A system and method for sending signals at temperatures associated with hypersonic speeds. A window system in a hypersonic aircraft is provided. The window system comprises a transmissive window in an aeroshell of the hypersonic aircraft, a thermal seal, a sensor, and a sensor housing assembly enclosing the sensor. The transmissive window comprises a facesheet and insulating material adjacent to the facesheet. The thermal seal surrounds a perimeter of the facesheet and seals the facesheet to the aeroshell. The window system is radio-frequency transparent at temperatures associated with hypersonic speeds. The window system is configured to operate at an insertion loss of less than one decibel at the hypersonic speeds.


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    Titel :

    Hypersonic aircraft window system


    Beteiligte:
    BEST MICHAEL JOHN (Autor:in) / HENG SANGVAVANN (Autor:in) / LAM TAI ANH (Autor:in) / SHAW PETER (Autor:in) / EMBLER JONATHAN DAVID (Autor:in)

    Erscheinungsdatum :

    07.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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