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Low-Mass, Low-Power Hall Thruster SystemNASA is developing an electric propulsion system capable of producing 20 mN thrust with input power up to 1,000 W and specific impulse ranging from 1,600 to 3,500 seconds. The key technical challenge is the target mass of 1 kg for the thruster and 2 kg for the power processing unit (PPU). In Phase I, Busek Company, Inc., developed an overall subsystem design for the thruster/cathode, PPU, and xenon feed system. This project demonstrated the feasibility of a low-mass power processing architecture that replaces four of the DC-DC converters of a typical PPU with a single multifunctional converter and a low-mass Hall thruster design employing permanent magnets. In Phase II, the team developed an engineering prototype model of its low-mass BHT-600 Hall thruster system, with the primary focus on the low-mass PPU and thruster. The goal was to develop an electric propulsion thruster with the appropriate specific impulse and propellant throughput to enable radioisotope electric propulsion (REP). This is important because REP offers the benefits of nuclear electric propulsion without the need for an excessively large spacecraft and power system.
Document ID
20160005342
Acquisition Source
Glenn Research Center
Document Type
Other
Authors
Pote, Bruce (Busek (J.) Co., Inc. Natick, MA, United States)
Date Acquired
April 26, 2016
Publication Date
July 1, 2015
Publication Information
Publication: An Overview of SBIR Phase 2 In-Space Propulsion and Cryogenic Fluids Management
Subject Category
Spacecraft Propulsion And Power
Energy Production And Conversion
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle20150015569Collected WorksAn Overview of SBIR Phase 2 In-Space Propulsion and Cryogenic Fluids Management
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