CAJ | 학술논문

建立了带有太阳翼的挠性航天器的姿态动力学模型,应用改进的罗德里格参数来描述姿态运动学模型。针对挠性航天器模型参数不确定性和环境干扰等问题,提出了变论域自整定模糊比例积分微分(PID)控制方案,构建了计算简单并且可以达到控制精度的伸缩因子。基于Matlab/Simulink进行了仿真验证,结果表明,变论域自整定模糊 PID 控制响应速度比传统PID控制、模糊PID控制快350 s,且无超调,不仅能够使航天器完成对目标姿态的机动,而且能够有效地抑制挠性太阳翼的振动。
건립료대유태양익적뇨성항천기적자태동역학모형,응용개진적라덕리격삼수래묘술자태운동학모형。침대뇨성항천기모형삼수불학정성화배경간우등문제,제출료변론역자정정모호비례적분미분(PID)공제방안,구건료계산간단병차가이체도공제정도적신축인자。기우Matlab/Simulink진행료방진험증,결과표명,변론역자정정모호 PID 공제향응속도비전통PID공제、모호PID공제쾌350 s,차무초조,불부능구사항천기완성대목표자태적궤동,이차능구유효지억제뇨성태양익적진동。
The attitude dynamical equations of flexible spacecraft with solar panels were established, and the attitude kinematic equations were described by modified Rodrigues parameters (MRPs ) in order to prevent the singularity of the large angle maneuver. A variable universe self-tuning fuzzy PID controller was proposed for model uncertainties and environmental disturbances. A new shrinkable factor was designed, and it was easy to calculate and could achieve the accuracy. Numerical simulation based on Matlab/Simulink shows that the response of the variable universe self-tuning fuzzy PID controller are 350 s faster than that of the conventional PID and fuzzy PID controllers, and that it has no overshoot and can realize the effective control of attitude maneuver and effectively suppress the vibration of solar panels.