Flutter control of a composite plate with piezoelectric multilayered actuators |
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| Institution: | 1. Aeroelasticity and Smart Structures Group, Structures Division, National Aerospace Laboratories (CSIR), Bangalore 560017, India;2. Flight Mechanics and Controls Division, National Aerospace Laboratories (CSIR), Bangalore 560017, India;3. Aeronautical Development Agency, Bangalore 560037, India;1. College of Information Science and Technology, Shanghai Ocean University, Shanghai 201306, China;2. Department of Architecture and Civil Engineering, City University of Hong Kong, Kowloon, Hong Kong;3. City University of Hong Kong, Shenzhen Research Institute Building, Shenzhen Hi-Tech Industrial Park, Nanshan District, Shenzhen, China;1. School of Naval Architecture, Ocean and Civil Engineering, Shanghai Jiao Tong University, Shanghai 200240, China;2. Department of Architecture and Civil Engineering, City University of Hong Kong, Kowloon, Hong Kong, China;3. City University of Hong Kong Shenzhen Research Institute, Shenzhen 518057, China;1. School of Astronautics, Harbin Institute of Technology, P.O. Box 137, Harbin 150001, China;2. Dynamics and Vibrations Group, Numerical Methods in Mechanical Engineering, Technische Universität Darmstadt, Dolivostr. 15, Darmstadt 64293, Germany;3. College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China;1. Mechanical Engineering, Indian Institute of Technology (Indian School of Mines), Dhanbad 826004, India;2. Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560012, India |
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| Abstract: | Active flutter velocity enhancement scheme is presented for lifting surfaces, employing Linear Quadratic Gaussian based multi-input multi-output controller with multilayered piezoelectric actuators. To numerically test the developed concept, a composite plate wing, surface bonded with eight piezoelectric bender actuators and sensors has been considered. A modal flutter control model is formulated in state-space domain using coupled piezoelectric finite element procedures along with unsteady aerodynamics and optimal control theory. The bending – torsion flutter instability has been actively postponed from 44.13 to 55.5 m/s using the energy imparted by the multilayered piezoelectric actuators. As the power requirement by these actuators is comparatively very low with respect to stack actuators, they can be employed in an integrated form to develop active lifting surfaces for real time applications. |
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