IP Library › Granted Patent US 11,618,544
Granted Patent B2
US 11,618,544 · App. 16/199,886 · Granted Apr 4, 2023

Method for producing a structural section of a vehicle

Inventors: Peter Linde (Hamburg, DE); Markus Müller (Hamburg, DE); Markus Feiler (Hamburg, DE)
Assignee: AIRBUS OPERATIONS GMBH
B64C1/069B29C70/086B29D99/0014B64C1/12B64F5/10B29K2071/00B29L2031/3082B64C2001/0072
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Quick Facts
Patent No.
US 11,618,544
App. No.
16/199,886
Granted
Apr 4, 2023
Kind
B2
Abstract

A method for producing a structural section of a vehicle comprises the steps of providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel; arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side; integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component; arranging at least two structural components on a carrier, so that at least regions of the borders of the structural components concerned are in surface-area contact; and integrally connecting the regions of the borders that are in surface-area contact to one another.

Claims (20)

1. A method for producing a structural section of a vehicle, comprising the steps of:

providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel,

arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side,

integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component,

arranging at least two structural components on a carrier, so that at least regions of the borders of the skin panels concerned of the structural components are in surface-area contact,

integrally connecting the regions of the borders that are in surface-area contact to one another, and

compacting and removing the carrier from the connected at least two structural components,

wherein the at least one stiffening component is arranged with an offset in relation to the skin panel in such a way that one end of the stiffening component protrudes beyond a border of the skin panel and an opposite end of the stiffening component is at a distance from an opposite border of the skin panel.

2. The method according to claim 1 , the step of providing multiple skin panels comprising, for each skin panel, placing at least two layers one on top of the other in a mold and integrally connecting the layers, each layer having a circumferential contour and an offset being formed between the circumferential contours of two layers lying one on top of the other.

3. The method according to claim 1 , including wherein the step of arranging at least one stiffening component comprises forming the at least one stiffening component by placing at least two layers, one on top of the other in a mold, subsequently integrally connecting the layers to form the stiffening component, and placing the stiffening component onto the skin panel and subsequently integrally connecting the stiffening component.

4. The method according to claim 3 , wherein each layer of the stiffening component has a circumferential contour and an offset being formed between the circumferential contours of two layers lying one on top of the other.

5. The method according to claim 1 , further comprising arranging multiple structural components in rows to form individual area segments with an uninterrupted circumference.

6. The method according to claim 1 , further comprising

arranging the carrier for a defined placing of individual structural components, and

successive placing of individual structural components onto the carrier and the respectively subsequent integral connecting of adjacent structural components.

7. The method according to claim 6 , wherein at least the placing of the structural components onto the carrier being performed by a multi-axis robot.

8. The method according to claim 1 , wherein the fiber-reinforced plastic for providing at least one of the skin panels or the stiffening component comprises a matrix material of a thermoset with reinforcing fibers embedded therein.

9. The method according to claim 8 , wherein the integral connecting of two structural components comprises adhesive bonding.

10. The method according to claim 1 , wherein the fiber-reinforced plastic for providing at least one of the skin panels or the stiffening component comprises a matrix material of a thermoplastic with reinforcing fibers embedded therein.

11. The method according to claim 10 , wherein the integral connecting of structural components comprises welding by at least locally heating a joining zone of the structural components.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Feb 19, 2019
From: LINDE, PETER; MÜLLER, MARKUS; FEILER, MARKUS
To: AIRBUS OPERATIONS GMBH
Reel/Frame 048366/0613 →
Priority Claims (1)
DE 10 2017 128 496.6 · Nov 30, 2017 · national
Continuity (1)
Related Publication 20190161154A1 · May 30, 2019
Cited By (1)
US 12,686,486