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Two-step rocket engine bipropellant valve conceptInitiating combustion of altitude control rocket engines in a precombustion chamber of ductile material reduces high pressure surges generated by hypergolic propellants. Two-step bipropellant valve concepts control initial propellant flow into precombustion chamber and subsequent full flow into main chamber.
Document ID
19690000280
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Capps, J. E.
Ferguson, R. E.
Pohl, H. O.
Date Acquired
August 5, 2013
Publication Date
August 1, 1969
Subject Category
Mechanics
Report/Patent Number
MSC-10951
Accession Number
69B10280
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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