Method for manufacturing an aircraft leading edge panel that allows extensive laminar flow to be obtained, and leading edge comprising at least one panel obtained using the said method
US11027818B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Aug 22, 2018 |
| Grant date | Jun 8, 2021 |
| Priority date | — |
| Expiry date | Aug 23, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.