Design and Flight Testing of a Gain-Scheduled Autopilot Based on Reduced Model Constraints

Abstract

The purpose of this paper focuses on the design, evaluation and flight testing of a gain-scheduled autopilot for a missile system based on reduced modelling constraints. The controller synthesis based on frequency response analysis theory formed the basis for the implementation of gain-scheduled controllers. During the controller synthesis process, the design constraints were based on a reduced missile model and analytically computed controller initial gains which improved the controller optimization phase while satisfying the robustness and performance requirements across the envisioned flight envelope. This process was shown to produce successful results in both a nonlinear desktop simulation and a flight testing campaign.