Simulation of Ablationin a Sounding Rocket Thermal Protection System via an Interface Tracking Method with Two Moving Fronts


  • Humberto Araujo Machado Instituto de Aeronáutica e Espaço - IAE


TPS, Ablation, Moving boundary, Computational simulation, Sounding rocket


In this work, an interface tracking method is employed to simulate the ablative process in the region near the stagnation point of the VSB-30 sounding rocket Thermal Protection System (TPS). The ablation model considers the presence of two-fronts, the char-melting and the pyrolysis fronts. The results for the proposed model are compared to the ones obtained from the traditional one-front model, which supposes a constant ablation temperature. Results show that the one-front model overestimates the ablation period, mass loss and the internal temperature after the flight. The increase in the accuracy with this model shall provide a better dimensioning of the TPS, reducing its weight and cost.

Author Biography

Humberto Araujo Machado, Instituto de Aeronáutica e Espaço - IAE

Associate Researcher

Space Systems Division - ASE






Original Papers