torque disturbances, and considering the uncertainty of the system parameters, the attitude controller of variable universe fuzzy PID control has been designed ; without considering the decoupling calculation, the influence of the dynamic variation parameters of the controller on the stably control performance of attitude. The simulation and verification of the system are carried out based on Matlab/simulink. The simulation results verify the correctness, in attitude control of the satellite,this control method features good stability, fast response and small overshoot;makes nanosat complete the target attitude maneuver, and achieve the effective control of the systematic attitude.