Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H₂/H_∞Control

Abstract

We report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees <TEX>$H_2/H_{\infty}$</TEX> performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory.