基于反馈解耦法的旋转火箭弹自适应控制系统设计

火箭弹弹体的旋转将引起俯仰和偏航通道的强耦合,而且在飞行过程中,导弹的动力学参数在不断变化。这些因素加大了旋转火箭弹的控制系统设计难度。采用反馈方法实现了俯仰、偏航两通道的动态解耦,并利用模型参考自适应控制方法完成了两通道的控制系统设计。研究发现,所提方法很好地克服了耦合因素对控制系统的影响,提高了控制系统对动力学参数变化和外界干扰的鲁棒性,满足旋转火箭弹飞行控制系统设计要求。

Design of Adaptive Control System for Spinning Rockets Based on Feedback Decoupling Method

The spinning of rockets will cause strong coupling between pitch and yaw channel and the kinetic parameters of rockets are changing significantly during flight,which will make it more difficult to design the control system for spinning rockets. For the coupling of two channels,the feedback method is applied to achieve dynamic decoupling and the model reference adaptive control (MARC) method is used to design the controller for every single channel. The results show that the above methods can reduce the impact of coupling on control system and improve robustness of control system against the changes of kinetic parameters and external disturbance as well as satisfy the requirements of flight control system for spinning rockets.