Title :
Design of flight control system for quad tilt-wing UAV
Author :
Mikami, Takahito ; Uchiyama, Kenji
Author_Institution :
Dept. of Aerosp. Eng., Nihon Univ., Chiba, Japan
Abstract :
Aircraft control system is designed to provide adequate stability during transition flight of a quad-tilt wing (QTW) UAV. The dynamic inversion method, which is a linearization method without an approximation algorithm, is applied to a control problem of the UAV, because of strong nonlinearity of its dynamical behavior. The validity of the proposed control system is verified through numerical simulation and experiment.
Keywords :
aerospace components; aircraft control; autonomous aerial vehicles; control nonlinearities; control system synthesis; linearisation techniques; numerical analysis; QTW UAV; aircraft control system; dynamic inversion method; dynamical behavior nonlinearity; flight control system design; linearization method; numerical simulation; quad tilt-wing UAV; stability; transition flight; unmanned aerial vehicle; Aerodynamics; Aerospace control; Control systems; Mathematical model; Nonlinear dynamical systems; Rotors; Unmanned aerial vehicles; QTW-UAV; dynamic inversion method; transition flight;
Conference_Titel :
Unmanned Aircraft Systems (ICUAS), 2015 International Conference on
Conference_Location :
Denver, CO
Print_ISBN :
978-1-4799-6009-5
DOI :
10.1109/ICUAS.2015.7152364
