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Advances in Aircraft and Spacecraft Science
  Volume 8, Number 3, May 2021 , pages 251-271
DOI: https://doi.org/10.12989/aas.2021.8.3.251
 

Computational ablative thermal response analysis of carbon/phenolic composites for thermal protection system
Taehoon Park, Kang-Hyun Lee and Gun Jin Yun

 
Abstract
    This study presents an efficient computational methodology to perform ablative thermal response analysis of carbon/phenolic composites by introducing a novel dual-domain technique for heat transfer and gas diffusion physics. Phenomena such as in-depth heat transfer, material decomposition (i.e. pyrolysis), in-depth gas diffusion, and surface recession required for ablation analysis of carbon/phenolic composites are simulated. The proposed method is verified with reference simulation test data from Ablation Workshop for a one-dimensional model under four different combinations with surface heat flux, temperature, pressure boundary conditions, and surface recession conditions verified. A two-dimensional ablation problem was also solved, showing its scalability. Temperatures, recession depth, depth of boundaries between layers, the mass flux of char, and pyrolysis gas are obtained and compared with the reference for all cases.
 
Key Words
    charring ablation; carbon/phenolic composite; finite element analysis; thermal protection system
 
Address
Taehoon Park and Kang-Hyun Lee: Department of Aerospace Engineering, Seoul National University, Gwanak-gu Gwanak-ro 1 Seoul 08826, South Korea

Gun Jin Yun: 1.) Department of Aerospace Engineering, Seoul National University, Gwanak-gu Gwanak-ro 1 Seoul 08826, South Korea
2.) Institute of Advanced Aerospace Technology, Seoul National University, Gwanak-gu Gwanak-ro 1, Seoul 08826, South Korea
 

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