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Satellite Propellant Pump ResearchNASA Glenn initiated a satellite propellant pump technology demonstration program. The goal was to demonstrate the technologies for a 60 percent efficient pump at 1 gpm flow rate and 500 psia pressure rise. The pump design and analysis used the in-house developed computer codes named PUMPA and HPUMP3D. The requirements lead to a 4-stage impeller type pump design with a tip diameter of 0.54 inches and a rotational speed of 57,000 rpm. Analyses indicated that flow cavitation was not a problem in the design. Since the flow was incompressible, the stages were identical. Only the 2-stage pump was designed, fabricated, assembled, and tested for demonstration. Water was selected as the surrogate fluid for hydrazine in this program. Complete mechanical design including stress and dynamic analyses were conducted. The pump was driven by an electric motor directly coupled to the impellers. Runs up to 57,000 rpm were conducted, where a pressure rise of 200 psia at a flow rate of 0.8 gpm was measured to validate the design effort.
Document ID
20060000023
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Schneider, Steven J. (NASA Glenn Research Center Cleveland, OH, United States)
Veres, Joseph P. (NASA Glenn Research Center Cleveland, OH, United States)
Hah, Chunill (NASA Glenn Research Center Cleveland, OH, United States)
Nerone, Anthony L. (NASA Glenn Research Center Cleveland, OH, United States)
Cunningham, Cameron C. (NASA Glenn Research Center Cleveland, OH, United States)
Kraft, Thomas G. (NASA Glenn Research Center Cleveland, OH, United States)
Tavernelli, Paul F. (NASA Glenn Research Center Cleveland, OH, United States)
Fraser, Bryan (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2005
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 2005-3560
NASA/TM-2005-214025
E-15379
Meeting Information
Meeting: 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Tucson, AZ
Country: United States
Start Date: July 10, 2005
End Date: July 13, 2005
Sponsors: American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Society for Electrical Engineers
Funding Number(s)
WBS: WBS 22-612-50-81-17
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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