CAJ | 학술논문

为解决无控刚性箭体和弹性箭体姿态控制系统的不稳定问题，以俯仰通道为例，对无控刚性箭体引入了姿态角偏差和姿态角速度偏差反馈，设计了 PD 控制器；对弹性箭体引入结构滤波器，进行控制器设计.仿真结果显示无控刚性箭体和弹性箭体姿态控制系统俯仰通道的稳态误差分别为0.05%、-0.30%，从而使无控刚性箭体和弹性箭体姿态控制系统的不稳定问题得到了有效控制.
위해결무공강성전체화탄성전체자태공제계통적불은정문제，이부앙통도위례，대무공강성전체인입료자태각편차화자태각속도편차반궤，설계료 PD 공제기；대탄성전체인입결구려파기，진행공제기설계.방진결과현시무공강성전체화탄성전체자태공제계통부앙통도적은태오차분별위0.05%、-0.30%，종이사무공강성전체화탄성전체자태공제계통적불은정문제득도료유효공제.
In order to solve the instability of free rigid rocket and elastic rocket attitude control systems,taking the pitch channel as an example,the attitude angle and attitude angular velocity deviation feedbacks are added to the PD controller for the free rigid rocket,and a structure filter is added to the controller for the elastic rocket.The simulation results show that pitch channel steady-state errors of free rigid rocket and elastic rocket attitude control systems are 0.05%,-0.30%separately.So the instability of free rigid rocket and elastic rocket attitude control systems is controlled effectively.