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The hard start phenomena in hypergolic engines. Volume 2: Combustion characteristics of propellants and propellant combinationsThe combustion characteristics of hypergolic propellants are described. A research project was conducted to determine if the reaction control system engine propellants on Apollo spacecraft undergo explosive reaction when subjected to conditions present in the engine at the time of ignition. Combustion characteristics pertinent to the hard-start phenomenon are considered. The thermal stability of frozen mixtures of hydrazine-based fuels with nitrogen tetroxide was analyzed. Results of the tests are presented in the form of tables and graphs.
Document ID
19740020121
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Miron, Y. (Bureau of Mines Pittsburgh, PA, United States)
Perlee, H. E. (Bureau of Mines Pittsburgh, PA, United States)
Date Acquired
September 3, 2013
Publication Date
March 22, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-134314
BM-IR-1646-VOL-2
Accession Number
74N28234
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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