20-kW Bismuth Hall Thruster with Evaporative Anode

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-04-M-3003
Agency Tracking Number: F041-198-2431
Amount: $99,725.00
Phase: Phase I
Program: SBIR
Awards Year: 2004
Solicitation Year: 2004
Solicitation Topic Code: AF04-198
Solicitation Number: 2004.1
Small Business Information
30981 Woodbush Road, Calumet, MI, 49913
DUNS: 003583429
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Satwik Deshmukh
 Research Engineer
 (906) 337-4024
 satwik_deshmukh@yahoo.com
Business Contact
 Lyon King
Title: President
Phone: (906) 487-2683
Email: lbking@mtu.edu
Research Institution
N/A
Abstract
High-power Hall thrusters operating at high thrust-to-power ratios will consume and emit unprecedented amounts of xenon propellant. The inherent costs associated with xenon use have significantly hindered development of such devices. Metallic propellants, specifically bismuth, have recently emerged as potentially higher-performing, lower-cost alternatives to xenon. When used in a Hall thruster, bismuth will likely enable improved thruster efficiency, which will translate to lower spacecraft inert mass. Furthermore, the use of bismuth will reduce mission propellant costs by a factor of 200 and may reduce the cost of developing high-power thrusters by a factor of 10. As bismuth is a solid at STP, an energy-efficient means of producing and controlling bismuth vapors is a prerequisite to Hall thruster use. In this document, a unique method of propellant vapor control is proposed and a plan-of-work is described to develop a 20-kW bismuth Hall thruster. The metal propellant will be maintained in a liquid state within the primary anode using waste heat dissipation within the thruster. The propellant supply rate will be controlled through a power-sharing shim electrode, which intercepts a fraction of the plasma discharge current, thereby regulating the liquid metal temperature within the primary anode and hence the evaporation rate.

* Information listed above is at the time of submission. *

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