Total Energy Flight Control Architecture Optimization for a Tilt-Wing Aircraft

Abstract

It is imperative that safe and robust flight control system architectures are employed for the novel vertical takeoff and landing urban air mobility concepts currently in various stages of development. Unique challenges stem from the over-actuated nature of these vehicles and the fact that they transition between vertical and forward modes of flight. This paper aims to present a methodology for designing and optimizing a Total Energy-based control system architecture for a tilt-wing urban air mobility concept. The Total Energy Control System algorithm, which was originally developed for fixed-wing applications, is extended to also be applicable to hovering and transitioning flight. Control system parameters are optimized using a genetic algorithm optimization scheme, subject to constraints on dynamic stability and control response characteristics. Control system optimization and flight simulations are performed using the MATLAB/Simulink-based Modular Aircraft Dynamics and Control Algorithm Simulation Platform. Results presented will include the performance of the flight control system for lateral, longitudinal, and directional maneuvering at airspeeds representative of hover, transition, and forward flight conditions as well as during transitions between vertical and forward flight modes. The presented results will aim to demonstrate the effectiveness of the proposed control system architecture and the demonstrated optimization methodology.