Articulated rotor systems with pitch independent damping
Articulated rotor systems with pitch independent damping
- Neue Suche nach: CHOI JOUYOUNG JASON
- Neue Suche nach: PARHAM JR THOMAS CLEMENT
- Neue Suche nach: MILLER GARY
- Neue Suche nach: STAMPS FRANK BRADLEY
- Neue Suche nach: CHOI JOUYOUNG JASON
- Neue Suche nach: PARHAM JR THOMAS CLEMENT
- Neue Suche nach: MILLER GARY
- Neue Suche nach: STAMPS FRANK BRADLEY
A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.
Dokumentinformationen
Articulated rotor systems with pitch independent damping
2019-10-29
Patent
Elektronische Ressource
Englisch
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