Rotor hub with blade-to-blade dampers attached to the pitch change axis
US10773798B2 · kind B2 · utility
5Cited by
10References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2017 |
| Grant date | Sep 15, 2020 |
| Priority date | — |
| Expiry date | Jun 3, 2038 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2027/7255
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.