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Design of a high density cold gas attitude control systemA comparison of the experimental results of a nitrous oxide cold gas thruster with the predicted performance from a numerical simulation of nozzle operations is discussed. Tests were conducted in a vacuum chamber to verify analytical predictions of both nitrogen and nitrous oxide. Preliminary results indicate an Isp for N2O of 61, and an Isp of 69 for N2. Based on the results of this research, parameters are presented for a nitrous oxide-based reaction control system for a small spacecraft currently under development.
Document ID
19930066300
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hall, Sarah E. (NASA Headquarters Washington, DC United States)
Lewis, Mark J. (NASA Headquarters Washington, DC United States)
Akin, David L. (Maryland Univ. College Park, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2583
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: SAE, AIAA, ASME, ASEE
Accession Number
93A50297
Funding Number(s)
CONTRACT_GRANT: NAGW-2245
Distribution Limits
Public
Copyright
Other

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