Articulated rotor systems with pitch independent damping

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 rela...

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Bibliographische Detailangaben
Hauptverfasser:	Miller, Gary, Stamps, Frank Bradley, Parham, Jr., Thomas Clement, Choi, Jouyoung Jason
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BEARINGS BLASTING COSMONAUTICS ELEMENTS OR CRANKSHAFT MECHANISMS ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS LIGHTING MEANS FOR DAMPING VIBRATION MECHANICAL ENGINEERING PERFORMING OPERATIONS ROTARY BODIES OTHER THAN GEARING ELEMENTS SHAFTS SHOCK-ABSORBERS SPRINGS THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	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.