The overall objective of the current research is to achieve a basic understanding of the erosive burning mechanism in solid-propellant rocket motors. Both theoretical and experimental studies are undertaken. In the theoretical modeling, a reactive turbulent boundary-layer approach is used to analyze the erosive burning phenomenon. A second-order turbulent closure has been selected in the theoretical formulation. The theoretical model can be used to study the effect of gas velocity, pressure, streamwise pressure gradient, oxidizer particle size, and oxidizer-to-fuel ration. For model validation, a test rig has been designed to establish a two-dimensional, turbulent boundary layer flow over a flat plate. The test rig can operate under various gas-dynamic conditions. A laser-photodiode servomechanism has been developed to measure the burning rate, and preliminary tests have demonstrated successful operation of the apparatus.


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    Title :

    Erosive burning studies of composite solid propellants by the reacting turbulent boundary-layer approach


    Additional title:

    Studie der erosiven Verbrennung von hybriden Festtreibstoffen mittels der turbulenten Grenzschichtmethode


    Contributors:
    Razdan, M.K. (author) / Kuo, K.K. (author)

    Published in:

    Publication date :

    1976


    Size :

    87 Seiten


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English