Properties of Heterogeneous Solid Rocket Propellants Based on Poly(glycidyl azide) and Octogen

ABSTRACT This paper presents the manufacturing process and the results of investigations into the physicochemical properties of heterogeneous solid rocket propellants based on poly(glycidyl azide) (GAP) and hydroxyl‐terminated polybutadiene (HTPB) with the addition of octogen (HMX). The aim of the study was to determine the influence of the binder type and HMX particle size on the density, hardness, heat of combustion, and burning rate of the propellants. Twelve propellant formulations were produced, differing in binder type and the class of HMX used. The results demonstrated that GAP‐based propellants exhibit higher density, greater heat of combustion, and higher burning rates compared to HTPB‐based propellants. An increase in HMX content led to a decrease in the heat of combustion and burning rate, whereas the HMX particle size had no significant effect on density, hardness, or calorific value. The findings confirm that replacing HTPB with the energetic polymer GAP improves the energetic performance of solid rocket propellants.