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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes
SJR: 0.137 SNIP: 0.341 CiteScore™: 0.43

ISSN Print: 1093-3611
ISSN Online: 1940-4360

High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes

DOI: 10.1615/HighTempMatProc.v8.i2.120
pages 283-292

IMPORTANCE OF THE CATALYCITY DURING AN ATMOSPHERIC RE-ENTRY PHASE OF AEROSPACE VEHICLES

M. Balat-Pichelin
Laboratoire "Precedes, Materiaux et Energie Solaire", PROMES-CNRS, rue du four solaire, BP 5,66125 Font-Romeu Odeillo, France
L. Bedra
Laboratoire "Precedes, Materiaux et Energie Solaire", PROMES-CNRS, rue du four solaire, BP 5,66125 Font-Romeu Odeillo, France

ABSTRACT

During the atmospheric re-entry phase of aerospace vehicles, the physico-chemical phenomena taking place on the hot parts (nose cap and wing leading edges) can lead to an important excess of heating and a damage of the protective materials. One aim of the researches undertaken at the PROMES-CNRS laboratory is the study of the catalytic recombination of atomic oxygen under conditions nearby Earth or Mars atmospheric re-entry. Four parameters allow to fully describe the catalycity phenomena: the recombination coefficient γ, the accommodation coefficient β, the catalycity rate kw linked to the apparent recombination coefficient γ' (equal to γ.β) and the recombination thermal flux transferred to the material. Experimental determination of these four parameters, simulation and modeling are presented according to a multi-scale approach: for the experimental part, microscopic scale for the recombination coefficient, mesoscopic scale for both the thermal flux of recombination and accommodation coefficient, and for the theoretical part, atomic scale for molecular dynamic simulation and macroscopic scale for kinetic modeling. Examples of results are given for silica and alumina ceramics in the temperature range 800-2300 K.


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