Light Metal Propellant Hall Thruster

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX09CE07P
Agency Tracking Number: 085135
Amount: $99,991.00
Phase: Phase I
Program: SBIR
Awards Year: 2009
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Busek Co., Inc.
11 Tech Circle, Natick, MA, 01760
DUNS: 185739591
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 James Szabo
 Principal Investigator
 (508) 655-5565
 jszabo@busek.com
Business Contact
 Judy Budny
Title: Business Official
Phone: (508) 655-5565
Email: judy@busek.com
Research Institution
N/A
Abstract
Busek proposes to develop light metal Hall Effect thrusters that will help reduce the travel time, mass, and cost of SMD spacecraft. Busek has identified three attractive light metal propellants: magnesium (Mg), zinc (Zn), and a eutectic (Mg/Zn). These metals are plentiful and practical alternatives to Xe and Kr, which are expensive and scarce, and Bi, which is overly condensable and requires a high voltage power processing unit (PPU) to reach velocities of interest. Because Mg and Zn are lightweight, specific impulse > 3000 s will be available with a near term, low voltage PPU, decreasing propellant mass and program and hardware costs. Both metals have favorable ionization properties, implying high efficiencies are possible. Mg can also be combusted with water in a rocket, enabling a multi-mode propulsion system where the Hall thruster and rocket share propellant. The availability of a high thrust impulsive mode can greatly decrease delta V and trip times for SMD spacecraft. These light metals are non-toxic and solid at room temperature. They can be stored and fed to a thruster as a wire. For Zn and Mg/Zn, liquid distribution is also feasible. Life testing will be low cost because the light metals are inexpensive and self pumping; they will condense on the vacuum chamber wall. Vapor pressure curves suggest minimal spacecraft interactions. In-situ propellant production is also possible. Mg, for example, can be extracted from Martian regolith using solar energy. The key innovation in this proposal is the use of light metals to fuel a Hall thruster. In Phase I, Busek will design and demonstrate a wire based light metal feed system that will be integrated with an existing 1-2 kW bismuth vapor Hall Effect thruster. Busek will then demonstrate a Mg, Zn, or Mg/Zn discharge and measure its operating parameters. Finally, Busek will lay out a dedicated thruster and feed system to be built and tested in Phase II.

* information listed above is at the time of submission.

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