Modeling of diffusion and premixed flame of AP/HTPB laminate propellant

Abstract

Composite propellants feature a diffusion flame. The size of oxidizer particles leverage some combustion properties (mainly, burning rate and pressure sensitivity) along with flame structure. Macroscopic combustion features are strictly related to those events occurring inside the gas phase and close to the burning surface. The flame of nonaluminized composite energetic materials is considered and a simplified combustion model is tested for this case. Combustion of a laminate propellant with varying lamina size is simulated. The benchmark consists of some movies taken from ammonium perchlorate (AP) / hydroxyl-terminated polybutadiene (HTPB) propellant combustion with a high-speed video camera. Three different powder sizes are used in propellant manufacturing.