Closed-loop control of a microtab-based load control system

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[1] Cooperman, Aubryn M.
[2] Van Dam, C.P.
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| 1600年 / AIAA International卷 / 52期
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A closed-loop control system has been developed for microtabs and demonstrated in the University of California; Davis; Aeronautical Wind Tunnel. Input to the system comes from two dynamic pressure transducers located at 15% chord on the upper and lower surfaces of the airfoil. Microtabs with a height of1%chord are located at 95%chord on the lower surface and 90% chord on the upper surface; enabling rapid increase or decrease of the lift force through deployment of the tabs on the pressure or suction side of the airfoil; respectively. Tests have been conducted with variations of up to 23% in airspeed; and the control system is able to reduce the total deviation in the lift force by 60% compared to the performance of the airfoil without the control system. The experiment validates the effectiveness of closed-loop control of lift using a trailing-edge tab-based system for lifting surfaces such as wind-turbine rotor blades. Copyright 2014 by the American Institute of Aeronautics and Astronautics; Inc. All rights reserved;
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