Abstract
A method, which measures the temperature of solid rocket motor exhaust plume, was developed by employing an improved sodium line reversal process. The formula for calculating the temperature was improved and simplified. The temporal temperature-time distributions of the exhaust plume of double base propellant rocket motors were given by the established method. The maximum time resolution and accuracy for the temperature measurement are 40 μs and 8%, respectively. This kind of temperature measurement does not disturb the combustion flow field of exhaust plume and is simpler and more sensitive. The maximum temperatures of SQ-2 propellant exhaust plumes are 2234 K and 2202 K for 240 mm and 500 mm apart from the motor nozzle, respectively. More combustion phenomena of the exhaust plume can be measured by using an existing instrument.
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