Because planetary missions to Mars take years from initial design to arrival at Mars, and because of the unpredictability of major global dust storms, the de-sign of the thermal protection system (TPS) of a Mars entry vehicle requires an estimation for the potential damage caused by dust particle impacts on the heat-shield. This paper will review previous analytical and experimental approaches to modeling dust particle ero-sion and will compare the legacy models against more modern computational techniques and new dust ero-sion models that will be based on upcoming experi-ments in the German Aerospace Center (DLR) GBK facility. The various models will be compared by incorporating them into the Icarus material response code applied to a representative vehicle entering the Martian atmosphere.
Modeling Heatshield Erosion Due to Dust Particle Impacts for a Martian Entry Vehicle
International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR) ; 2019 ; Monopoli, Italy
2019-09-30
Conference paper
No indication
English
Heatshield Erosion in a Dusty Martian Atmosphere
Online Contents | 1993
|Heatshield erosion in a dusty Martian atmosphere
NTRS | 1993
|Heatshield erosion in a dusty Martian atmosphere
AIAA | 1993
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