Ignition of Small Rocket Motor Using Black Powder Igniters

Abstract

This article examines an optimal amount of igniter propellant for infallible ignition of solid rocket motor propellant grain. Based on the experiment, the aim is to identify a successful ignition transient of solid rocket motor grain with as little igniter propellant as possible and pressure time history of igniter using black powder by using inert grain. Applying an exploratory approach, comparative case studies are used as a primary research method and pressure-time histories are analyzed. Findings reveal that optimal amount of igniter propellant to ignite solid rocket motor grain tempered on temperature 20 °C and –40 °C recumbent between 2.5 g and 5 g black powder Vesuvit© type Vr and between 5 g and 10 g black powder Vesuvit© type T 1/2. Obtaining experimental pressure-time histories in solid rocket motor chamber are identified as a crucial source for comparison real and simulating pressure-time histories and for finding the optimal amount of igniter propellant in theoretical calculations.