Abstract
AbstractSuitability of a number of metal based igniter compositions have been studied for magnesium based fuel rich propellant. Igniter compositions have been tested in closed vessel for evaluation of ignition pressure output and impetus. Heat energy values were determined calorimetrically in a closed bomb. Vented vessel study was carried out in a test motor for assessing relative behaviour and to select a suitable composition. Compositions containing magnesium powder and potassium nitrate were found to give satisfactory ignition to the propellant.
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