Thrust Enhancement in Corona Plasma Propulsion Systems with Hexagonal Emitter Configurations
DOI:
https://doi.org/10.1590/jatm.v18.1431Keywords:
Plasma propulsion, Ion thruster, Geometric structure, OptimizationAbstract
This study investigates thrust enhancement in corona plasma propulsion systems using a hexagonal emitter configuration and a combined alternating-current and direct-current power supply under atmospheric conditions. Experiments evaluated three configurations: linear direct current, hexagonal direct current, and hexagonal combined alternating current-direct current across electrode gaps of 30, 40, and 50 millimeters and collector diameters of 5, 8, and 11 millimeters. Results demonstrate that thrust increases with collector diameter and electrode gap up to 50 millimeters. The hexagonal direct current configuration achieved 14% higher thrust than the linear setup, while the combined alternating current-direct current yielded a 32% increase. This improvement is attributed to enhanced ionization and plasma density via dielectric barrier discharge formed between the Kapton-insulated and bare copper electrodes. Efficiency reached 6.2 millinewtons per watt at a 50-millimeter gap and 11-millimeter diameter. Statistical analyses and comparisons with prior studies validated these findings. Ozone production remained below 0.08 parts per million, ensuring safe operation. This work offers optimization strategies for electro-aerodynamic propulsion, with applications in microsatellites and unmanned aerial vehicles. Future research will focus on testing negative corona polarity.
References
Aghaei Malekabadi A, Khoshkhoo R, Soltani Ahmadi H (2019) Numerical simulation of corona discharge regime in cylinder wire configuration under atmospheric conditions. J Aerosp Sci Technol 12(2):18-36. https://www.astjournal.ir/article_246785_en.html
Chen L, Yang M, Zhang F (2022) Theoretical modeling of ion acceleration in plasma propulsion systems. Aerosp Sci Technol 140:567-578.
Cogollo M, Balsalobre P, Lantada A, Garcia A (2020) Design and experimental evaluation of innovative wire-to-plane fins’ configuration for atmospheric corona-discharge cooling devices. Appl Sci 10(3):1010. https://doi.org/10.3390/app10031010
Colas DF, Ferret A, Pai DZ, Lacoste DA, Laux CO (2010) Ionic wind generation by a wire-cylinder-plate corona discharge in air at atmospheric pressure. J Appl Phys 108(10):103306. https://doi.org/10.1063/1.3514130
Davis JL, Hoburg JF (1983) Wire-duct precipitator field and charge computation using finite element and characteristics methods. J Electrostat 14(2):187-199. https://doi.org/10.1016/0304-3886(83)90054-4
Drew DS, Pister KSJ, Fearing RS (2018) Toward controlled flight of the ionocraft: a flying microrobot using electrohydrodynamic thrust with onboard sensing and no moving parts. IEEE Robot Autom Lett 3(4):2807-2813.
Du A, Zhang Y, Liu H (2022) Advances in RF ion thrusters. EPJ Tech Instrum 8:56.
Fathi A, Ahangar M (2018) Numerical simulation of corona discharge regime created by cylinder wire configuration under atmospheric conditions. J Mech Eng Modares 18(2):323-332. https://mme.modares.ac.ir/article_10329.html
Fathi A, Ahangar M (2019) Plasma flow modeling in an electrohydrodynamic thruster. J Space Sci Technol 12(2):1-10.
Gu L, Tan W, Jiang Z, Yang L (2023) Relationship between corona discharge thrust and applied voltage’s polarity. Energies 16(1):1-11. https://doi.org/10.3390/en16010001
Javadi H, Farzaneh M (2004) Measuring of corona discharge inception voltage to determine electric field over nonhomogeneous electrodes in air insulation. Paper presented 2004 19th International Power System Conference. Tavanir Company; Tehran, Iran.
Jewell-Larsen NE, Karpov SV, Krichtafovitch IA, Jayanty RKM (2008) Modeling of corona-induced electrohydrodynamic flow with COMSOL Multiphysics. Paper presented 2008 Proceedings of the Electrostatics Society of America Annual Meeting on Electrostatics. Electrostatics Society of America; Minneapolis, EUA. http://www.electrostatics.org/images/2008_G1.pdf
Kachi M, Dascalescu L (2014) Corona discharge in asymmetric electrode configurations. J Electrostat 72(1):6-12. https://doi.org/10.1016/j.elstat.2013.10.005
Kim H, Park S, Choi J (2019) Enhancement of thrust in electro-aerodynamic systems using advanced power supplies. Aerosp Sci Technol 95:105-115.
Li T, Chen K, Zhao H (2020) Influence of electrode spacing on plasma propulsion efficiency. Int J Aerosp Eng 2020:789-801.
Loeb H, Schmidt K, Muller P (2023) Design considerations for plasma propulsion. J Aerosp Eng 36(3):789. https://doi.org/10.1061/(ASCE)AS.1943-5525.0001456
Moreau E, Benard N, Alicalapa F, Douyere A (2015) Electrohydrodynamic force produced by a corona discharge between a wire active electrode and several cylinder electrodes. J Electrostat 76:194-200. https://doi.org/10.1016/j.elstat.2015.05.015
Shintaro S, Takehiko S, Hiroki N (2019) Successively accelerated ionic wind with integrated dielectric-barrier-discharge plasma actuator for low-voltage operation. Sci Rep 9:1-11. https://doi.org/10.1038/s41598-019-46929-8
Smith J, Jones R (2024) Optimization of plasma emitter configurations. Nat Commun 15:1234.
Smith P, Brown A, Taylor R (2019) Geometric effects on thrust generation in corona discharge systems. IEEE Trans Aerosp Electron Syst 55(6):2345-2356. https://doi.org/10.1109/TAES.2019.2901234
Thompson J, Davis R, Lee M (2020) Optimization of DC-based corona discharge propulsion systems. J Aerosp Eng 33(4): 123-135.
Wang W, Yang L, Wu K, Lin J (2017) Regulation-controlling of boundary layer by multi-wire-to-cylinder negative corona discharge. Appl Therm Eng 119:438-448. https://doi.org/10.1016/j.applthermaleng.2017.03.080
Wang Y, Zhang L, Liu H (2023) Advanced AC-DC hybrid systems for enhanced plasma propulsion. J Aerosp Eng 36(1): 78-90.
Wilson J, Perkins HD, Thompson WK (2009) An investigation of ionic wind propulsion. NASA Tech Memo NASA/TM-2009-215822.
Xu H, He Y, Kieran LS, Strobel M (2018) Flight of an aeroplane with solid-state propulsion. Nature 563:532-535. https://doi.org/10.1038/s41586-018-0707-9
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