Wide Throttling, High Throughput Hall Thruster for Science and Exploration Missions

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX13CP02C
Agency Tracking Number: 115498
Amount: $699,996.00
Phase: Phase II
Program: SBIR
Awards Year: 2013
Solicitation Year: 2011
Solicitation Topic Code: S3.04
Solicitation Number: N/A
Small Business Information
11 Tech Circle, Natick, MA, 01760-1023
DUNS: 185739591
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Lawrence Byrne
 Principal Investigator
 (508) 655-5565
 larry@busek.com
Business Contact
 Judy Budny
Title: Business Official
Phone: (508) 655-5565
Email: judy@busek.com
Research Institution
N/A
Abstract
In response to Topic S3.04 "Propulsion Systems," Busek Co. Inc. will develop a high throughput Hall effect thruster with a nominal peak power of 1-kW and wide throttling range in terms of both power and Isp. In Phase I the preliminary thruster design was completed. Project activities focused on achieving a magnetic field that shields the discharge channel from ion induced erosion. The goal is to achieve a propellant throughput greater than 100 kg/kW. Numerical modeling is playing a critical role in the thruster design. In Phase I, we used a fluid based code developed by JPL to model the plasma in an existing thruster that is currently undergoing life testing. The erosion predictions of the model were found to agree well with actual measurements. The numerical model was then applied to the magnetically shielded 1-kW thruster and preliminary results were found to be reasonable. The goal is to demonstrate a thruster design where channel erosion is entirely eliminated as a life limiting mechanism. In Phase II, we will build and test the extended lifetime thruster. The performance, lifetime, and plume properties of the thruster will then be evaluated, and the design will be optimized. Numerical modeling will be used throughout the process to ensure that magnetic shielding is achieved. Code predictions will be grounded in plasma measurements taken with a variety of diagnostics including channel wall probes, high speed intrusive channel probes, and plume probes. The ability of the thruster to achieve its lifetime goals will be assessed through a 500 hour wear test. When the design is finalized, an engineering development unit (EDU) thruster will be designed, built, validated, and delivered to NASA. The EDU thruster design will be modeled thermally and structurally to facilitate the transition to Phase III. At the end of the Phase II, the TRL will be 5/6.

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

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