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.
Design of flight control system for quad tilt-wing UAV
01.06.2015
675803 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Quad Tilt Wing VTOL UAV: Aerodynamic Characteristics and Prototype Flight
British Library Conference Proceedings | 2009
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