Article: Modelling of radiative fluxes to the heat shield of a Martian orbiter Journal: International Journal of Aerodynamics (IJAD) 2014 Vol.4 No.3/4 pp.154 - 174 Abstract: The present study proposes a simple model for simulating radiation of high-temperature gases, with the intention of predicting radiative transfers in hypersonic flows surrounding a spacecraft when it enters a planetary atmosphere. This paper presents the methodology and the physical models implemented in an aerodynamics code to account for those specific heat transfers in the flow past a blunt body entering a CO<SUB align="right"><SMALL>2</SMALL></SUB> atmosphere. The line-by-line radiation models include the atomic lines of the atoms C and O, and the molecular systems of the molecule CO, in the [100-7,000 nm] range of the radiation spectrum. The radiation transfers are computed according to a ray-tracing method. Analyses are done to understand the radiative behaviour of the high-temperature gases. The cumulated radiative heat fluxes to the surface of the spacecraft are compared to other computed radiative heat transfer results for verification purpose. Inderscience Publishers - linking academia, business and industry through research

Title: Modelling of radiative fluxes to the heat shield of a Martian orbiter

Authors: Nicolas Bédon; Marie-Claude Druguet; Pascal Boubert

Addresses: Aix-Marseille Université, CNRS UMR 7343, Laboratoire IUSTI, 5, rue Enrico Fermi – Technopole de Château-Gombert, 13453, Marseille Cedex 13, France ' Aix-Marseille Université, CNRS UMR 7343, Laboratoire IUSTI, 5, rue Enrico Fermi – Technopole de Château-Gombert, 13453, Marseille Cedex 13, France ' Université de Rouen, CNRS UMR 6614, Laboratoire CORIA, Site Universitaire du Madrillet – BP 12, 76801, St Etienne du Rouvray Cedex, France

Abstract: The present study proposes a simple model for simulating radiation of high-temperature gases, with the intention of predicting radiative transfers in hypersonic flows surrounding a spacecraft when it enters a planetary atmosphere. This paper presents the methodology and the physical models implemented in an aerodynamics code to account for those specific heat transfers in the flow past a blunt body entering a CO₂ atmosphere. The line-by-line radiation models include the atomic lines of the atoms C and O, and the molecular systems of the molecule CO, in the [100-7,000 nm] range of the radiation spectrum. The radiation transfers are computed according to a ray-tracing method. Analyses are done to understand the radiative behaviour of the high-temperature gases. The cumulated radiative heat fluxes to the surface of the spacecraft are compared to other computed radiative heat transfer results for verification purpose.

Keywords: modelling; aerodynamics code; hypersonic flow; radiative heat flux; Mars atmosphere entry; ray tracing; line-by-line radiation models; radiative fluxes; heat shield; Martian orbiters; radiation; high-temperature gases; spacecraft entry; planetary atmospheres; heat transfer; blunt body.

DOI: 10.1504/IJAD.2014.067582

International Journal of Aerodynamics, 2014 Vol.4 No.3/4, pp.154 - 174

Accepted: 07 Oct 2014
Published online: 28 Feb 2015 *

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Title: Modelling of radiative fluxes to the heat shield of a Martian orbiter

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