ROBUST MISSILE AUTOPILOT DESIGN USING A GENERALIZED SINGULAR OPTIMAL-CONTROL TECHNIQUE

A generalized singular linear quadratic control technique is developed to design an optimal trajectory tracking system. The output feedback control law is designed using this technique. The feedback gain matrix is synthesized to minimize tracking errors with pole placement capability to satisfy the control activity requirements. Modeling error terms such as the uncertainty, nonlinearity, and the anticipated forcing function are included in the control problem formulation, enabling the resulting control law to adapt to these modeling changes. An application to a bank-to-turn missile-coordinated autopilot system design is presented. The optimal trajectory tracking autopilot consists of an adaptive feedforward controller and a robust output feedback controller.