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Experimental Study of Dielectric Barrier Discharge Driven Duct Flow for Propulsion Applications in Unmanned Aerial Systems
ISSN: 0148-7191, e-ISSN: 2688-3627
Published September 19, 2017 by SAE International in United States
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The dielectric barrier discharge (DBD) has been studied significantly in the past two decades for its applications to various aerodynamic problems. The most common aerodynamic applications have been stall/separation control and boundary layer modification. Recently several researchers have proposed utilizing the DBD in various configurations to act as viable propulsion systems for micro and nano aerial vehicles. The DBD produces stable atmospheric-pressure non-thermal plasma in a thin sheet with a preferred direction of flow. The plasma flow, driven by electrohydrodynamic body forces, entrains the quiescent air around it and thus develops into a low speed jet on the order of 10-1 to 101 m/s. Several researchers have utilized DBDs in an annular geometric setup as a propulsion device. Other researchers have used them to alter rectangular duct flows and directional jet devices. This study investigates 2-D duct flows for applications in micro plasma thrusters. The DBD actuators are located on the convergent intake section of the thruster which allows for variation of the effective flow entrainment angle for maximal thrust and a second set of actuators are located in the constant area portion of the duct. DBD operating parameters and thruster geometry were varied during experimentation to determine optimal conditions for maximized net thrust output. Flow measurements were collected via particle image velocimetry (PIV) and correlated to DBD operating parameters and thruster geometry.
CitationBrowning, P., Shambaugh, B., and Dygert, J., "Experimental Study of Dielectric Barrier Discharge Driven Duct Flow for Propulsion Applications in Unmanned Aerial Systems," SAE Technical Paper 2017-01-2063, 2017, https://doi.org/10.4271/2017-01-2063.
Data Sets - Support Documents
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- Shrestha, R., Tyata R. B., and Subedi D. P.. “Estimation of electron temperature in atmospheric pressure dielectric barrier discharge using line intensity ratio method.” Kathmandu University Journal of Science, Engineering and Technology 8, no. 2 (2013): 37-42.
- Ozturk, C. and Jacob, J., "Plasma Micro-Thrusters for Micro-Aerial Vehicles," SAE Technical Paper 2008-01-2244, 2008, doi:10.4271/2008-01-2244.
- Greig, A., Birzer C. H., and Arjomandi M.. “Atmospheric plasma thruster: Theory and concept.” AIAA journal 51, no. 2 (2012): 362-371.
- Khozikov, Vyacheslav, and Liu Shengyi. “Plasma actuating propulsion system for aerial vehicles.” U.S. Patent 8,944,370, issued February 3, 2015.
- Ginn, Kerry B., Jenkins Stewart A., Wells David M., and McCallum Brent N.. “Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators.” U.S. Patent 8,453,457, issued June 4, 2013.
- Speller, Kevin E. “Method and apparatus for vectoring thrust employing electrodes generating voltages greater than the dielectric breakdown voltage.” U.S. Patent 5,752,381, issued May 19, 1998.
- Defoort, E., Benard N., and Moreau E.. "Ionic wind produced by an electro-aerodynamic pump based on corona and dielectric barrier discharges." Journal of Electrostatics 88 (2017): 35-40.
- Gramer, Lew. “Kelvin-Helmholtz Instabilities.” GFD-II 2007.
- Abdollahzadeh, M., Rodrigues F., Pascoa J. C., and Oliveira P. J.. "Numerical design and analysis of a multi-DBD actuator configuration for the experimental testing of ACHEON nozzle model." Aerospace Science and Technology 41 (2015): 259-273.