The Design of Integrated Guidance and Control Law Considering Rudder Angle Saturation

Abstract

The hypersonic vehicle doesn’t satisfy separation design condition of guidance and control law in the terminal guidance process. Moreover, the rudder angle of system is easy to be long time saturated because the state of guidance and control system changes rapidly. If the guidance and control law is designed without considering above two points, the closed-loop system performance will be influenced and the system may be instability. So, an integrated guidance and control law is designed with considering rudder saturation in this paper. Taking the anti-saturation control method into the integrated design of guidance and control law, an anti-saturation compensator is designed to compensate the state changes caused by input bias. The integrated guidance and control law with rudder saturation is deduced and the closed-loop system’s stabilization is proved. The numerical simulation shows that the closed-loop system has better performance when the designed anti-saturated guidance and control law is used. It has shorter saturation time and higher control efficiency than traditional guidance and control law.