Robust Nonlinear Missle Autopilot Design

Abstract

A methodology incorporating both dynamic inversion and structured singular value synthesis is employed to design a robust nonlinear autopilot for an air-to-air missile. The nonlinear components include fast and slow inversion loops which approximately lin earize the system when closed in the absence of modeling errors. A feedback control law is designed for this closed-loop system in the presence of structured uncertainties. The current controller architecture differs from previous work in the following two respects: uncertainties and modeling errors in the slow dynamics are treated explicitly, and the autopilot accepts external commands in bank angle rather than stability-axis roll rate.