非干渉化参照モデルを用いた2自由度制御による柔軟構造をもつ宇宙機の姿勢制御と制振の両立

抄録

One of the problems of spacecraft with flexible structure is that vibration is generated in the flexible structure due to the demand of attitude control of the spacecraft, and this vibration affects to the performance of the attitude control. A flexible structure has higher order modes which cannot be treated as controlled modes, and those modes can make the spacecraft unstable. Moreover, in a real spacecraft system, there are some time delays such as in the actuator. Time delay may destroy the stability of the control system. In this paper, two-degree-of-freedom (2DOF) control using the decoupled plant as a reference model is developed. It is shown that both three-axis attitude control and vibration suppression including higher order modes are achieved by the 2DOF control in the presence of spillover and time delay.