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

Authors

  • Humberto Araujo Machado Instituto de Aeronáutica e Espaço - IAE

Keywords:

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

Abstract

http://dx.doi.org/10.5028/jatm.v5i4.262

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

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Published

2013-11-23

Issue

Vol. 5 No. 4 (2013): Oct. /Dec., 2013

Section

Original Papers

License

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