STABILITY AND FLYING QUALITIES ROBUSTNESS OF A DYNAMIC INVERSION AIRCRAFT CONTROL LAW

Dynamic inversion, or feedback linearization theory, represents a comm only 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 flyi ng qualities robustness of a dynamic inversion based control law, desi gned for a prototype aircraft, to uncertain aerodynamic parameters is analyzed. The results indicate that the pitch plane stability and dyin g qualities are robust to parameter uncertainties, but the lateral dir ectional dying qualities are sensitive to uncertain stability derivati ves.