Simulation of Two Moving Fronts Ablation in a Composite Thermal Protection System Via an Interface Tracking Method

摘要

In this work, the two-dimensional computational simulation of the ablative process in composites used in rocket thermal protection systems via an interface tracking method is presented. The ablative model considers the presence of two simultaneous moving fronts, the pyrolisis and char fronts. A complementary model, that considers temperature dependence for the reaction rate in the pyrolisis, is also tested. The results are compared with some experimental data, showing better agreement than the one-front model. Such procedure will allow a more accurate dimensioning of rocket thermal protection systems, contributing for project optimization.