Ignition and Combustion of Solid Propellants
Final technical rept.
UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING
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The response was studied of propellant ignition to externally supplied heat flux. Both radiant flux from electrically heated tube furnaces and convective flux from shock-heated gas were employed, the former giving fluxes in the range 5 to 50, the latter, 100 to 300 Btu per sec., sq. ft. The results, ignition delay time as a function of heat flux are correlated. The theory predicts the effect of initial propellant temperature on the ignition time-heat flux relationship, but is noncommittal with respect to the effect of pressure. The effect of pressure on the ignition delay time of perchlorate propellants is a function of heat flux level, being very slight, for the propellants studied, at flux levels above 20 Btu per sec., sq. ft. Exploratory studies concerned flame spread, effects of aerodynamic transients on burning propellant, and the diffusion flame between large bodies of fuel and oxidant. One firm conclusion is that flame spread across fresh surface, unassisted by external heat flux to that surface, is too slow to be an important factor in the over-all ignition process. As one aspect of the aerodynamic transient studies, a theory of the rarefaction tube was developed.
- Combustion and Ignition
- Solid Rocket Propellants