Model and Adaptive Flight-by-Wire Control Law of an Autogyro

Abstract

The autogyro is the first successful type of rotating-wing aircraft. With simple mechanical structure and high aerodynamic efficiency, it has significant development and application potential in UAM and military scenes, which presents new requirements for flight control. This paper presents a new control scheme for autogyro. An example autogyro is modeled based on explicit blade element method. The dynamic modes and stability are analyzed. To tackle the model uncertainty and disturbances, a new control scheme is proposed with normal load control. The scheme employs Robust Servomechanism LQR method augmented with L1 adaptive controller to achieve fast compensation. Numerical simulations illustrate the superior performance of the proposed scheme in the presence of disturbances.