# US 10,118,685 B2 · Method of joining panels for an airframe

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- Number: US 10,118,685 B2
- Document ID: US10118685B2
- Status: Granted
- Kind: B2
- Application number: 14/514,994
- Filed: 2014-10-15
- Published: 2015-10-15
- Granted: 2018-11-06
- Earliest claimed: 2013-10-17
- Assignees: Airbus Operations GmbH
- Applicants: Airbus Operations GmbH
- Inventors: Stefan Elze; Marco Pacchione; Juergen Silvanus
- Web page: https://patentgrep.com/patent/US10118685B2

## CPC

- B64C 1/12: Construction or attachment of skin panels
- B23K 20/002: {specially adapted for particular articles or work (B23K20/129 takes precedence)}
- B23K 20/1265: {Non-butt welded joints, e.g. overlap-joints, T-joints or spot welds}
- B23K 20/129: {specially adapted for particular articles or work}
- B23K 31/02: relating to soldering or welding
- B29C 65/48: using adhesives {, i.e. using supplementary joining material; solvent bonding}
- B29C 65/564: {hidden in the joint, e.g. dowels or Z-pins (B29C65/603 takes precedence)}
- B29C 65/72: by combined operations {or combined techniques}, e.g. welding and stitching
- B29C 66/02241: {Cutting, e.g. by using waterjets, or sawing (using heat B29C66/0246; 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)}
- B29C 66/0326: {Cutting, e.g. by using waterjets, or perforating (using heat B29C66/0346)}
- B29C 66/1162: {Single bevel to bevel joints, e.g. mitre joints}
- B29C 66/14: {the joint having the same thickness as the thickness of the parts to be joined (B29C66/1142 takes precedence)}
- B29C 66/43: {Joining a relatively small portion of the surface of said articles (B29C66/45 takes precedence)}
- B29C 66/721: {Fibre-reinforced materials (B29C66/729 takes precedence)}
- B32B 37/06: characterised by the heating method
- B32B 37/182: {one or more of the layers being plastic}
- B32B 38/0004: {Cutting, tearing or severing, e.g. bursting; Cutter details (cutting in general B26D; laminating combined with punching or perforating B32B38/04; removing all or part of the layers B32B38/10; cutting in combination with laying up and registration B32B38/185 takes precedence)}
- B64C 1/069: {Joining arrangements therefor}
- B29C 66/7212: {characterised by the composition of the fibres}
- B29L 2031/3082: {Fuselages}
- B29L 2031/3085: {Wings}
- B32B 2605/18: Aircraft
- B64C 2001/0072: {from composite materials}
- F16B 5/08: by means of welds or the like (welding B23K)
- Y02T 50/40: Weight reduction
- B64C: AEROPLANES; HELICOPTERS
- B23K: SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00)
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- F16B: DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING (couplings for transmitting rotation F16D)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 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.

### Claim 2 (depends on 1)

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.

### Claim 3 (depends on 2)

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.

### Claim 4 (depends on 3)

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.

### Claim 5 (depends on 3)

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.

### Claim 6 (depends on 1)

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.

### Claim 7 (depends on 6)

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.

### Claim 8 (depends on 6)

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.

### Claim 9 (depends on 6)

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