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Experimental studies of leading edge vortex control of delta wing micro aerial vehicle

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Języki publikacji
EN
Abstrakty
EN
It is known, that small disturbances generated by the micro actuators can alter large-scale vortex structures, and consequently, generate appreciable aerodynamic moments along all three axes for flight control. In the current study, we explored the possibility of independently controlling these moments. We perform analytical simulations showing optimal position of LEX generators, and water tunnel measurements showing effectiveness of MEX generators as MAV control devices. We applied array of actuators located on either the forward or the rear half section of the leading edge. Both one- and two-sided control configurations have also been investigated. Experimental results showed that asymmetric vortex pairs were formed, which leads to the generation of significant torques in all three axes. The article presents typical vortical flow over a delta wing, water tunnel at Wroclaw University of Technology, experimental setup and procedures, static test results on water tunnel testing including normal forces, pitching and yawing moments, maximum values of rolling, pitching, and yawing moment coefficients, effectiveness of pitching and yawing control.
Twórcy
autor
  • Air Force Institute of Technology Ks. Boleslawa Street 6, Warsaw, 01-494, Poland
autor
  • Air Force Institute of Technology Ks. Boleslawa Street 6, Warsaw, 01-494, Poland
  • Wroclaw University of Technology Wybrzeże Wyspiańskiego 27, 50-370 Wroclaw, Poland
Bibliografia
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Uwagi
Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-79b46984-7fdf-43d5-9fe8-bde645345107
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