A hub for a rotary wing aircraft includes a plurality of rotor blades, and a heat dissipation system including an aerodynamic faring arranged outwardly of the hub. The aerodynamic fairing has an outer surface and an inner surface defining a component receiving zone. An electronic component is mounted to the inner surface of the aerodynamic faring in the component receiving zone.
HEAT DISSIPATION SYSTEM FOR ROTOR MOUNTED ELECTRONICS
WÄRMEABLEITUNGSSYSTEM FÜR ROTORMONTIERTE ELEKTRONIK
SYSTÈME DE DISSIPATION DE CHALEUR POUR APPAREILS ÉLECTRONIQUES MONTÉS SUR UN ROTOR
2020-01-29
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
HEAT DISSIPATION SYSTEM FOR ROTOR MOUNTED ELECTRONICS
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