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HIGH ANGLE OF ATTACK FLIGHT CONTROL OF DELTA WING AIRCRAFT USING VORTEX ACTUATORS

MAY, CAMERON
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109166873

Abstract Details

2005, MS, University of Cincinnati, Engineering : Aerospace Engineering.
The overall objective of this work was to develop an active fluidic control system that can effectively manipulate the vortex breakdown location over a highly swept delta wing. By moving the vortex breakdown fore or aft, a pitching moment can be induced on the delta wing without the use of any conventional control surfaces. The active control system can be incorporated into a feedback loop to input a desired pitching moment based on the real-time measured surface pressure. The type of active fluidic control system shown to be the most effective at delaying vortex breakdown was the along-core injection technique. In the previous studies using this technique, the control was an open loop system, that is, the flow field was observed and measured and then injection conditions were changed manually. The process was repeated until optimal conditions were observed. In order to move this technique closer to practical application, two important steps must be taken. The fist step is to close the control loop so that input changes can be instantly made according to the changing flow field. The second step is to simplify and optimize the control system. One advantage this control system has over conventional control surfaces is its simplicity. Conventional control surfaces employ complex and costly combinations of hydraulic and electronic components whereas the along-core injection system requires only solenoid actuators and a source of compressed air. Compressed air is readily available in the form of compressor bleed on most gas turbine engines. Other advantages of this system include elimination of drag due to deployed control surfaces and reduced radar vulnerability. A 60° delta wing model with a maximum span of 15.5 inches and a root chord of 13.5 inches was mounted in a subsonic wind tunnel. The wing is equipped with six control jets with variable azimuthal and pitch angles on the top surface approximately beneath the vortex core. A thorough optimization process was completed measuring static pressure to determine vortex breakdown location. Other variables in addition to azimuthal and pitch angles were injection momentum, frequency, and duty cycle. Measuring dynamic pressure, that is pressure fluctuation due to vortex shedding and pulsed injection, was also necessary to the development of a control algorithm. Dynamic pressure was measured at four chord-wise locations with uniform and randomly modulated duty cycles in order to ascertain duty cycle sensitivity on the systems overall effectiveness.
Ephraim Gutmark (Advisor)
129 p.
Engineering, Aerospace
Delta Wing; Flight Control; Flow Control; Vortex Breakdown

Recommended Citations

Citations

  • MAY, C. (2005). HIGH ANGLE OF ATTACK FLIGHT CONTROL OF DELTA WING AIRCRAFT USING VORTEX ACTUATORS [Master's thesis, University of Cincinnati]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109166873

    APA Style (7th edition)

  • MAY, CAMERON. HIGH ANGLE OF ATTACK FLIGHT CONTROL OF DELTA WING AIRCRAFT USING VORTEX ACTUATORS. 2005. University of Cincinnati, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109166873.

    MLA Style (8th edition)

  • MAY, CAMERON. "HIGH ANGLE OF ATTACK FLIGHT CONTROL OF DELTA WING AIRCRAFT USING VORTEX ACTUATORS." Master's thesis, University of Cincinnati, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109166873

    Chicago Manual of Style (17th edition)

ucin1109166873
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© 2005, all rights reserved.
This open access ETD is published by University of Cincinnati and OhioLINK.