Method for joining two substantially planar fiber-composite structural components with each other

Patent metadata

Field	Value
Publication number	US-11807352-B2
Application number	US-202217882841-A
Country	US
Kind code	B2
Filing date	Aug 8, 2022
Priority date	Aug 10, 2021
Publication date	Nov 7, 2023
Grant date	Nov 7, 2023

Abstract

A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

First claim

The invention claimed is:

1. A method for joining two substantially planar fiber-composite structural components with each other, the method comprising:
arranging a lower structural component of the two structural components beneath an upper structural component of the two structural components on top of a support jig, such that the two structural components overlap with each other along a joining region,
wherein an end section of the lower structural component within the joining region borders a defined gap between the upper structural component and the support jig in which the upper structural component is unsupported by the support jig,
wherein the defined gap is bordered on an opposite side of the end section of the lower structural component by a filling portion of the upper structural component or a planar filler element being supported by the support jig; and

joining the lower structural component to the upper structural component within the joining region by applying temperature and pressure to the structural components,
wherein a width of the defined gap is chosen such that the upper structural component elastically deforms along the defined gap under the pressure and bends down into the defined gap such that the upper structural component abuts the support jig along the defined gap and thereby compensates thickness tolerances between the structural components during the application of the pressure.

2. The method according to claim 1 , wherein the width of the defined gap is defined depending on at least one of the applied pressure, a material of the upper structural component, a thickness of the upper structural component above the defined gap and expected tolerances of the structural components.

3. The method according to claim 1 , wherein the two structural components are bonded to each other by an adhesive, which is brought between them within the joining region prior to the joining.

4. The method according to claim 3 , further comprising:
temporarily positioning an insert element within the defined gap at least one of prior to or during the joining to control leakage of adhesive at the defined gap.

5. The method according to claim 1 ,
wherein the structural components follow a stepped shape at respective opposing joining surfaces such that they are complementary formed to each other along the stepped shape,
wherein the structural components are connected via mechanical fasteners at each individual step defined by the stepped shape excepting for a final step constituting the end section of the lower structural component.

6. The method according to claim 1 , wherein the two substantially planar fiber-composite structural components comprise two skin sections of an aircraft.

Assignees

• Airbus Operations Gmbh

Inventors

• Poppe Andreas
• Benthien Hermann
• Beumler Thomas

Classifications

• B64C1/12 Primary

  Construction or attachment of skin panels · CPC title

• B29C65/4825

  Pressure sensitive adhesives · CPC title

• B29C65/562

  using extra joining elements, i.e. which are not integral with the parts to be joined (using plastic snap elements B29C65/58; using plastic rivets B29C65/601) · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B29L2031/3082

  Fuselages · CPC title