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Solid propellant combustion response to oscillatory radiant heat fluxA progress report is given on a research project to use the microwave Doppler velocimeter technique to measure the combustion response to an oscillating thermal radiation source (CO2 laser). The test technique and supporting analyses are described, and the results are presented for an initial test series on the nonmetallized, composite propellant, Naval Weapons Center formulation A-13. It is concluded that in-depth transmission of radiant heat flux is not a factor at the CO2 laser wave length.
Document ID
19890059629
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strand, L. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Weil, M. T.
(California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)
Cohen, N. S.
(Cohen Professional Services, Inc. Redlands, CA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 89-2667
Accession Number
89A47000
Distribution Limits
Public
Copyright
Other

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