Robust aeroelastic control of flapped wing systems using a sliding mode observer |
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| Institution: | 1. Korea University, Department of Mechanical Engineering, Seoul 136-701, South Korea;2. Virginia Polytechnic Institute and State University, Department of Engineering Science and Mechanics, Blacksburg, VA 24061, USA;3. Pusan National University, Department of Naval Architecture and Ocean Engineering Pusan 609-735, South Korea;4. Clarkson University, Department of Mechanical and Aeronautical Engineering, Potsdam, NY 13699-5725, USA;2. Haifa, Israel;1. School of Electrical and Automation Engineering, Hefei University of Technology, Hefei 230009, PR China;2. Engineering Technology Research Center of Industrial Automation, Anhui Province, Hefei 230009, PR China;1. Universidad Distrital Francisco José de Caldas, Bogotá, Colombia;2. Universidad Nacional de Colombia, Bogotá, Colombia |
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| Abstract: | The performance of a robust control strategy applied to a three-degrees-of-freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined. |
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