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.
Heat-transfer processes during ignition of solid propellant rockets
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 1
1967
6 pages
Article (Journal)
English
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Ignition Problems in Solid-Propellant Rockets
NTRS | 1968
|NTIS | 1968
|Engineering Index Backfile | 1955
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