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Predictive Modeling of Carbon Ablators Using Micro and Macro-Scale ModelingEfforts to build a Predictive Material Modeling (PMM) framework from the micro-scale to the macro-scale are presented in this abstract. To reduce the need for extensive testing, accelerate the design cycle process, and reduce uncertainty margins applied to final designs, NASA is developing simulation and modeling tools that enable characterization of material properties and response to high-enthalpy environments. The Porous Microstructure Analysis (PuMA) code has been developed for computing macroscale (volume averaged) properties of porous materials using microscale images from micro-computed tomography (micro-CT). Microscale modeling requires a realistic representation of a material microstructure; these are obtained either synthetically during the design of the material or through X-ray micro-CT. Volume averaged properties are then used to inform macroscale material response models, such as those implemented in the Porous-material Analysis Toolbox based on OpenFOAM (PATO) software, also actively developed by NASA. The computational model in PATO is a generic heat and mass transfer model for porous reactive materials containing several solid phases and a single gas phase. The detailed chemical interactions occurring between the solid phases and the gas phase are modeled at the pore scale assuming local thermal equilibrium. These tools were developed to efficiently interface with other pre-existing codes such as SPARTA (direct simulation Monte Carlo), DPLR (hypersonic CFD), NEQAIR (radiative transport) and DAKOTA (uncertainty quantification and optimization). Detailed flight data (Mars Science Laboratory [MSL] Entry Descent and Landing Instrument [MEDLI]) is critical for validating these computational tools for NASA applications. Examples of modeling ablative material response using these codes will be presented including 3D simulations of the full-scale heatshield of the MSL capsule. The simulations demonstrate the ability of the modern material response code, PATO, to handle the material response of geometrically complex and large domains, through the use of massively parallel computations.
Document ID
20210016075
Acquisition Source
Ames Research Center
Document Type
Presentation
Authors
John M Thornton
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Federico Semeraro
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Jeremie B E Meurisse
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Arnaud P Borner
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Joshua D Monk
(Ames Research Center Mountain View, California, United States)
Nagi N Mansour
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Date Acquired
May 21, 2021
Subject Category
Fluid Mechanics And Thermodynamics
Meeting Information
Meeting: National Space and Missile Materials Symposium
Location: Virtual
Country: US
Start Date: June 21, 2021
End Date: June 25, 2021
Sponsors: Northrop Grumman (United States), Boeing (United States)
Funding Number(s)
CONTRACT_GRANT: NNA15BB15C
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
NASA Peer Committee
Keywords
Thermal Protection Systems
Ablative Materials
Heat Transfer
Pyrolysis
Material Response Modeling
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