Thermal Induced Damage Evolution of GAP/AP/RDX/Al Composite Solid Propellant

In order to study the heat-induced damage evolution of GAP/AP/RDX/Al composite solid propellants under heating conditions, two GAP-based propellants with different RDX/AP Contents were prepared, and the thermal decomposition proper-ties of the samples were characterized by TG-DSC-IR technology. The samples were heated with a heating device, and the CT profile image, 3D pore distribution map, porosity and pore size distribution of the two propellant samples were obtained under different heating temperatures (50—130°C), heating times (5—35min) and heating areas (25%, 50% and 87. 5% surface area) through micro-CT imaging and three-dimensional reconstruction of scanning images. The results show that the pores in the initial sample of GAP propellant are mainly the initial pores inside solid particles such as AP and RDX, and the thermal damage pores are mainly the interface dewedding pores between solid particles and the adhesive matrix, the pores generated after the matrix decomposition, and the initial structural defects. The pore damage size of GAP propellant after heating at 130 C increases significantly compared with the initial sample, and the higher the RDX content, the greater the damage degree of the sample after thermal Stimulation. © 2024 China Ordnance Industry Corporation. All rights reserved.