Fiber reinforced structural element
US-9643382-B2 · May 9, 2017 · US
Joining method and assembly for an aircraft
US11697251B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11697251-B2 |
| Application number | US-202117219228-A |
| Country | US |
| Kind code | B2 |
| Filing date | Mar 31, 2021 |
| Priority date | Apr 7, 2020 |
| Publication date | Jul 11, 2023 |
| Grant date | Jul 11, 2023 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.
First claim
Opening claim text (preview).
The invention claimed is: 1. A joining method for joining together fiber-reinforced first and second components, the method comprising: forming a connecting region, which comprises one or more thermoplastic polymer materials and is formed with a surface structure region; forming, via additive manufacturing, a first fiber-reinforced component, which comprises a first polymer material as matrix, on the connecting region, such that the connecting region and the first component are attached together to provide a joining surface on the first component; forming a second fiber-reinforced component, which comprises a curable thermosetting second polymer material as matrix; and arranging, after the connecting region and the first component are attached together, a region of the second component in contact with the joining surface and supplying heat to fix the connecting region to the second component while curing the second polymer material to join the first component to the second component; wherein the surface structure region comprises periodic elevations and indentations in at least one direction and is formed on a side of the connecting region that faces away from the joining surface; and wherein, in a plane parallel to the joining surface, the elevations and the indentations are of wavelike design and/or a corrugated or serrated pattern.
Assignees
Inventors
Classifications
Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title
- B29C65/02Primary
by heating, with or without pressure · CPC title
Products made by additive manufacturing · CPC title
characterised by the material of at least one of the parts being a thermoplastic · CPC title
- B29C66/721Primary
Fibre-reinforced materials (B29C66/729 takes precedence) · CPC title
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Frequently asked questions
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- What does patent US11697251B2 cover?
- A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, …
- Who is the assignee on this patent?
- Airbus Sas
- What technology area does this patent fall under?
- Primary CPC classification B29C65/02. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Jul 11 2023 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 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).