Research Of Synthetic Control For Supersonic Air-to-air Missile With High Angle-of-attack

The main content of the paper is to design an air-to-air missile autopilot by self-tuning adaptive theory. This type of missile has some characters such as supersonic speed and high angle-of-attack, which cause nonlinear timevariation, cross-coupling among three channels and other uncertainties of aerodynamic parameters. To solve this problem, the recursive instrumental variable method with limited memory is founded, which will identify the aerodynamic parameters of the missile online. Based on that method, a pole assignment self-tuning adaptive autopilot with improved performance and robustness is designed.The recursive accessorial variable method with limited memory can eliminate the effect of the data saturation and colored noise. That will ensure the accuracy of the identification to the time-varying parameters when there is noise in real-time system. The pole assignment self-tuning regulator can be used to control the non-minimum phase systems such as missiles. The control signal is limited in a suitable range. Meanwhile, the poles of closed-loop system can be configured according to the design requirements to obtain the desired property. This control algorithm is sample, robust, and widely applied.The basic structure of the autopilot is constructed on the foundations of missile-model. On the basis of the identified parameters, a pole assignment self-tuning adaptive control algorithm is designed, which achieves the design requirements. Through mathematical simulation using the MATLAB tools and hardware-in-loop simulation including the missile servos, the result is proved to be correct that the pole assignment self-tuning adaptive autopilot can stabilize the attitude of the missile and attain a nice dynamic capability. It also can effectively restrain the influence of uncertainties of aerodynamic parameters. Compared with the traditional gain scheduling control system, it has better performance and stronger robustness.