AbstractResults of experiments performed with an advanced, automated measuring system and dealing with combusion of polymethylmethacrylate and polyethylene with oxygen and different mixtures of oxygen and nitrogen are reported.Factors affecting the regression rate of the fuel are the mass flux, the geometry, the pressure level and the presence of oscillations, the composition of the oxidizer and the burning time. The effect of pressure on the regression rate appears to be stronger at lower pressures. A newly developed technique allows the measurement of the local instantaneous regression rate. The dependence of this regression rate on the various above mentioned parameters varies from location to location in the motor. The characteristic velocity depends on the mixture ratio and on the residence time of the reacting gases. A rearward facing step increases the mean regression rate and changes the profile of the burned fuel grain. Such a step is necessary to obtain combustion with mixtures containing 20% oxygen and 80% nitrogen.


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    Title :

    Advanced hybrid rocket motor experiments


    Contributors:

    Published in:

    Acta Astronautica ; 15 , 2 ; 97-104


    Publication date :

    1986-05-26


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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