Adaptive Autopilot Design for Missiles with Aerodynamic Parameters Rapidly Varying

An indirect adaptive control scheme is applied to the design of an autopilot for missiles with aerodynamic parameters rapidly varying. Controller design is based on the linearized model of missile motions. It is assumed that system parameters. are modelled as linear combinations of known bounded functions with unknown constant coefficients. Unknown coefficients are then estimated and based on the parameter estimates an adaptive controller is constructed. As an example, a normal acceleration controller for a generic bank-to-turn missile is designed and excellent performance is shown by large-scale computer simulations.