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Dual throat engine design for a SSTO launch vehicleA propulsion system analysis of a dual fuel, dual throat engine for launch vehicle application was conducted. Basic dual throat engine characterization data are presented to allow vehicle optimization studies to be conducted. A preliminary baseline engine system was defined. Dual throat engine performance, envelope, and weight parametric data were generated over the parametric range of thrust from 890 to 8896 KN (200K to 2M lb-force), chamber pressure from 6.89 million to 34.5 million N/sq m (1000 to 5000 psia) thrust ratio from 1.2 to 5, and a range of mixture ratios for the two tripropellant combinations: LO2/RP-1 + LH2 and LO2/LCH4 + LH2. The results of the study indicate that the dual fuel dual throat engine is a viable single stage to orbit candidate.
Document ID
19800021887
Document Type
Conference Paper
Authors
Obrien, C. J. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Salmon, J. W. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
August 10, 2013
Publication Date
March 1, 1980
Publication Information
Publication: APL The 1980 JANNAF Propulsion Meeting, Vol. 5
Subject Category
SPACECRAFT PROPULSION AND POWER
Funding Number(s)
CONTRACT_GRANT: NAS8-32967
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.