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LOX/LH2 propulsion system for launch vehicle upper stage, test resultsThe test results of small LOX/LH2 engines for two propulsion systems, a pump fed system and a pressure fed system are reported. The pump fed system has the advantages of higher performances and higher mass fraction. The pressure fed system has the advantages of higher reliability and relative simplicity. Adoption of these cryogenic propulsion systems for upper stage of launch vehicle increases the payload capability with low cost. The 1,000 kg thrust class engine was selected for this cryogenic stage. A thrust chamber assembly for the pressure fed propulsion system was tested. It is indicated that it has good performance to meet system requirements.
Document ID
19850003781
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Ikeda, T. (NASA Headquarters Washington, DC United States)
Imachi, U. (NASA Headquarters Washington, DC United States)
Yuzawa, Y. (NASA Headquarters Washington, DC United States)
Kondo, Y. (NASA Headquarters Washington, DC United States)
Miyoshi, K. (NASA Headquarters Washington, DC United States)
Higashino, K. (NASA Headquarters Washington, DC United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1984
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-77727
NAS 1.15:77727
REPT-2
Accession Number
85N12089
Funding Number(s)
CONTRACT_GRANT: NASW-3541
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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