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.
Hypersonic aircraft window system
07.11.2023
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
NTIS | 1964
|Hypersonic aircraft nose cone and hypersonic aircraft with same
Europäisches Patentamt | 2023
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