HOME

Science and Technology of Energetic Materials

Vol.64, No.3 (2003)

Research paper

Burning characteristics of fuel-rich AP/HTPB composite propellant added with iron oxide
Makoto Kohga and Yutaka Hagihara
p.110-115

Abstract

Hybrid rocket motor has been developing for a rocket motor of the next generation. It is necessary to investigate the burning characteristics of fuel-rich AP/HTPB composite propellant in order to develop a solid fuel for hybrid rocket motor. Iron oxide is used as a positive catalyst for the AP/HTPB composite propellant. The burning characteristics of fuel-rich AP/HTPB composite propellant added with iron oxide were investigated in this study. From this study the following conclusions were obtained: 1) The burning rate decreases as the AP content decreases, and the propellants self-quench less than a certain AP content. The self-quenched combustion occurs at a lower pressure and a higher pressure. 2) The possibility of combustion for fuel-rich AP/HTPB composite propellant added with iron oxide is dependent on the AP content, the particle size of AP and the pressure. 3) The lower limit of AP content to combust is decreased by the addition of iron oxide. 4) The effect of the addition of iron oxide on the decrease in the lower limit of AP content to combust becomes greater as the size of AP particle decreases. 5) The effect of iron oxide on the increase in the burning rate is dependent on the AP content and the size of AP particle.

> Full text (Open access*)

© Copyright 1999-2017 Japan Explosives Society. All right reserved.