Dynamic Inversion for Missile Lateral Velocity Control via Polynomial Eigenstructure Assignment

Abstract

A sideslip velocity autopilot is designed for a model of a tactical missile. The tail-controlled missile in the cruciform fin configuration is modelled as a secondorder quasi-linear parameter-varying system. This nonlinear model is obtained from the Taylor linearised model of the horizontal motion by including explicit dependence of the aerodynamic derivatives on a state (incidence) and external parameters (Mach number). The autopilot design is based on Polynomial Eigenstructure Assignment which can be view as another approach to dynamic inversion. The theory of Polynomial Eigenstructure Assignment is described and the resulting controller is presented in a chosen structure. The stability is proved over the full envelope of the missile. Simulations for constant lateral acceleration demands show good tracking with fast response time over the full envelope.