Integrated Control and Guidance Systems for High Angle of Attack Missiles

Development of seamlessly integrated flight control and guidance systems for short-range missiles capable of high angle-of-attack maneuvers is proposed. Modern nonlinear dynamic systems methods such as bifurcation analysis will be used to study the missile dynamic behavior at high angles of attack. The use of various flight control actuator modes such as continuous control, bang-bang control with and without a sliding mode, and pulse width modulation will be explored. Optimal blending of multiple control actuators will be examined. Autopilot designs will be based on control system techniques such as gain-scheduled linear control, feedback linearization, Lyapunov optimal control, describing functions, and sliding mode control. a nonlinear high angle of attck guidance law based on differential game theory will be used to generate commands for the autopilot. The high angle of attck missile control and guidance laws will be ealuated in a simulation to bring out the advantages of high angle of attack maneuvers.