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

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 resul...

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Bibliographic Details
Published in:Journal of aerospace technology and management 2013-12, Vol.5 (4), p.409-420
Main Author: Machado, Humberto Araujo
Format: Article
Language:eng ; por
Subjects:
ENGINEERING, AEROSPACE
Online Access:Get full text
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Summary: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.
ISSN:2175-9146
2175-9146
DOI:10.5028/jatm.v5i4.262