Electrostatic propulsion device for aerodynamics applications

A self-consistent model of single-stage electrohydrodynamic thrusters is proposed in order to compare and study their performances in terms of net thrust production and thrust-to-power efficiency. Simulations of three thruster's cathode configurations (conical, cylindrical, and funnel-like) at...

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Bibliographic Details
Published in:Physics of plasmas 2016-07, Vol.23 (7)
Main Authors: Granados, Victor H., Pinheiro, Mario J., Sá, Paulo A.
Format: Article
Language:English
Subjects:
Cathodes
Computer simulation
Configurations
Electrohydrodynamics
Electrostatic propulsion
Nitrogen
Plasma physics
Power efficiency
Thrust
Thrusters
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Summary:A self-consistent model of single-stage electrohydrodynamic thrusters is proposed in order to compare and study their performances in terms of net thrust production and thrust-to-power efficiency. Simulations of three thruster's cathode configurations (conical, cylindrical, and funnel-like) at a working pressure of ≃ 66.7  Pa (0.5 Torr) were conducted. Three working gases were employed: argon (Ar, Ar*, and Ar+), nitrogen (N, N+, N 2 ,   N 2 + , and N 4 + ), and oxygen (O, O+, O − ,   O 2 ,   O 2 + , and O 2 − ). We found the funnel-like cathode configuration to produce the highest amount of thrust comparing with the other studied cathode geometries. Additionally, nitrogen gas presented the highest net thrust of 5.2 nN with a thrust-to-power ratio of 0.94 μN/W. Although the thrust obtained for oxygen is more than one order of magnitude lower than nitrogen's, the thrust-to-power ratio obtained is more than three times greater.
ISSN:1070-664X
1089-7674
DOI:10.1063/1.4958815