Abstract Hypersonic crew vehicles need reliable thermal protection systems (TPS) to ensure their safety. Since there exists relative large temperature difference between cabin airflow and TPS structure, the TPS shield that covers the cabin is always subjected to a non-adiabatic inner boundary condition, which may influence the heat transfer characteristic of the TPS. However, previous literatures always neglected the influence of the inner boundary by assuming that it was perfectly adiabatic. The present work focuses on studying the impact of cabin environment on the thermal performance. A modified TPS model is created with a mixed thermal boundary condition to connect the cabin environment with the TPS. This helps make the simulation closer to the real situation. The results stress that cabin environment greatly influences the temperature profile inside the TPS, which should not be neglected in practice. Moreover, the TPS size can be optimized during the design procedure if taking the effect of cabin environment into account.

    Highlights Development of thermal design model for multilayer thermal protection system. A hybrid cooling boundary condition is imposed to the TPS inside wall. A series of contrastive cases are conducted to evaluate the impact of cabin environment on TPS. Big discrepancy is found between the simulation results of the cases with adiabatic and non-adiabatic boundary condition. TPS thickness is optimized by taking the cabin environment into account.


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    Titel :

    Impact of cabin environment on thermal protection system of crew hypersonic vehicle


    Beteiligte:
    Zhu, Xiao Wei (Autor:in) / Zhao, Jing Quan (Autor:in) / Zhu, Lei (Autor:in) / Yu, Xi Kui (Autor:in)

    Erschienen in:

    Acta Astronautica ; 122 ; 287-293


    Erscheinungsdatum :

    2016-01-28


    Format / Umfang :

    7 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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