高超声速飞行器模糊模型参考自适应控制方法  

The Research on Fuzzy Model Reference Adaptive Control for Hypersonic Vehicle

作　　者：程仙垒 刘鲁华[1] 汤国建[1] 

机构地区：[1]国防科技大学航天科学与工程学院,长沙410073

出　　处：《航天控制》2014年第4期13-18,共6页Aerospace Control

摘　　要：研究了高超声速飞行器大跨度飞行条件下的俯仰通道姿态控制问题。首先,建立了高超声速飞行器俯仰通道姿态运动模型。然后,针对高超声速飞行器俯仰通道模型非线性、不确定性等特点,应用模糊控制和模型参考自适应控制方法,设计了俯仰通道的模糊模型参考自适应控制器:以参考模型和实际系统的误差及其变化率作为模糊控制器的输入,以PID控制参数的修正量作为模糊控制器的输出,通过在线调节PID参数实现自适应控制。最后,对俯仰通道姿态控制方法进行了数值仿真。当模型发生切换时,俯仰角发生变化,能够在2s内精确跟踪参考模型,且稳态误差趋于0,验证了控制方法的有效性。A novel control scheme for attitude control of the hypersonic vehicle is proposed.Firstly,the mathematical model of the hypersonic vehicle pitching motion is established.Secondly,the attitude control system is designed by using fuzzy logic theory and model reference adaptive control methodology.A fuzzy controller is proposed in which the control gains are tuned according to the fuzzy rules,regarding the system error and derivative as fuzzy control inputs and PID control gain as fuzzy control output.Finally,the simulation results show the effectiveness of the proposed control scheme.

关 键 词：高超声速飞行器 模糊逻辑系统 模型参考自适应控制 俯仰通道姿态控制 切换模型 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]