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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
