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Hybrid fuel formulation and technology developmentThe objective was to develop an improved hybrid fuel with higher regression rate, a regression rate expression exponent close to 0.5, lower cost, and higher density. The approach was to formulate candidate fuels based on promising concepts, perform thermomechanical analyses to select the most promising candidates, develop laboratory processes to fabricate fuel grains as needed, fabricate fuel grains and test in a small lab-scale motor, select the best candidate, and then scale up and validate performance in a 2500 lbf scale, 11-inch diameter motor. The characteristics of a high performance fuel have been verified in 11-inch motor testing. The advanced fuel exhibits a 15% increase in density over an all hydrocarbon formulation accompanied by a 50% increase in regression rate, which when multiplied by the increase in density yields a 70% increase in fuel mass flow rate; has a significantly lower oxidizer-to-fuel (O/F) ratio requirement at 1.5; has a significantly decreased axial regression rate variation making for more uniform propellant flow throughout motor operation; is very clean burning; extinguishes cleanly and quickly; and burns with a high combustion efficiency.
Document ID
19960001302
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dean, D. L.
(McDonnell-Douglas Aerospace Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1995
Subject Category
Propellants And Fuels
Report/Patent Number
MDC-95W5102
NASA-CR-199184
NAS 1.26:199184
Report Number: MDC-95W5102
Report Number: NASA-CR-199184
Report Number: NAS 1.26:199184
Accession Number
96N11309
Funding Number(s)
CONTRACT_GRANT: NAS8-39944
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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