Optimization of a coaxial electron cyclotron resonance plasma thruster with an analytical model
Abstract
A new cathodeless plasma thruster currently under development at Onera is presented and characterized experimentally and analytically. The coaxial thruster consists of a microwave antenna immersed in a magnetic field, which allows electron heating via cyclotron resonance. The magnetic field diverges at the thruster exit and forms a nozzle that accelerates the quasineutral plasma to generate a thrust. Different thruster configurations are tested, and in particular, the influence of the source diameter on the thruster performance is investigated. At microwave powers of about 30 W and a xenon flow rate of 0.1 mg/s (1 SCCM), a mass utilization of 60% and a thrust of 1 mN are estimated based on angular electrostatic probe measurements performed downstream of the thruster in the exhaust plume. Results are found to be in fair agreement with a recent analytical helicon thruster model that has been adapted for the coaxial geometry used here.
 Authors:
 Physics and Instrumentation Department, Onera The French Aerospace Lab, Palaiseau, Cedex 91123 (France)
 (France)
 Laboratoire de Physique des Plasmas, CNRS, Sorbonne Universites, UPMC Univ Paris 06, Univ ParisSud, Ecole Polytechnique, 91128 Palaiseau (France)
 Publication Date:
 OSTI Identifier:
 22410347
 Resource Type:
 Journal Article
 Resource Relation:
 Journal Name: Physics of Plasmas; Journal Volume: 22; Journal Issue: 5; Other Information: (c) 2015 AIP Publishing LLC; Country of input: International Atomic Energy Agency (IAEA)
 Country of Publication:
 United States
 Language:
 English
 Subject:
 70 PLASMA PHYSICS AND FUSION TECHNOLOGY; ANTENNAS; CONFIGURATION; ELECTRON CYCLOTRONRESONANCE; ELECTRONS; ELECTROSTATIC PROBES; FLOW RATE; HEATING; MAGNETIC FIELDS; MICROWAVE RADIATION; NOZZLES; PLASMA; THRUSTERS; XENON
Citation Formats
Cannat, F., Email: felix.cannat@onera.fr, Email: felix.cannat@gmail.com, Lafleur, T., Laboratoire de Physique des Plasmas, CNRS, Sorbonne Universites, UPMC Univ Paris 06, Univ ParisSud, Ecole Polytechnique, 91128 Palaiseau, Jarrige, J., Elias, P.Q., Packan, D., and Chabert, P. Optimization of a coaxial electron cyclotron resonance plasma thruster with an analytical model. United States: N. p., 2015.
Web. doi:10.1063/1.4920966.
Cannat, F., Email: felix.cannat@onera.fr, Email: felix.cannat@gmail.com, Lafleur, T., Laboratoire de Physique des Plasmas, CNRS, Sorbonne Universites, UPMC Univ Paris 06, Univ ParisSud, Ecole Polytechnique, 91128 Palaiseau, Jarrige, J., Elias, P.Q., Packan, D., & Chabert, P. Optimization of a coaxial electron cyclotron resonance plasma thruster with an analytical model. United States. doi:10.1063/1.4920966.
Cannat, F., Email: felix.cannat@onera.fr, Email: felix.cannat@gmail.com, Lafleur, T., Laboratoire de Physique des Plasmas, CNRS, Sorbonne Universites, UPMC Univ Paris 06, Univ ParisSud, Ecole Polytechnique, 91128 Palaiseau, Jarrige, J., Elias, P.Q., Packan, D., and Chabert, P. 2015.
"Optimization of a coaxial electron cyclotron resonance plasma thruster with an analytical model". United States.
doi:10.1063/1.4920966.
@article{osti_22410347,
title = {Optimization of a coaxial electron cyclotron resonance plasma thruster with an analytical model},
author = {Cannat, F., Email: felix.cannat@onera.fr, Email: felix.cannat@gmail.com and Lafleur, T. and Laboratoire de Physique des Plasmas, CNRS, Sorbonne Universites, UPMC Univ Paris 06, Univ ParisSud, Ecole Polytechnique, 91128 Palaiseau and Jarrige, J. and Elias, P.Q. and Packan, D. and Chabert, P.},
abstractNote = {A new cathodeless plasma thruster currently under development at Onera is presented and characterized experimentally and analytically. The coaxial thruster consists of a microwave antenna immersed in a magnetic field, which allows electron heating via cyclotron resonance. The magnetic field diverges at the thruster exit and forms a nozzle that accelerates the quasineutral plasma to generate a thrust. Different thruster configurations are tested, and in particular, the influence of the source diameter on the thruster performance is investigated. At microwave powers of about 30 W and a xenon flow rate of 0.1 mg/s (1 SCCM), a mass utilization of 60% and a thrust of 1 mN are estimated based on angular electrostatic probe measurements performed downstream of the thruster in the exhaust plume. Results are found to be in fair agreement with a recent analytical helicon thruster model that has been adapted for the coaxial geometry used here.},
doi = {10.1063/1.4920966},
journal = {Physics of Plasmas},
number = 5,
volume = 22,
place = {United States},
year = 2015,
month = 5
}

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