In theoretical model, radiative and convective heat transfer are considered; radiative mode includes gas phase and condensed phase emanations; convective transfer is treated by means of simple film model in which driving force is ratio of enthalpy of combustion products to their frozen heat capacity; models are used as basis for correlating results of experiments with typical igniters fired in simulated motor chambers; results of tests that include variations in location of sensors in propellant port, igniter composition, flow rate, and port diameter are presented; correlation of experimental data with theoretical model.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Heat-transfer processes during ignition of solid propellant rockets


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Allan, D.S. (author) / Bastress, E.K. (author) / Smith, K.A. (author)

    Published in:

    Publication date :

    1967


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




    Ignition Problems in Solid-Propellant Rockets

    B E Paul / R L Lovine | NTRS | 1968


    Solid Propellant Rockets

    J. De Montravel | NTIS | 1968


    Solid propellant rockets

    Zaehringer, A.J. | Engineering Index Backfile | 1955