An introductory 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 (laser). The objective is to relate the measured burning rate response to the thermal radiation to an equivalent oscillation in pressure using existing thermal combustion theory. The test system is described, and the results of an initial test series on the composite propellant A-13 are presented.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Propellant combustion response to oscillatory radiant heat flux


    Contributors:
    Strand, L. D. (author) / Schwartz, K. (author) / Burns, S. P. (author)


    Publication date :

    1987-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Solid propellant combustion response to oscillatory radiant heat flux

    Strand, L. D. / Weil, M. T. / Cohen, N. S. | NTRS | 1989


    Solid propellant combustion response to oscillatory radiant heat flux

    STRAND, L. / WEIL, M. / COHEN, N. | AIAA | 1989


    Measurement of propellant combustion response to sinusoidal radiant heat flux

    FINLINSON, J. / HANSON-PARR, D. / SON, S. et al. | AIAA | 1991


    Measuring Response Of Propellant To Oscillatory Heat Flux

    Strand, Leon D. / Schwartz, Ken / Burns, Shawn P. | NTRS | 1990