Full envelope missile longitudinal autopilot design using the state-dependent Riccati equation method

Abstract

A full envelope missile output feedback pitch autopilot is designed using the state-dependent Riccati equation (SDRE) approach presented in [1]. The particular SDRE design methodology chosen for this paper is referred to as SDRE HZ- The SDRE HI design structure is the same as that of linear HZ, except that the two Riccati equations are state-dependent. Hence, SDRE HZ design is a nonlinear extension of linear HZ design. A full envelope missile model using the same aerodynamics as an earlier work [5] is used to demonstrate the usefulness of the SDRE method for full envelope design. In this paper the SDRE Hz method is breifly discussed. The full envelope model is described and the state dependent coefficient (SDC) parameterization is presented. Finally the SDRE Hz design and design results are presented.