This paper involves thermal analyses of the base and lateral wall of the test launch vehicle based on the flight result. The base is estimated to have 44    kW / m 2 of heat flux and is covered by a thermal protection system to protect itself from the heat. The measured heat flux on the base is 44 55    kW / m 2 in ground firing tests and 38    kW / m 2 in the flight test. The temperature is maintained below 25 ° C during the flight. A significant convective heat flux, expected to arise from the recirculation, is observed in the subsonic region below 10 km of altitude when ascending. The heat flux and temperature of the lateral wall are estimated by considering the aerodynamic heating by external flow and the radiative cooling at the wall, and a thermal protection system is not applied. During most of the flight time, wall temperatures are maintained below 30 ° C . It is expected that the effect of solar radiation and heat loss on the cryogenic parts will appear to depend on the location.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Pre- and Postflight Thermal Analysis of Test Launch Vehicle Fuselage


    Beteiligte:
    Kim, Jongmin (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2019-08-29


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch