Slat-Cove Filler for Wing Structure of an Aircraft
US-2021237850-A1 · Aug 5, 2021 · US
Vented leading-edge assembly and method for manufacturing a vented leading-edge assembly
US11440665B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11440665-B2 |
| Application number | US-201916595722-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 8, 2019 |
| Priority date | Oct 23, 2018 |
| Publication date | Sep 13, 2022 |
| Grant date | Sep 13, 2022 |
How to read this patent
A practical reading order for non-experts. Skip the full description unless you need deep technical detail.
- Title
What the patent document calls the invention.
- Abstract
A short plain-language summary of the technical disclosure.
- Assignees and inventors
Who owns or filed the patent and who is credited as inventor.
- Key dates
Filing, priority, publication, and grant dates set the timeline.
- First independent claim
The legal scope of protection — read this for what is actually claimed.
- CPC / IPC classifications
Technology tags used to group this patent with similar filings.
- Citations and related patents
Prior art links and similar publications in this corpus.
Abstract
Official abstract text for this publication.
A vented leading-edge assembly is provided, the assembly including: a slat having a bay and a top skin delimiting a portion of the bay; a spar being arranged in the slat, the spar dividing the bay in a front bay and an aft bay; and a plurality of channel sidewalls being arranged between the top skin and the spar, the plurality of channel sidewalls defining a plurality of channels between the front bay and the aft bay, wherein at least a portion of the spar defines lower channel walls for the plurality of channels.
First claim
Opening claim text (preview).
The invention claimed is: 1. A vented leading-edge assembly comprising: a slat comprising a bay and a top skin delimiting a portion of the bay; a spar arranged in the slat, the spar dividing the bay in a front bay and an aft bay; and a plurality of channel sidewalls arranged between the top skin and the spar, the plurality of channel sidewalls defining a plurality of channels between the front bay and the aft bay, wherein at least a portion of the spar defines lower channel walls for the plurality of channels, and wherein the plurality of channel sidewalls is provided by a perforated strip arranged between the top skin and the spar. 2. The vented leading-edge assembly according to claim 1 , wherein the plurality of channel sidewalls is non-parallel to each other such that a distance between the plurality of channel sidewalls at the front bay is bigger than a distance between the plurality of channel sidewalls at the aft bay. 3. The vented leading-edge assembly according to claim 1 , wherein the plurality of channel sidewalls is parallel. 4. The vented leading-edge assembly according to claim 1 , wherein the leading-edge assembly comprises a plurality of fastening elements connecting the top skin to the spar through the plurality of channel sidewalls. 5. The vented leading-edge assembly according to claim 1 , wherein the front bay comprises a de-icing air outlet configured to fill the front bay with de-icing air. 6. The vented leading-edge assembly according to claim 5 , wherein the de-icing air outlet is a bleeding air outlet in fluid communication with an engine of an aerospace vehicle. 7. The vented leading-edge assembly according to claim 1 , further comprising a rear skin rearward of the spar and delimiting the aft bay, wherein the rear skin comprises a plurality of openings along a bottom of the rear skin. 8. An aerospace vehicle comprising a wing; and a vented leading-edge assembly according to claim 1 ; wherein the vented leading-edge assembly is arranged on a leading-edge of the wing. 9. A method for manufacturing a vented leading-edge assembly, the method comprising: providing a slat comprising a bay and a top skin delimiting a portion of the bay; arranging a spar in the bay such that the spar divides the bay into a front bay and an aft bay; providing a strip comprising a row of channel sidewalls that define a plurality of perforations; and connecting the strip between the spar and the top skin such that each perforation of the plurality of perforations is in fluid communication with the front bay and the aft bay, thereby providing a plurality of channels between the front bay and the aft bay, wherein at least a portion of the spar defines lower channel walls for the plurality of channels. 10. The method according to claim 9 , wherein the method further comprises at least one of the following steps: removing at least one portion of the strip arranged between the row and the aft bay; and removing at least one portion of the strip arranged between the row and the front bay.
Assignees
Inventors
Classifications
Patent family
Related publications grouped by family.
External sources
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US11440665B2 cover?
- A vented leading-edge assembly is provided, the assembly including: a slat having a bay and a top skin delimiting a portion of the bay; a spar being arranged in the slat, the spar dividing the bay in a front bay and an aft bay; and a plurality of channel sidewalls being arranged between the top skin and the spar, the plurality of channel sidewalls defining a plurality of channels between the fr…
- Who is the assignee on this patent?
- Airbus Operations Gmbh
- What technology area does this patent fall under?
- Primary CPC classification B64D15/04. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Sep 13 2022 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).