Assembly having individual components made of a fibre-reinforced composite material

Patent metadata

Field	Value
Publication number	US-10661507-B2
Application number	US-201514879422-A
Country	US
Kind code	B2
Filing date	Oct 9, 2015
Priority date	Oct 21, 2014
Publication date	May 26, 2020
Grant date	May 26, 2020

Abstract

An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

First claim

What is claimed is:

1. An aircraft assembly comprising:
a first component comprising a first fibre-reinforced composite material having reinforcing fibre layers and a curable plastics material, the first component configured as a T-shaped reinforcing element having a base and a leg extending from the base, the base having two edge sections, and the leg having an edge section;
a second component comprising a second fibre-reinforced composite material having reinforcing fibre layers and the curable plastics material; and
sealing tape comprising reinforcing fibres and the curable plastics material;
a first piece of the sealing tape extending over the edge section of the leg, and over two surface sections of the leg, wherein the two surface sections of the leg are adjacent to the edge section of the leg;
a second piece of the sealing tape extending over a first edge section of the base, over a first surface section of the base adjacent to the first edge section of the base, and over a first surface section of the second component adjacent to the first edge section of the base;
a third piece of the sealing tape extending over a second edge section of the base, over a second surface section of the base adjacent to the second edge section of the base, and over a second surface section of the second component adjacent to the second edge section of the base; and
the curable plastics material being cured to seal the edge section of the leg and the two edge sections of the base with the sealing tape, and such that the second and third pieces of the sealing tape connect the first component to the second component.

2. The aircraft assembly according to claim 1 ,
wherein 85 to 95 vol % of the reinforcing fibres contained in the sealing tape are carbon fibres.

3. The aircraft assembly according to claim 1 ,
wherein 5 to 15 vol % of the reinforcing fibres contained in the sealing tape are fibres comprising a thermoplastic plastics material.

4. The aircraft assembly according to claim 1 ,
wherein the sealing tape contains less than 35 vol % of reinforcing fibres.

Assignees

• Airbus Operations Gmbh

Inventors

• Vichniakov Alexei
• Sayeh Mohamed-Mourad
• Witte Tassilo
• Hoffmeister Thomas

Classifications

• B29C66/1122

  Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title

• B29C65/5014

  being fibre-reinforced (B29C65/5028 takes precedence) · CPC title

• B29C66/72143

  Fibres of discontinuous lengths · CPC title

• B29C65/4885

  characterised by their composition being non-plastics · CPC title

• B29C66/00145

  Vacuum, e.g. partial vacuum · CPC title