Author ORCID Identifier

https://orcid.org/0000-0003-0375-7298

Year of Publication

2022

Degree Name

Master of Science in Mechanical Engineering (MSME)

Document Type

Master's Thesis

College

Engineering

Department/School/Program

Mechanical Engineering

First Advisor

Dr. Alexandre Martin

Abstract

During planetary entry, space vehicles encounter high loads of thermal energy which requires a thermal protection system. Ablative thermal protection systems are usually made out of fibrous materials that exhibit internal radiation. In order to model the internal radiation response of a thermal protection system one should obtain proper radiative properties as well as thermal properties. The objective of this work is to provide a method that solves for the solid/gas thermal conductivity. Which can be used in coupled detailed radiative analysis.

Keywords: radiative conductivity, fibrous materials, radiative transfer, thermal protection system, P1 approximation, Finite Volume method.

Digital Object Identifier (DOI)

https://doi.org/10.13023/etd.2022.187

Funding Information

Support for this work was provided by the NASA SpaceTech–REDDI–2018 – ESI grant 80NSSC19K0218

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