Articulated rotor systems with pitch independent damping
US10457380B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 28, 2017 |
| Grant date | Oct 29, 2019 |
| Priority date | — |
| Expiry date | Feb 26, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F15/124
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.