Method of joining panels for an airframe

Patent metadata

Field	Value
Publication number	US-10118685-B2
Application number	US-201414514994-A
Country	US
Kind code	B2
Filing date	Oct 15, 2014
Priority date	Oct 17, 2013
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

Abstract

A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

First claim

The invention claimed is:

1. A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, the method comprising:
preparing a planar edge region of a first panel to form a first joining surface;
preparing a planar edge region of a second panel to form a second joining surface, wherein the first panel is positioned on top of the second panel such that respective planar edge regions thereof overlie one another;
wherein preparing the edge region of the first panel and preparing the edge region of the second panel comprises machining or cutting the planar edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously, wherein a cutting tool extends through both of the panels into a backing material layer which supports the edge regions of the panels;
aligning and positioning the first and second panels with respect to one another such that the first and second joining surfaces abut and interface in contact with one another to form a joint area, wherein the joining surfaces are substantially congruous or matching and make face-to-face contact in the joint area, and wherein the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a major plane or a major surface of the first and second panels; and
joining the first and second panels at the joining surfaces in the joint area.

2. The method according to claim 1 , wherein the joining comprises fusing or bonding the first and second joining surfaces with one another in the joint area, preferably over a substantially full extent thereof.

3. The method according to claim 2 , wherein the joining comprises friction welding the first and second panels to one another at and along the joining surfaces.

4. The method according to claim 3 , comprising applying a strip of metal on the first and second panels over the joint area, wherein the metal strip covers and extends along the joining surfaces, whereby the metal strip is incorporated in the friction welding along the joining surfaces.

5. The method according to claim 3 , wherein an intermediate member having an elongate stiffening profile is provided in the joint area to interface with and abut the joining surfaces, wherein the intermediate member is incorporated in the friction welding along the joining surfaces.

6. The method according to claim 1 , wherein joining the first and second panels at the joining surfaces includes inserting one or more connector pins or studs to extend through the joining surfaces, and through or to a major surface or an outer surface of each panel.

7. The method according to claim 6 , comprising boring one or more holes through the joining surfaces of the first and second panels for respectively receiving the one or more connector pins or studs.

8. The method according to claim 6 , wherein the step of joining the first and second panels at the joining surfaces includes applying adhesive between the joining surfaces and clamping the first and second panels together such that the joining surfaces abut one another in face-to-face contact.

9. The method according to claim 6 , wherein the connector pins or studs are adhesively bonded in the holes bored through the joining surfaces.

Assignees

• Airbus Operations Gmbh

Inventors

• Elze Stefan
• Pacchione Marco
• Silvanus Juergen

Classifications

• B29C65/72

  by combined operations {or combined techniques}, e.g. welding and stitching · CPC title

• B29C66/721

  Fibre-reinforced materials (B29C66/729 takes precedence) · CPC title

• B29C66/0326

  Cutting, e.g. by using waterjets, or perforating (using heat B29C66/0346) · CPC title

• B29C65/564

  hidden in the joint, e.g. dowels or Z-pins (B29C65/603 takes precedence) · CPC title

• B32B37/182

  one or more of the layers being plastic · CPC title