Robust Lateral Augmented Acceleration Flight Control Design

Abstract

A lateral augmented acceleration autopilot is designed for a model of a tactical missile. The tail-controlled missile in the cruciform fin configuration is modelled as a second-order quasi-linear parameter-varying system. The autopilot design is based on input-output pseudolinearisation, which is a restriction of input-output feedback linearisation to the set of equilibria of the nonlinear model. Robust autopilot design taking account parametric stability margins for uncertainty aerodynamic derivatives is implemented using convex optimisation and linear matrix inequalities - LMI. Simulations for constant lateral acceleration demands including uncertainties show satisfactory robust performance.