Date Available
6-13-2015
Year of Publication
2014
Document Type
Doctoral Dissertation
Degree Name
Doctor of Philosophy (PhD)
College
Engineering
Department/School/Program
Mechanical Engineering
Advisor
Dr. Alexandre Martin
Co-Director of Graduate Studies
Dr. James M. McDonough
Abstract
During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent the payload from overheating, charring ablative materials are favored to be applied as the heat shield at the exposing surface of the vehicle. Accurate modeling not only prevents mission failures, but also helps reduce cost. Existing models were mostly limited to one-dimensional and discrepancies were shown against measured experiments and flight-data. To help improve the models and analyze the charring ablation problems, a multidimensional material response module is developed, based on a finite volume method framework. The developed computer program is verified through a series of test-cases, and through code-to-code comparisons with a validated code. Several novel models are proposed, including a three-dimensional pyrolysis gas transport model and an orthotropic material model. The effects of these models are numerically studied and demonstrated to be significant.
Digital Object Identifier (DOI)
https://doi.org/10.13023/etd.2014.002
Recommended Citation
Weng, Haoyue, "Multidimensional Modeling of Pyrolysis Gas Transport Inside Orthotropic Charring Ablators" (2014). Theses and Dissertations--Mechanical Engineering. 50.
https://uknowledge.uky.edu/me_etds/50
Included in
Heat Transfer, Combustion Commons, Space Vehicles Commons, Structures and Materials Commons
