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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...
A robust control method is proposed for quadrotor systems. The designed controller is developed based upon the quaternion representation model, which is subject to multiple uncertainties. A feedback controller is proposed to restrain the effects of nonlinearities and uncertainties on the closed-loop system. These uncertainties are considered as input equivalent disturbances and their effects are proven...
In this work, design and control system development of a gas-electric hybrid quad tilt-rotor UAV with morphing wing are presented. The proposed aircraft has an all carbon-composite body, gas-electric hybrid electric generation system for 3 hours hovering or up to 10 hours of horizontal flight, a novel configuration for VTOL and airplane-like flights with minimized aerodynamic costs and mechanical...
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