Abstract
In this paper we design a robust adaptive model reference autopilot for a symmetrical missile in both pitch and yaw planes. The design is baseutopilot forapunov stability theory to ensure the stability of the adaptive contrond on the Laptive algorithm is tested for a simple linear plant, and for a linear time-varying plant, which approximates up to a reasonable degree the nonlinear plant (missile plodel). Moreover, the adaptive algorithm is implemented in the nonlinear flight model, and the scaling matrices are adjusted properly to achieve satisfactory re- sponses to both step command test signal at different points on the trajectory And a command signal from the guidance algorithm, in order to verify the perfor- mance of the adaptive autopilot. A model reference adaptive autopilot designed and simulated with a nonlinear flight model has shown a superior performance in the existence of unmodeled dynamics, stochastic disturbance at input and output, actuator