# US 10,766,232 B2 · Smooth surface forming tool and manufacture thereof

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- Number: US 10,766,232 B2
- Document ID: US10766232B2
- Status: Granted
- Kind: B2
- Application number: 14/688,074
- Filed: 2015-04-16
- Published: 2015-10-15
- Granted: 2020-09-08
- Earliest claimed: 2012-10-23
- Assignees: Saab AB
- Applicants: Saab AB
- Inventors: Per Hallander; Mikael Petersson; Björn Weidmann; Tommy Grankäll; Göte Strindberg; Pontus Nordin
- Web page: https://patentgrep.com/patent/US10766232B2

## CPC

- B32B 27/08: of synthetic resin
- B29C 35/0227: {using pressure vessels, e.g. autoclaves, vulcanising pans (B29C35/065 takes precedence)}
- B29C 70/443: {and impregnating by vacuum or injection}
- B29C 70/882: {partly or totally electrically conductive, e.g. for EMI shielding (conductive floors or floor coverings H05F3/025; EMI shielding in general H05K9/00)}
- B29K 2105/0872: {Prepregs}
- B29K 2105/167: {Nanotubes}
- B29K 2863/00: Use of EP, i.e. epoxy resins or derivatives thereof as mould material
- B29K 2995/0005: Conductive
- B29L 2031/3085: {Wings}
- B32B 2262/106: Carbon fibres, e.g. graphite fibres
- B32B 2605/18: Aircraft
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- 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)
- B29K: INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR {MOULDS, } REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES

## Abstract

A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.

## Claims

### Claim 1

A method of manufacture of a composite aircraft article having an aerodynamic surface by forming the composite aircraft article having the aerodynamic surface on an aircraft article composite forming tool, wherein the aircraft article composite forming tool comprises a matrix laminate comprising a plurality of laid-up plies with an upper ply including a forming surface for forming said composite aircraft article having the aerodynamic surface, the upper ply of the aircraft article composite forming tool comprising a nano filament structure embedded therein, wherein a portion of the nano filament structure is exposed to the forming surface and wherein the nano filament structure comprises nano filaments that as a whole have a well-defined perpendicular orientation relative to an extension of a plane of the upper ply; the method comprising:
conforming a blank onto the aircraft article composite forming tool;
forming the conformed blank on the upper ply of the forming surface, wherein the forming surface of the aircraft article composite forming tool is adapted to form the aerodynamic surface of the composite aircraft article;
curing the formed blank into the composite aircraft article having the aerodynamic surface; and
finishing the composite aircraft article.

### Claim 2 (depends on 1)

The method according to claim 1, wherein the curing comprises:
heating the forming surface to cure the formed blank into said composite aircraft article having the aerodynamic surface.

### Claim 3 (depends on 2)

The method according to claim 2, further comprising:
coupling at least a portion of the nano filament structure to an energy supply for heating the forming surface, wherein the nano filaments have a closer distance between each other in one portion of the nano filament structure to such degree that the resistance increases than another portion of the nano filament structure.

### Claim 4 (depends on 3)

The method according to claim 3, further comprising:
controllably coupling the energy supply to at least two portions of the nano filament structure.

### Claim 5 (depends on 1)

The method according to claim 1, wherein the nano filament structure is adapted as a forming surface temperature detector.

### Claim 6 (depends on 1)

The method according to claim 1, wherein the nano filament structure comprises carbon nano tubes.

### Claim 7 (depends on 6)

The method according to claim 6, wherein the carbon nano tubes are adapted for electrical conductivity.

### Claim 8 (depends on 6)

The method according to claim 6, wherein the carbon nano tubes are adapted for thermal conductivity.

### Claim 9 (depends on 1)

The method according to claim 1, further comprising:
building the plurality of laid-up plies with fiber reinforced resin pre-impregnated plies, each of the plies comprising a nano filament structure;
impregnating a dry nano filament structure mat to form the upper ply; and
laying the plies upon each other and co-curing the plies.

### Claim 10 (depends on 9)

The method according to claim 9, wherein the dry nano filament structure mat is impregnated with resin by an injection.