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.


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    Title :

    Modeling Heatshield Erosion Due to Dust Particle Impacts for a Martian Entry Vehicle


    Contributors:
    Palmer, G. E. (author) / Ching, E. (author) / Ihme, M. (author) / Kerkhoff, D. (author) / Gulhan, A. (author)

    Conference:

    International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR) ; 2019 ; Monopoli, Italy


    Publication date :

    2019-09-30


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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    Heatshield Erosion in a Dusty Martian Atmosphere

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    Heatshield erosion in a dusty Martian atmosphere

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    Heatshield erosion in a dusty Martian atmosphere

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