Temperature Sensitivity of the Burning Rate of Composite Solid Propellants

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Abstract
This paper presents the results of an experimental program designed to determine the burning-rate temperature sensitivity of various ammonium perchlorate (A.P.) based propellants in the temperature range from 0 to 140°C The effect of aluminum, copper chromite, and lithium fluoride on the thermal-sensitivity coefficient ( β ≡ ∂ In vb / ∂ To) was also investgated. The results, which are generally well represented by the empirical law vb ≡ vb ∗ exp [β (To-T∗ )] indicate, that the aluminized propellants have a tower value of β and that the presence of additives in the propellants tends to decrease this coefficient still more. Scanning electron microscope observations of the burning surface after the quenching of the combustion, seem to reveal the influence of the difference between the thermal stabilites of the oxidizer (A.P.) and the binder (poly-butadiene, polyumhae).

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