The application of gain-scheduling H_ infinity controllers for a missile atuopilot

摘要

In this paper, a gain-scheduling H _infinity autopilto for a missile pitch axis is designed over a wide operating range. The synthesis of the paramettric controller is based on a loo-shaping design at distinct operating conditions and on a least-squares procedure over the entire flight envelope. Robust stability and performance are firstly checked by means of linear simulations and #mu# -analysis, and secondly verified by using non-linear simulations, in the face of noise disturbances, aerodynamic dispersions and scheduling parameters variations.