The application of the MATLAB/SIMULINK analysis packages to the design of a discrete linear quadratic optimal missile autopilot

This paper describes the application of the MATLAB and SIMULINKT packages in the design and analysis of a discrete-time lateral autopilot for a generic tactical missile. This missile is highly manoeuvrable, tail controlled, and has a symmetric cruciform configuration. Such a missile exhibits a non-minimum phase response to acceleration commands and may be open loop unstable at some points in the flight envelope. This paper makes use of modern discrete-time linear quadratic (LQ) optimal control techniques to design the missile autopilot. The performance of the final design is assessed by examining the closed loop step response. Open loop gain margin and phase margin are the standard indicators of robustness.