The application of H∞/mixed sensitivity approach to attitude control system for a winged missile

Considering the aerodynamic uncertainty of a winged missile, the longitudinal attitude controller design problem of the missile was transformed to mixed sensitivity problem. The longitudinal control loop of the missile was designed by the application of H_∞ mixed sensitivity control approach. A method of choosing the mixed sensitivity weight functions was given and computer simulations were performed. Detailed simulation results were given and compared with the results of classical PD controller. It is shown that the H_∞ mixed sensitivity approach has stronger robustness, and can effectively solve the aerodynamic uncertainty problem of the winged missile in the design of attitude control system.