Method for producing a frame component for a door frame structure of an aircraft, frame component, and door frame structure

Patent metadata

Field	Value
Publication number	US-11548659-B2
Application number	US-201816195977-A
Country	US
Kind code	B2
Filing date	Nov 20, 2018
Priority date	Nov 24, 2017
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

First claim

The invention claimed is:

1. A method for producing a frame component that defines an opening of a door frame of an aircraft, the method comprising:
forming a first connecting zone on a first assembly surface of a connecting component by generating a surface texture of the first assembly surface, wherein the connecting component comprises a metal material;
forming a second connecting zone on a second assembly surface of the connecting component by generating a surface texture of the second assembly surface, wherein the second assembly surface extends transversely with respect to the first assembly surface;
placing the first assembly surface of the connecting component against a door frame member which comprises a fiber-reinforced thermoplastics material;
welding the connecting component and the door frame member, wherein thermoplastics material of the door frame member ingresses into the first connecting zone of the connecting component;
placing an attachment member against the second assembly surface of the connecting component, wherein the attachment member comprises a fiber-reinforced thermoplastics material; and
welding the connecting component and the attachment member together on an opposite side of the connecting component from where the door frame member and the connecting component are welded together, wherein thermoplastics material of the attachment member ingresses into the second connecting zone of the connecting component.

2. The method according to claim 1 , wherein:
forming the first connecting zone of the connecting component comprises melting the metal material on the first assembly surface by a laser beam or by electrochemical roughening of the first assembly surface; and
forming the second connecting zone of the connecting component comprises melting the metal material on the second assembly surface by a laser beam or by electrochemical roughening of the second assembly surface.

3. The method according to claim 1 , wherein:
welding the connecting component to the door frame member is performed by laser welding, ultrasound welding, or induction welding; and
welding the connecting component to the attachment member is performed by laser welding, ultrasound welding, or induction welding.

4. The method according to claim 1 , wherein the first and the second connecting zone of the connecting component are each formed with a surface topography which has level differences of between 1 μm and 8 μm.

5. The method according to claim 1 , comprising:
forming a third connecting zone on a third assembly surface of the connecting component by generating a surface texture of the third assembly surface, wherein the third assembly surface is arranged opposite the second assembly surface and is oriented so as to face the latter, such that the second and the third assembly surface form a receiving space;
at the same time as the attachment member is placed against the second assembly surface of the connecting component, placing the attachment member against the third assembly surface of the connecting component by sliding the attachment member into the receiving space; and
welding the connecting component and the attachment member both at the second and at the third assembly surface of the connecting component, wherein the thermoplastics material of the attachment member ingresses into the second and the third connecting zones of the connecting component.

6. The method according to claim 1 , wherein the first assembly surface of the connecting component is placed against an abutment region of a surface of the door frame member and the second assembly surface of the connecting component is placed against an abutment region of a surface of the attachment member, wherein the thermoplastics material of the door frame member and the thermoplastics material of the attachment member have, in the respective abutment region, a thickness range of between 1 pm and 8 pm from the surface.

7. The method according to claim 1 , wherein the door frame member has a U-shaped or C-shaped cross section formed by a transverse web and two side webs, and wherein the first assembly surface of the connecting component is placed against an inner surface, which extends between the side webs, of the transverse web of the door frame member.

8. The method according to claim 7 , wherein the connecting component is placed with the first assembly surface against the inner surface of the transverse web of the door frame member such that the second assembly surface of the connecting component extends transversely with respect to the side webs of the door frame member.

9. The method according to claim 1 , wherein the fiber-reinforced thermoplastics material has polyether ether ketone, polyphenylene sulphide, or polyethyleneimine as a matrix material.

10. A frame component that defines an opening of a door frame of an aircraft, the frame component comprising:
a door frame member comprising a fiber-reinforced thermoplastics material;
a connecting component comprising a metal material, which is welded to an inner surface of the door frame member; and
an attachment member comprising a fiber-reinforced thermoplastics material, which is welded to the connecting component on an opposite side of the connecting component from where the door frame member and the connecting component are welded together.

11. The frame component according to claim 10 , wherein the connecting component is formed as an L-shaped or T-shaped angle piece, and wherein the connecting component is fastened, by a first assembly surface, to the door frame member and, by a second assembly surface, to the attachment member.

12. The frame component according to claim 10 , wherein the door frame member has a U-shaped or C-shaped cross section formed by a transverse web and two side webs, and wherein the connecting component is fastened to an inner surface, which extends between the side webs, of the transverse web of the door frame member.

13. The frame component according to claim 10 , comprising:
a structure member comprising a fiber-reinforced thermoplastics material; and
a further connecting component comprising a metal material, wherein the further connecting component is welded to an inner surface of the structure member and to an end section, situated opposite the door frame member, of the attachment member.

14. The frame component according to claim 10 , comprising a door stopper arranged on an outer surface, which is situated opposite the inner surface of the door frame member, wherein the door stopper comprises an abutment lug which projects from the outer surface.

15. A door frame of ctructurc for an aircraft, the door frame comprising:
a first frame component comprising:
a first door frame member comprising a fiber-reinforced thermoplastics material;
a first connecting component comprising a metal material, which is welded to an inner surface of the first door frame member; and
a first attachment member comprising a fiber-reinforced thermoplastics material, which is welded to the first connecting component on an opposite side of the first connecting component from where the first door frame member and the first connecting component are welded together;

a second frame component comprising:
a second door frame member comprising a fiber-reinforced thermoplastics material;
a second connecting component comprising a metal material, which is welded to an inner surface of the second door frame member; and

a second attachment member comprising a fiber-reinforced thermoplastics material, which is welded to the second connecting component on an opposite side of the se

Assignees

• Airbus Operations Gmbh

Inventors

• Linde Peter
• Kluge Albrecht

Classifications

• B29C66/0246

  Cutting or perforating, e.g. burning away by using a laser or using hot air (simultaneously welding and severing using a fluid B29C65/7471; simultaneously welding and severing using radiation B29C65/7473; cutting-off or cutting-out a part of a strip-like or sheet-like material, transferring that part and fixing it to an article B29C69/005) · CPC title

• B29C66/52441

  with two right angles, e.g. for making T-shaped pieces · CPC title

• B64F5/10 Primary

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

• B29C65/44

  Joining a heated non plastics element to a plastics element · CPC title

• B29L2031/724

  Doors · CPC title