Abstract—Results of a numerical study of the flow structure occurring between the descent module and landing surface during the braking maneuver of the propulsion system are presented. Data on the force and thermal effect of the emerging flow on the descent module are given, depending on its distance and orientation relative to the landing surface and amount of the braking engine thrust. The pictures of the arising unsteady vortex motion of the medium are presented.
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ACKNOWLEDGMENTS
The calculations were performed using the computing resources of the Interdepartmental Supercomputer Center of the Russian Academy of Sciences (ISC RAS).
Funding
The work was carried out within the framework of the state assignment of the Institute for Computer-Aided Design of the Russian Academy of Sciences.
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Translated by E. Seifina
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Babakov, A.V., Shmatov, S.I. Mathematical Modeling and Analysis of Aerodynamic and Thermal Effects on the Descent Module of the Spacecraft ExoMars-2020 During Soft Landing. Sol Syst Res 55, 668–676 (2021). https://doi.org/10.1134/S0038094621070042
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DOI: https://doi.org/10.1134/S0038094621070042