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.


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    Titel :

    Propellant combustion response to oscillatory radiant heat flux


    Beteiligte:
    Strand, L. D. (Autor:in) / Schwartz, K. (Autor:in) / Burns, S. P. (Autor:in)


    Erscheinungsdatum :

    01.10.1987


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Solid propellant combustion response to oscillatory radiant heat flux

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    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