CAJ | 학술논문

基于时标分离思想,将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计.外环采用精确线性化方法设计控制器.考虑到飞行器转动惯量的大范围时变或摄动,内环采用模型参考自适应控制方法设计控制器.仿真验证了方法的有效性.
기우시표분리사상,장비행기자태공제계통분위만변화적자태각회로화쾌변화적각속도회로분별설계.외배채용정학선성화방법설계공제기.고필도비행기전동관량적대범위시변혹섭동,내배채용모형삼고자괄응공제방법설계공제기.방진험증료방법적유효성.
The aerocraft' s attitude control system is divided into the outer loop that is an angle loop and the in-ner loop that is an angle velocity loop based on their time-scale separation principle.Then the control law of each loop is designed independently.Exact linearization method is used for the outer loop controller.Model ref-erence adaptive control is used for the the inner loop considering the time variant or perturbation of aerocraft' s moment inertia.Simulation results demonstrate the effectiveness of the method.