Modeling and Numerical Simulation of Combustion Process inside a solid‐propellant crack

Abstract

AbstractTransient combustion processes inside a solid‐propellant crack cavity have been formulated and solved numerically, with emphasis placed on the coupling between combustion dynamics and propellant grain deformation and fracture. Sample calculations were performed for a center‐perforated propellant grain with an existing crack. Parametric study investigating the effect of several physical properties on the initiation of fracture was also carried out. Numerical results indicated that the existence of cracks in a propellant grain may impose a safety issue for a rocket motor due to the creation of large free volume and extra burning surface area. Comparison of calculated results of this analysis and those which do not consider propellant deformation and fracture revealed that the coupling between combustion and structural analyses is mandatory for accurate simulation of crack combustion event. It was also found that, from the parametric study, fracture initiation is very sensitive to the magnitude of pressure exponent of the propellant burning rate.