A rotor system for a rotorcraft includes a rotor hub having a plurality of rotor blade pairs mechanically coupled to a rotor mast. A pitch link assembly is mechanically coupled to each rotor blade pair for controlling the pitch angle of each rotor blade pair in tandem. Each rotor blade pair has an upper rotor blade and a lower rotor blade. The plurality of rotor blade pairs rotor in a single direction and about a single axis of rotation.
ROTOR HUB AND CONTROLS FOR MULTI-BLADED ROTOR SYSTEM
MOYEU DE ROTOR ET COMMANDES POUR UN SYSTEME DE ROTOR A PLUSIEURS PALES
2015-03-31
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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AIAA | 1998
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Tema Archive | 1988
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