Numerical Transient Burning Rate Model for Solid Rocket Motor Simulations

*The incorporation of time- and frequency-dependent effects on solid propellant burning behavior is important in the developing of more sophisticated solid rocket internal ballistic simulation models. A general numerical model based on the Zeldovich-Novozhilov solidphase energy conservation result for transient solid-propellant burning is presented in this study. A burning rate limiting function enables numerical stability at representative spatial and temporal increments, and with adjustment allows for an applicable alignment with observed experimental combustion response characteristics for a given propellant.