Ignition and Unsteady Combustion of AP-Based Composite Propellants in SubscaleSolid Rocket Motors

摘要

The objective of this study is to develop a numerical tool able to predict theflow-solid propellant interaction responsible for the ignition process. The numerical package developed for the simulations comprises a multi-dimensional CFD code using a k-epsilon turbulence model which is associated with two main components: a one-dimensional unsteady heat conduction analytical solution for the propellant surface temperature or burning rate and a one-dimensional Couette flow solution for the wall boundary layer. In addition, one considers that a bidimensional combustion propagation occurs by conduction at the gas side propellant surface when the critical inflammation conditions to sustain such a propagation are satisfied. This paper presents the details of these modules created to simulate the ignition transient period and the applications conducted to predict the ignition delay and the flow field in selected subscale solid rocket motor configurations.