Collapsible flap deployment system for a wing of an aircraft
US11059563B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 6, 2018 |
| Grant date | Jul 13, 2021 |
| Priority date | — |
| Expiry date | Aug 17, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A collapsible flap deployment system for an aircraft wing that includes a support beam pivotably connected to a carrier beam, which is connected to a wing flap. A rear spar fitting is connected to a wing rear spar by a first plurality of fasteners and a second plurality of fasteners connects the support beam to the rear spar fitting. A fuse pin connects a link to the rear spar fitting. The fuse pin is configured to shear upon the application of a first predetermined force. An impact load to the bottom of the support beam puts the link into compression applying a force to the fuse pin until the fuse pin shears releasing the link from the rear spar fitting. The impact load rotates the support beam and carrier beam causing the second plurality of fasteners to fail releasing the support beam and carrier beam from the wing rear spar.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.