The hypersonic regime of planetary entry combines the most severe environments that an entry vehicle will encounter with the greatest amount of uncertainty as to the events unfolding during that time period. This combination generally leads to conservatism in the design of an entry vehicle, specifically that of the thermal protection system (TPS). Each planetary entry provides a valuable aerodynamic and aerothermal testing opportunity; the utilization of this opportunity is paramount in better understanding how a specific entry vehicle responds to the demands of the hypersonic entry environment. Previous efforts have been made to instrument entry vehicles in order to collect data during the entry period and reconstruct the corresponding vehicle response. The purpose of this paper is to cumulatively document past TPS instrumentation designs for applicable planetary missions, as well as to list pertinent results and any explainable shortcomings.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Aerodynamic and Aerothermal TPS Instrumentation Reference Guide


    Contributors:

    Conference:

    IEEE Aerospace Conference ; 2016 ; Big Sky, MT, United States


    Publication date :

    2016-03-05


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Aerodynamic and Aerothermal TPS Instrumentation Reference Guide

    B. A. Woollard / R. D. Braun / D. Bose | NTIS | 2016


    Dragonfly Aerothermal Environment and Aerosciences Instrumentation

    Brandis, Aaron M. / Naughton, Christopher / Saunders, David et al. | AIAA | 2023


    Dragonfly Aerothermal Environment and Aerosciences Instrumentation

    Brandis, Aaron M. / Naughton, Christopher / Saunders, David et al. | TIBKAT | 2023



    XJet: A Small-Scale Aerothermal Test Environment for Instrumentation

    Fu, Johnny / Olivares, Ricardo / Oishi, Tomo et al. | AIAA | 2006