A Static combustion study on fuel rich propellant for ducted rocket gas generator

Abstract

In this paper, propellant composition was developed for ducted rocket gas generator and a series of static combustion tests were performed. In order to develop a propellant with high pressure exponent, Boron Beads was introduced. This Boron Beads was applied for propellant of ducted rocket gas generator. Static tests using 4 inch standard motor were conducted to evaluate combustion characteristic of the propellant. And then gas generator was designed and manufactured for the static test. Static tests was carried out with various exhaust parts of gas generator to find optimum shape to produce fuel-rich combustion gas. Finally, combustion gas flow controller was driven during static test to check combustion characteristics in different combustion chamber pressure. Fuel-rich combustion gas from gas generator was tested to check the feasibility of complete combustion in blast tube simulating the 2nd combustion chamber of ducted rocket. © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.