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
2020-01-30
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
HEAT DISSIPATION SYSTEM FOR ROTOR MOUNTED ELECTRONICS
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