Translational inerter assembly and method for damping movement of a flight control surface
US10145434B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 11, 2018 |
| Grant date | Dec 4, 2018 |
| Priority date | — |
| Expiry date | Jan 11, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.