Method and device for joining components

Patent metadata

Field	Value
Publication number	US-10035303-B2
Application number	US-201213399339-A
Country	US
Kind code	B2
Filing date	Feb 17, 2012
Priority date	Aug 18, 2009
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

A method for joining a first and a second component, at least one of which comprises a fiber-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

First claim

The invention claimed is:

1. A method for tolerance compensation between a first and a second aircraft fuselage shell segment, at least one of which comprises a fiber-reinforced plastics material, comprising:
arranging, after curing of the fiber-reinforced plastics material to a degree sufficient to make a complete aircraft fuselage cell, the aircraft fuselage shell segments in relation to one another while leaving a gap region having a width of at least 0.3 mm between the first and the second aircraft fuselage shell segment;
filling the gap region, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed; and
introducing energy locally into the nanoparticles by exciting the nanoparticles in the gap region by sound waves in order to cure the plastics material filler.

2. The method according to claim 1 , wherein the width of the gap region is 2 mm or less.

3. The method according to claim 1 , comprising heating the plastics material filler by the local introduction of energy in order to cure the plastics material filler is provided.

4. The method according to claim 3 , wherein the heating of the plastics material filler is performed up to 40° C. to 90° C. in order to cure the plastics material filler.

5. The method according to claim 1 , comprising stimulating, by the local introduction of energy, a chemical reaction in the plastics material filler, which reaction is catalysed by the nanoparticles, in order to cure the plastics material filler is provided.

6. The method according to claim 1 , wherein the nanoparticles comprise a material having a higher thermal conductivity than the plastics material filler.

7. The method according to claim 1 , wherein the nanoparticles comprise a boehmite.

8. The method according to claim 1 , wherein energy is introduced locally by exciting the nanoparticles by ultrasonic waves.

9. A method for tolerance compensation between a first and a second aircraft fuselage section, at least one of which comprises a fiber-reinforced plastics material, comprising:
arranging, after curing of the fiber-reinforced plastics material to a degree sufficient to make a complete aircraft fuselage cell, the aircraft fuselage sections in relation to one another while leaving a gap region having a width of at least 0.3 mm between the first and the second aircraft fuselage section;
filling the gap region, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed; and
introducing energy locally into the nanoparticles by exciting the nanoparticles in the gap region by sound waves in order to cure the plastics material filler.

10. The method according to claim 9 , wherein the width of the gap region is 2 mm or less.

11. The method according to claim 9 , comprising heating the plastics material filler by the local introduction of energy in order to cure the plastics material filler is provided.

12. The method according to claim 11 , wherein the heating of the plastics material filler is performed up to 40° C. to 90° C. in order to cure the plastics material filler.

13. The method according claim 9 , comprising stimulating, by the local introduction of energy, a chemical reaction in the plastics material filler, which reaction is catalysed by the nanoparticles, in order to cure the plastics material filler is provided.

14. The method according to claim 9 , wherein energy is introduced locally through the first and/or second aircraft fuselage shell segment.

15. The method according to claim 9 , wherein energy is introduced locally through the first and/or second aircraft fuselage section.

16. The method according to claim 9 , wherein the nanoparticles comprise a material having a higher thermal conductivity than the plastics material filler.

17. The method according to claim 9 , wherein the nanoparticles comprise a boehmite.

18. The method according to claim 9 , wherein energy is introduced locally by exciting the nanoparticles by ultrasonic waves.

19. The method according to claim 9 , comprising curing the plastics material filler simultaneously in a complete transverse joint region between the aircraft fuselage sections is provided.

Assignees

• Litzenberger Karsten
• Edelmann Klaus
• Schweim Matthias
• Schildt Rainer
• Airbus Operations Gmbh

Inventors

• Litzenberger Karsten
• Edelmann Klaus
• Schweim Matthias
• Schildt Rainer

Classifications

• C09J2205/31

  Chemistry & Metallurgy · mapped topic

• B29C65/1409

  Visible light radiation · CPC title

• B29C66/72321

  consisting of metals or their alloys · CPC title

• B29C2035/0822

  using IR radiation · CPC title

• B29C65/489

  being metals · CPC title