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Year 2004, Volume 8 / Issue 1

DOI: 10.1615/HighTempMatProc.v8.i1

Pages: 178

DOI: 10.1615/HighTempMatProc.v8.i1.100

Article price - $35.00

OXIDATION AND CATALYCITY OF THERMAL PROTECTION MATERIALS AT HIGH TEMPERATURE

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

When a space vehicle enters in planetary atmospheres like Earth (air) and/or Mars (CO₂), oxidation and catalycity coupled phenomena occur on the thermal protective materials of the nose cap and wing leading edges conducting to an important excess of heating and possible damage of the materials. At the PROMES-CNRS laboratory (formerly IMP-CNRS), in the research field "Interaction high solar fluxes-matter", oxidation under plasma conditions, and particularly the active-passive transition in the oxidation of silicon-based ceramics and the catalytic recombination of atomic oxygen under the same conditions are studied. The most important conditions for the ground simulation (high temperature, non-equilibrium plasma flow) have been realized in the MESOX set-up which associates a solar radiation concentrator and a microwave generator. In this paper, are presented some results about the transition between the active and passive oxidation regimes and the recombination of atomic oxygen and/or carbon monoxide at the surface of sintered silicon carbide at high temperatures and in a total pressure range of 10²-10⁴ Pa. The comparison is made between the two atmospheres: air (Earth entry) and CO₂ (Mars entry) for the oxidation transition domain and for the atoms recombination.

pages 161-171

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