ROBUST AUTOPILOT DESIGN FOR A HIGHLY FLEXIBLE AIRCRAFT

摘要

This paper discusses the design of a robust autopilot system for a flexible aircraft, with significant coupling between flight mechanics and structural dynamics modes. Based on a lateral model, an autopilot inner loop law is designed with an iterative algorithm which will guarantee aeroelastic stabilization and robustness with respect to parameter uncertainties. This new synthesis algorithm will be applied to a civil aircraft autopilot in lateral flight At the end, the robustness of the flight control law with respect to parameter uncertainties such as delays, actuator and calibrated airspeed will be analyzed.