HOME

Science and Technology of Energetic Materials

Vol.64, No.2 (2003)

Research paper

Self-quenched combustion of fuel-rich AP/HTPB composite propellant
Makoto Kohga and Yutaka Hagihara
p.68-74

Abstract

In order to develop a solid propellant for gas hybrid rocket motor, it is required to investigate the burning characteristics of fuel - rich ammonium perchlorate(AP) based composite propellant. For fuel - rich composite propellant prepared with coarse AP and fine AP, the burning characteristics and the self - quenched combustion were investigated in this study. The following results were obtained : 1) The burning rate decreases as the AP content decreases, and the propellants contained less than a certain AP content self - quench. The self - quenched combustion occurs at a lower pressure and a higher pressure. 2) The lower limit of AP content to combust, Φmin exists. The Φmin of coarse AP is lower than that of fine AP. 3) It was found that the possibility of combustion for AP / HTPB composite propellant was dependent on the AP content, the particle size of AP, and the pressure. 4) The combustion of the propellant was self - quenched when AP particle did not expose on the burning surface. 5) The Φmin was directly independent on the heat generated on the burning surface and the burning rate. It could be considered that Φmin was greatly dependent on the particle size and the distances between two adjacent AP particles.

> Full text (Open access*)

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