A rotary wing aircraft (10) is provided including a dual counter-rotating, coaxial rotor system (12) having an upper rotor system (16) and a lower rotor system (18) rotatable about a common axis (A). A plurality of blade assemblies (20) is mounted to a portion of either the upper rotor system (16) or the lower rotor system (18). A plurality of individually controllable actuators (38) is coupled to each of the plurality of blade assemblies (20). Each of the plurality of actuators (38) is configured to control movement of the coupled blade assembly (20) about a pitch axis (P). The rotary-wing aircraft (10) additionally includes a sensor system (56) within an airframe (F). A higher harmonic control (HHC) controller (54) is arranged in communication with the sensor system (56) and the plurality of actuators (38) to individually control the upper rotor system (16) and the lower rotor system (18) to reduce vibration.
Vibration control of a swashplateless coaxial rotor
Schwingungssteuerung eines taumelscheibenlosen Koaxialrotors
Contrôle des vibrations d'un rotor coaxial sans plateau cyclique
2017-12-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Green Swashplateless Helicopter Rotor
British Library Conference Proceedings | 2009
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