The Mars Science Laboratory (MSL) was protected during entry into the Martian atmosphere by a thermal protection system that used NASA’s Phenolic Impregnated Carbon Ablator (PICA). The heat shield of the probe was instrumented with the Mars Entry Descent and Landing Instrument (MEDLI) suite of sensors. MEDLI Integrated Sensor Plugs (MISP) included thermocouples that measured in-depth temperatures at various locations on the heatshield. The flight data has been used as a benchmark for validating ablation codes within NASA. This work seeks to refine the estimate of the material properties for the MSL heat shield and the aerothermal environment during Mars entry using estimation methods in DAKOTA on the temperature data obtained from MEDLI.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Determination of Aerothermal Environment and Ablator Material Response Using Inverse Methods


    Contributors:

    Conference:

    Ablation Workshop ; 2019 ; Minneapolis, MN, United States


    Publication date :

    2019-09-16


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Inverse Determination of Aeroheating and Charring Ablator Response

    Meurisse, Jeremie B. E. / Mansour, Nagi N. | NTRS | 2018



    ABLATOR, AND METHOD FOR MANUFACTURING ABLATOR

    KUBOTA YUKI / SUZUKI TOSHIYUKI / ISHIDA YUICHI et al. | European Patent Office | 2019

    Free access

    InSight Aerothermal Environment Assessment

    Beck, Robin A. S. / Songer, Jarvis T. / Szalai, Christine E. et al. | AIAA | 2021


    InSight Aerothermal Environment Assessment

    Beck, Robin A S. / Songer, Jarvis T. / Szalai, Christine E. et al. | AIAA | 2020