Abstract
Thermomechanical analysis of ablative materials is of great importance to the design of thermal-protection systems. A finite volume method for coupling the mechanical and thermal response models for ablation problems is proposed. This method is capable of simulating both transient and static thermomechanical responses. The solver is verified against analytic solutions and through code-to-code comparisons. It is then fully coupled to a state-of-the-art material response code. Coupled results show that high temperature gradients have significant effects on the mechanical performance and stress generation. The magnitude and the location ofthe stress concentration can play a significant role in structural integrity, and may lead to crack formation as well as spallation.
| Original language | English |
|---|---|
| Pages (from-to) | 369-379 |
| Number of pages | 11 |
| Journal | Journal of Thermophysics and Heat Transfer |
| Volume | 32 |
| Issue number | 2 |
| DOIs | |
| State | Published - 2018 |
Bibliographical note
Publisher Copyright:© Copyright 2017 by Rui Fu, Haoyue Weng, Jonathan F. Wenk, and Alexandre Martin.
Funding
Support for this work was provided by Kentucky EPSCoR and NASA award NNX13AN04A, and NASA award NNX16AD06A. The authors are grateful to E. Sozer at NASA Ames Research Center for insightful discussions on the modeling code.
| Funders | Funder number |
|---|---|
| Kentucky Statewide EPSCoR | |
| National Aeronautics and Space Administration | |
| National Aeronautics and Space Administration | NNX13AN04A, NNX16AD06A |
ASJC Scopus subject areas
- Condensed Matter Physics
- Aerospace Engineering
- Mechanical Engineering
- Fluid Flow and Transfer Processes
- Space and Planetary Science