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Hybrid propulsion technology program. Volume 1: Conceptional design packageA concept design study was performed to configure two sizes of hybrid boosters; one which duplicates the advanced shuttle rocket motor vacuum thrust time curve and a smaller, quarter thrust level booster. Two sizes of hybrid boosters were configured for either pump-fed or pressure-fed oxygen feed systems. Performance analyses show improved payload capability relative to a solid propellant booster. Size optimization and fuel safety considerations resulted in a 4.57 m (180 inch) diameter large booster with an inert hydrocarbon fuel. The preferred diameter for the quarter thrust level booster is 2.53 m (96 inches). As part of the design study critical technology issues were identified and a technology acquisition and demonstration plan was formulated.
Document ID
19900012477
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Jensen, Gordon E. (United Technologies Corp. San Jose, CA, United States)
Holzman, Allen L. (United Technologies Corp. San Jose, CA, United States)
Leisch, Steven O. (United Technologies Corp. San Jose, CA, United States)
Keilbach, Joseph (United Technologies Corp. San Jose, CA, United States)
Parsley, Randy (United Technologies Corp. San Jose, CA, United States)
Humphrey, John (United Technologies Corp. San Jose, CA, United States)
Date Acquired
September 6, 2013
Publication Date
October 15, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:183953
NASA-CR-183953
PROJ-2027-FR-VOL-1
Accession Number
90N21793
Funding Number(s)
CONTRACT_GRANT: NAS8-37778
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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