Stability and flying qualities robustness of a dynamic inversion aircraft control law

Abstract

Dynamic inversion, or feedback linearization theory, represents a commonly used nonlinear control method for designing aircraft control laws. This method has the ability to control a highly nonlinear plant but suffers from the lack of guaranteed robustness. The stability and flying qualities robustness of a dynamic inversion based control law, designed for a prototype aircraft, to uncertain aerodynamic parameters is analyzed. The results indicate that the pitch plane stability and flying qualities are robust to parameter uncertainties, but the lateral directional flying qualities are sensitive to uncertain stability derivatives.