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IN THIS PROPOSED WORK A MULTI-PHYSICS COMPUTATIONAL FRAMEWORK WILL BE DEVELOPED TO STUDY THE MICRO-SCALE DECOMPOSITION BEHAVIOR OF ABLATIVE THERMAL PROTECTION SYSTEMS. THE PROPOSED RESEARCH WILL INCLUDE MODELING HIGH-TEMPERATURE FLOW THOUGH POROUS MEDIA USING DIRECT SIMULATION MONTE CARLO (DSMC) METHODS GIVEN THE NON-CONTINUUM CONDITIONS THAT EXIST DURING AN ATMOSPHERIC ENTRY. WITHIN THE DSMC FRAMEWORK OXIDATION AT THE FIBER SCALE INCLUDING PITTING DYNAMICS (THE NON-UNIFORM WAY IN WHICH CARBON FIBERS OXIDIZE) AS WELL AS SOLID AND RADIATIVE HEAT TRANSFER WILL BE SIMULATED. OXIDATION MODELING WILL BE COUPLED WITH MECHANICAL FAILURE MODELING OF THE CARBON FIBERS INCLUDING THERMAL STRESSES AND FLUID-STRUCTURE INTERACTIONS. THE COMPUTATIONAL FRAMEWORK WILL BE USED TO MODEL THE THERMOCHEMICAL AND MECHANICAL EROSION THAT OCCURS WHEN A SPACECRAFT ENTERS AN ATMOSPHERE INCLUDING THOSE WITH ATMOSPHERIC DUST SUCH AS MARS.

$252,125FY2020National Aeronautics and Space AdministrationNASA

The Leland Stanford Junior University

Investigators

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IN THIS PROPOSED WORK A MULTI-PHYSICS COMPUTATIONAL FRAMEWORK WILL BE DEVELOPED TO STUDY THE MICRO-SCALE DECOMPOSITION BEHAVIOR OF ABLATIVE THERMAL PROTECTION SYSTEMS. THE PROPOSED RESEARCH WILL INCLUDE MODELING HIGH-TEMPERATURE FLOW THOUGH POROUS MEDIA USING DIRECT SIMULATION MONTE CARLO (DSMC) METHODS GIVEN THE NON-CONTINUUM CONDITIONS THAT EXIST DURING AN ATMOSPHERIC ENTRY. WITHIN THE DSMC FRAMEWORK OXIDATION AT THE FIBER SCALE INCLUDING PITTING DYNAMICS (THE NON-UNIFORM WAY IN WHICH CARBON FIBERS OXIDIZE) AS WELL AS SOLID AND RADIATIVE HEAT TRANSFER WILL BE SIMULATED. OXIDATION MODELING WILL BE COUPLED WITH MECHANICAL FAILURE MODELING OF THE CARBON FIBERS INCLUDING THERMAL STRESSES AND FLUID-STRUCTURE INTERACTIONS. THE COMPUTATIONAL FRAMEWORK WILL BE USED TO MODEL THE THERMOCHEMICAL AND MECHANICAL EROSION THAT OCCURS WHEN A SPACECRAFT ENTERS AN ATMOSPHERE INCLUDING THOSE WITH ATMOSPHERIC DUST SUCH AS MARS. · GrantIndex