Method for welding parts made of thermoplastic material

Patent metadata

Field	Value
Publication number	US-12240184-B2
Application number	US-202318317294-A
Country	US
Kind code	B2
Filing date	May 15, 2023
Priority date	Jul 16, 2018
Publication date	Mar 4, 2025
Grant date	Mar 4, 2025

Abstract

A method for welding at least two parts including a thermoplastic material and having respective surfaces to be welded, including: inserting an insert between the surfaces to be welded of the two parts; generating heat via the insert; wherein the insert moves in relation to the parts to be welded in a welding direction. Also, an installation adapted for implementation of the method.

First claim

The invention claimed is:

1. A method for welding at least two rigid parts comprising a thermoplastic material and having respective surfaces to be welded, comprising: inserting an insert between the surfaces to be welded of the two rigid parts, said insert having a thickness of 1.5 mm or less; providing heat via said insert; wherein the insert moves in relation to the two rigid parts to be welded at a time of welding, in a welding direction, at a rate of 50 to 1000 mm/min.

2. The method according to claim 1 , wherein the heat is provided by said insert, the latter being heated via induction, via resistive effect, via vibration, via friction, via ultrasound, via use of laser, via a stream of hot gas or via conduction from an external heat source.

3. The method according to claim 1 , wherein the insert comprises an induction-sensitive material, and the heat of the insert is provided by a generation of a magnetic field by at least one inductor.

4. The method according to claim 1 , further comprising a contacting of surfaces to be welded of the two rigid parts to be welded by applying pressure onto at least one of the two rigid parts upstream and/or downstream of a position of the insert in relation to the welding direction.

5. The method according to claim 1 , wherein the insert is in contact with each of the surfaces to be welded of the two rigid parts.

6. The method according to claim 1 , wherein at least one of the two rigid parts is made of composite material comprising reinforcing fibres in a matrix of thermoplastic material.

7. The method according to claim 1 , wherein the thermoplastic material is selected from the group of polyamides, polyimides, polyaryletherketones and polyetheretherketones, polyethylene terephthalate, polyolefins, phenylene polysulfide, polysulfones, chlorinated polymers, acrylic or methacrylic polymers.

8. The method according to claim 1 , wherein at least one of the two rigid parts, are a multilayer structure.

9. The method according to claim 1 , wherein the two rigid parts are aircraft fuselage parts.

10. The method according to claim 1 , wherein the insert includes a plate portion having the thickness of 1.5 mm or less.

11. The method according to claim 1 , wherein the insert is metallic.

12. An installation configured for the method of claim 1 , the installation comprising:
a support to hold the two rigid parts to be welded;
an arm comprising at its end portion a heating insert having a thickness of 1.5 mm or less, configured to be inserted between the surfaces to be welded of the two rigid parts;
the insert being configured to move in relation to the two rigid parts to be welded at the time of welding, in a welding direction.

13. The installation according to claim 12 , further comprising a heat-generating device of said insert via induction, via resistive effect, via vibration, via friction, via ultrasound, via laser, via a stream of hot gas or via conduction from an external heat source.

14. The installation according to claim 13 , wherein the heat-generating device is at least one inductor, and said insert comprises an induction-sensitive material.

15. The installation according to claim 12 , further comprising one or more compacting rollers and/or one or more pressure rollers.

16. The installation according to claim 15 , wherein the compacting roller(s) are configured to be subjected to vibration at an adapted frequency.

17. The installation according to claim 12 , wherein the support is configured to be heated.

18. The installation according to claim 12 , comprising a controlled-temperature chamber.

19. The installation according to claim 18 , wherein the controlled-temperature chamber comprises a flexible skirt.

20. The method according to claim 1 , wherein the insert has a thickness of from 0.3 to 1.5 mm.

21. The method according to claim 1 , wherein the insert has a thickness of from 0.5 to 1.5 mm.

22. The method according to claim 1 , wherein the insert has a thickness of from 0.1 to 1 mm.

23. The installation according to claim 12 , wherein the insert has a thickness of from 0.3 to 1.5 mm.

24. The installation according to claim 12 , wherein the insert has a thickness of from 0.5 to 1.5 mm.

25. The installation according to claim 12 , wherein the insert has a thickness of from 0.1 to 1 mm.

Assignees

• Arkema France
• Soudure Inst De

Inventors

• Glotin Michel
• Cauchois Jean-Pierre
• Philippe Aurélien
• Klein Philippe

Classifications

• B29L2031/3082

  Fuselages · CPC title

• B29K2995/0097

  Thickness · CPC title

• B29K2309/08

  Glass · CPC title

• B29K2307/04

  Carbon · CPC title

• B29K2105/20

  Inserts · CPC title