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Electrostatic Plasma Accelerator (EPA)The Electrostatic Plasma Accelerator (EPA) is a thruster concept which promises specific impulse levels between low power arcjets and those of the ion engine while retaining the relative simplicity of the arcjet. The EPA thruster produces thrust through the electrostatic acceleration of a moderately dense plasma. No accelerating electrodes are used and the specific impulse is a direct function of the applied discharge voltage and the propellant atomic mass. The goal of the present program is to demonstrate feasibility of the EPA thruster concept through experimental and theoretical investigations of the EPA acceleration mechanism and discharge chamber performance. Experimental investigations will include operating the test bed ion (TBI) engine as an EPA thruster and parametrically varying the thruster geometry and operating conditions to quantify the electrostatic plasma acceleration effect. The theoretical investigations will include the development of a discharge chamber model which describes the relationships between the engine size, plasma properties, and overall performance. For the EPA thruster to be a viable propulsion concept, overall thruster efficiencies approaching 30% with specific impulses approaching 1000 s must be achieved.
Document ID
19960022968
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Brophy, John R.
(Electric Propulsion Lab., Inc. Lancaster, CA United States)
Aston, Graeme
(Electric Propulsion Lab., Inc. Lancaster, CA United States)
Date Acquired
August 17, 2013
Publication Date
October 26, 1989
Publication Information
Publication: Overview of the Center for Advanced Space Propulsion
Subject Category
Plasma Physics
Accession Number
96N71339
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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