Rocket propellant combustion studies in a constant volume bomb

Abstract

A constant volume window bomb has been used to measure the characteristic velocity (c^∗ ) of rocket propellants. Analysis of the combustion process inside the bomb including heat losses has been made. The experiments on double base and composite propellants have revealed some (i) basic heat transfer aspects inside the bomb and (ii) combustion characteristics of Ammonium Perchlorate-Polyester propellants. It has been found that combustion continues even beyond the peak pressure and temperature points. Lithium Fluoride mixed propellants do not seem to indicate significant differences in c^∗ ) though the low pressure deflagration limit is increased with percentage of Lithium Fluoride.