Test-Based Thermal Decomposition Simulation of AP/HTPB and AP/HTPE Propellants

Abstract

The ammonium perchlorate composite propellant is a common choice for solid rocket propulsion. The externally heated rocket via fires, for instance, can cause the energetic substance to ignite, and this may lead to a thermal runaway event or a slow cook-off phenomenon marked by a severe explosion. To develop preventive measures to reduce the possibility of such accidents in propulsion systems, we investigate the ignition and initiation characteristics of ammonium-perchlorate-based propellants andperform the thermal decomposition simulation of a thermally loaded solid rocket motor.