CAJ | 학술논문

研究挠性卫星的姿态稳定性问题，利用H∞控制思想设计控制器，来消除不同的内外界干扰对卫星本身所造成的影响。针对挠性卫星的姿态控制系统，俯仰角、滚动角和偏航角及其角速度都是较小的变化量，可以把姿态系统的运动学方程以及动力学方程设计成较简单的线性化系统。基于LMI设计出姿态系统的输出反馈H∞控制器。并通过大量的仿真，验证了上述理论的可靠性和合理性。实验结果表明，上面提出的控制器设计思想能够很好地消除外部空间干扰对卫星姿态稳定性造成的影响。
연구뇨성위성적자태은정성문제，이용H∞공제사상설계공제기，래소제불동적내외계간우대위성본신소조성적영향。침대뇨성위성적자태공제계통，부앙각、곤동각화편항각급기각속도도시교소적변화량，가이파자태계통적운동학방정이급동역학방정설계성교간단적선성화계통。기우LMI설계출자태계통적수출반궤H∞공제기。병통과대량적방진，험증료상술이론적가고성화합이성。실험결과표명，상면제출적공제기설계사상능구흔호지소제외부공간간우대위성자태은정성조성적영향。
This paper considerd the attitude stability of a flexible satellite, and used the thought of H∞ control to design a controller to eliminate the effect which results from the external disturbance for the satellite. The pitch angle, roll angle, yaw angle and the angular velocity were relatively small amount in allusion to the flexible satellite attitude control system. The kinematical equation and dynamical equation of the attitude system can be designed to a relatively simple linear system according to the above ideas. Then the optimal output feedback H∞ controller of the attitude control system can be designed based on LMI. The mathematical simulation results show that the method can effec-tively eliminate the impact resulted from the external space disturbance.