Thermal Protection System (TPS) materials are usually subjected to harsh and complex environments, with high heat flux and high shear stress caused by the external hypersonic flow field. A great amount of uncertainties lies in these environments and often challenge the overall design and sizing. Moreover, the TPS materials inherently contain imperfections and defects that may also lead to uncertainties in the experiments and modeling. In this study, a sensitivity analysis is conducted by using a state-of-the-art numerical framework for charring ablation problems. Several key parameters such as heat flux, duration time and external pressure as well as material properties such as conductivity and porosity, are studied. The impact of these inputs are quantified with respect to both thermal response and structural response. The results of such study may increase the understanding of the physics of the charring of ablative materials, reveal the regions for optimal design and enhance communication between modelers and decision makers.
|State||Published - Jun 17 2019|
|Event||AIAA Aviation 2019 Forum - Dallas, United States|
Duration: Jun 17 2019 → Jun 21 2019
|Conference||AIAA Aviation 2019 Forum|
|Period||6/17/19 → 6/21/19|
Bibliographical noteFunding Information:
Financial support for this work was provided by the US Army Contracting Command W31P4Q-17-C-0009 and NASA SpaceTech-REDDI-2017-ESI contract number 80NSSC18K0261.
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
ASJC Scopus subject areas
- Computer Science Applications
- Electrical and Electronic Engineering
- Aerospace Engineering