Abstract
This work aims to optimize a previous self-consistent model of a single stage electrohydrodynamic (EHD) thruster for space applications. The investigated parameters were the thruster performance (propulsion force T, the thrust to power ratio T/P, the electric potential distribution, the spatial distribution for the electrons and ions, and the laminar flow velocity) under several conditions, such as the design features related to the cathode’s cylindrical geometry (height and radius) and some electric parameters such as the ballast resistor, and the applied potential voltage. In addition, we examined the influence of the secondary electron emission coefficient on the plasma propellant parameters. The anode to cathode potential voltage ranges between 0.9 and 40 kV, and the ballast resistance varies between 500 and 2500 M. Argon and xenon are the working gases. We assumed the gas temperature and pressure constant, 300 K and 1.3 kPa (10 Torr), respectively. The optimal matching for Xe brings off a thrust of 3.80 μN and an efficiency T/P = 434 mN/kW, while for Ar, T = 2.75 μN, and thruster to the power of 295 mN/kW. To our knowledge, the missing data in technical literature does not allow the verification and validation (V&V) of our numerical model.
Highlights
Electric Propulsion (EP) is an alternative type of rocket propulsion with higher efficiency at long operation maneuvering when compared to conventional chemical propulsion
The EHD thrust relies substantially on the flow pattern resulting from the electrode geometry and the electric potential morphology best suited for optimized performance
This paper aims to model and optimize the physics and geometric parameters of the EHD electrostatic propulsion devices for aerodynamic applications and is organized in the following parts: In Section 2, we briefly explain the model developed to analyze the behavior of an EHD thruster
Summary
Electric Propulsion (EP) is an alternative type of rocket propulsion with higher efficiency at long operation maneuvering when compared to conventional chemical propulsion. The electrohydrodynamic effect (EHD) is related to the possibility of generating or altering a gas flow, known as ionic wind, through the action of an electrical discharge, often a corona discharge. An EHD thruster, while working with partially ionized gas, is fuel-efficient, though at the expense of electrical power to sustain the plasma formation and ensuing gas acceleration. There are several theoretical, modulation, simulation, and experimental works that study the creation of an ionic wind resulting from the electrohydrodynamic force (EHD). The electrohydrodynamic force and the acceleration of the aerodynamic flow have been the subject of theoretical and modulation studies in dielectric barrier discharges plasma actuators and surfaces
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