Rotorcraft tail rotor, a rotorcraft fitted with such a tail rotor, and a method of statically and/or dynamically balancing a rotorcraft tail rotor
US10479494B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 24, 2015 |
| Grant date | Nov 19, 2019 |
| Priority date | — |
| Expiry date | Jun 24, 2036 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2027/005
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.