Under-flap stiffener for aircraft
US9108714B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 15, 2010 |
| Grant date | Aug 18, 2015 |
| Priority date | — |
| Expiry date | Apr 21, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.