Numerical Analysis of Microscale Combustion Phenomena in Composite Solid Rocket Propellants

The characterization of composite solid rocket propellants (SRMs) is a critical aspect of their development and practical applications. Performance parameters, such as the burning rate and flame temperature during combustion, are influenced by environmental conditions, including pressure and temperature. Various chemical and physical processes occurring during combustion happen at different dimensions, with the microscopic dimension being essential for identifying these processes and their effects. At this scale, the composition of the propellant plays a vital role in its combustion behavior. The primary components of a composite propellant include an
oxidizer and a binder, along with additives such as curing agents, plasticizers, and bonding agents. These additives enhance the propellant's processability while exerting minimal influence on the combustion process. This combination results in a heterogeneous propellant, uniquely defined by the mass ratios and the shape and size of the oxidizer.