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Hybrid rocket combustion studyThe objectives of this study of 'pure' or 'classic' hybrids are to (1) extend our understanding of the boundary layer combustion process and the critical engineering parameters that define this process, (2) develop an up-to-date hybrid fuel combustion model, and (3) apply the model to correlate the regression rate and scaling properties of potential fuel candidates. Tests were carried out with a hybrid slab window motor, using several diagnostic techniques, over a range of motor pressure and oxidizer mass flux conditions. The results basically confirmed turbulent boundary layer heat and mass transfer as the rate limiting process for hybrid fuel decomposition and combustion. The measured fuel regression rates showed good agreement with the analytical model predictions. The results of model scaling calculations to Shuttle SRM size conditions are presented.
Document ID
19930066176
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strand, L. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Ray, R. L.
(JPL Pasadena, CA, United States)
Cohen, N. S.
(Cohen Professional Services Redlands, CA, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2412
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
93A50173
Distribution Limits
Public
Copyright
Other

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