NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Hybrid rocket fuel combustion and regression rate studyThe objectives of this study are to develop hybrid fuels (1) with higher regression rates and reduced dependence on fuel grain geometry and (2) that maximize potential specific impulse using low-cost materials. A hybrid slab window motor system was developed to screen candidate fuels - their combustion behavior and regression rate. Combustion behavior diagnostics consisted of video and high speed motion pictures coverage. The mean fuel regression rates were determined by before and after measurements of the fuel slabs. The fuel for this initial investigation consisted of hydroxyl-terminated polybutadiene binder with coal and aluminum fillers. At low oxidizer flux levels (and corresponding fuel regression rates) the filled-binder fuels burn in a layered fashion, forming an aluminum containing binder/coal surface melt that, in turn, forms into filigrees or flakes that are stripped off by the crossflow. This melt process appears to diminish with increasing oxidizer flux level. Heat transfer by radiation is a significant contributor, producing the desired increase in magnitude and reduction in flow dependency (power law exponent) of the fuel regression rate.
Document ID
19920066267
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.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Anderson, F. A.
(JPL Pasadena, CA, United States)
Cohen, N. S.
(Cohen Professional Services Redlands, CA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 92-3302
Accession Number
92A48891
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available