Iodine Hall Thruster Propellant Feed System for a CubeSat
- Author:
- Peeples, Steven
- Published:
- July 28, 2014.
- Physical Description:
- 1 electronic document
- Additional Creators:
- Polzin, Kurt A.
Online Version
- hdl.handle.net , Connect to this object online.
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary:
- The components required for an in-space iodine vapor-fed Hall effect thruster propellant management system are described. A laboratory apparatus was assembled and used to produce iodine vapor and control the flow through the application of heating to the propellant reservoir and through the adjustment of the opening in a proportional flow control valve. Changing of the reservoir temperature altered the flowrate on the timescale of minutes while adjustment of the proportional flow control valve changed the flowrate immediately without an overshoot or undershoot in flowrate with the requisite recovery time associated with thermal control systems. The flowrates tested spanned a range from 0-1.5 mg/s of iodine, which is sufficient to feed a 200-W Hall effect thruster.
- Other Subject(s):
- Collection:
- NASA Technical Reports Server (NTRS) Collection.
- Note:
- Document ID: 20140012577.
M14-3863.
AIAA/ASME/SAE/ASEE Joint Propulsion Conference; 28-30 Jul. 2014; Cleveland, OH; United States. - Terms of Use and Reproduction:
- No Copyright.
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