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Cryogenic Flow Control Components For Rocket Propulsion SystemsThe design of cryogenic flow control components, specifically the prevalve, for the Saturn 5 vehicle is discussed. Design systems are assessed and component requirements revealed significant improvements in mass flow rate, temperature, and pressure.
Document ID
19730004123
Acquisition Source
Marshall Space Flight Center
Document Type
Contribution to a larger work
Authors
J H Potter (Marshall Space Flight Center Redstone Arsenal, United States)
Date Acquired
August 7, 2013
Publication Date
August 1, 1972
Publication Information
Publication: Research Achievements Review, Chemical Propulsion Research
Publisher: Marshall Space Flight Center
Volume: 4
Issue: 6
Subject Category
Propellants and Fuels
Report/Patent Number
NASA/TM-19730004113
NASA-TM-X-64690
Accession Number
73N12850
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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IDRelationTitle19730004113Collected WorksResearch Achievements Review, Volume 4, No. 6: Chemical Propulsion Research at MSFC19730004113Collected WorksResearch Achievements Review, Volume 4, No. 6: Chemical Propulsion Research at MSFC
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