# US 9,751,612 B2 · Multifunctional composite material including a viscoelastic interlayer

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- Number: US 9,751,612 B2
- Document ID: US9751612B2
- Status: Granted
- Kind: B2
- Application number: 13/929,166
- Filed: 2013-06-27
- Published: 2014-01-09
- Granted: 2017-09-05
- Earliest claimed: 2010-12-27
- Assignees: Airbus Operations S.L.
- Applicants: Airbus Operations, S.L.
- Inventors: Enrique Guinaldo Fernandez; Tamara Blanco Varela
- Web page: https://patentgrep.com/patent/US9751612B2

## CPC

- B64C 1/40: Sound or heat insulation {, e.g. using insulation blankets}
- B32B 5/022: {Non-woven fabric}
- B32B 5/024: {Woven fabric}
- B32B 5/12: characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other}
- B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)}
- B32B 7/05: the layers not being connected over the whole surface, e.g. discontinuous connection or patterned connection (using interposed adhesives or bonding materials applied in spaced arrangements B32B7/14)
- B32B 7/12: using interposed adhesives or interposed materials with bonding properties
- B32B 2260/023: Two or more layers
- B32B 2260/046: Synthetic resin
- B32B 2262/101: Glass fibres
- B32B 2262/106: Carbon fibres, e.g. graphite fibres
- B32B 2307/102: Insulating
- B32B 2307/202: Conductive
- B32B 2307/558: Impact strength, toughness
- B32B 2605/18: Aircraft
- Y10T 428/24851: Intermediate layer is discontinuous or differential
- Y10T 428/24995: Two or more layers
- Y10T 428/249951: Including a free metal or alloy constituent
- B64C: AEROPLANES; HELICOPTERS
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation, impact resistance and electric conductivity properties.

## Claims

### Claim 1

A method of manufacturing a structure of composite material comprising:
a structural component in a form of a matrix;
a structural component in a form of fiber;
a layer of viscoelastic material, which comprises a polymer with glass transition temperature that is less than −55° C. and with a melting temperature for a thermoplastic polymer or degradation temperature for a thermostable polymer that is greater than 180° C.; and
a layer of impact-protection material;
the method comprising:
A) laminating the matrix and the fiber by an automatic method, such as an automatic tape lay-up method or fiber placement method, to produce a laminated part, the laminated part being subjected to an autoclave curing or setting cycle to produce a first layer comprising laminated material;
B) adding a second layer comprising viscoelastic material to produce an assembly comprising the second layer on the first layer;
C) adding a third layer comprising impact-protection material on top of the assembly comprising the second layer on the first layer, the third layer forming an outermost layer of the structure of composite material, and the third layer being electrically conductive;
wherein:
a thickness of the second layer is 0.1-0.2 mm,
the third layer has a maximum thickness substantially equal to one-third of a total thickness of the structure of composite material, and
the third layer has a minimum thickness greater than 22% of the total thickness of the structure of composite material, such that a flexural rigidity of the first layer and the third layer is equalized, so that the interlaminar shear between the first layer and the third layer is increased.

### Claim 2 (depends on 1)

The method of manufacturing a structure of composite material according to claim 1, wherein the second layer is added such that:
B1) viscoelastic material in a form of strips or bands, continuous or non-continuous woven or non-woven web is subjected to a process of pre-impregnation with a matrix of thermostable or thermoplastic resin, either combined with carbon or glass fiber, or alone, to produce a pre-impregnated layer of viscoelastic material; and,
B2) the pre-impregnated layer of viscoelastic material is deposited on a surface of the first layer of composite material by automatic lamination, such as by automatic tape lay-up or fiber placement; the pre-impregnated layer is subsequently cured or set at a same time as the first layer, i.e., in a same curing or setting cycle, such that after the automatic lamination and curing or setting process, the pre-impregnated layer comprises the second layer of viscoelastic material.

### Claim 3 (depends on 1)

The method of manufacturing a structure of composite material according to claim 1, wherein the second layer comprises non-impregnated viscoelastic material in a form of a continuous or non-continuous sheet and is deposited either directly on top of a non-cured or non-set first layer of composite material or after depositing an adhesive film on the first layer, such that the second layer cures or sets in a same curing or setting cycle as the first layer of composite material.

### Claim 4 (depends on 3)

The method of manufacturing a structure of composite material according to claim 3, wherein the second layer is previously subjected to a surface treatment, such as by atmospheric pressure plasma treatment, to enhance attachment with the first layer.

### Claim 5 (depends on 1)

The method of manufacturing a structure of composite material according to claim 1, wherein the third layer is added on top of the second layer by thermal spray deposition.

### Claim 6 (depends on 1)

The method of manufacturing a structure of composite material according to claim 1, wherein the third layer is mechanically attached on top of the second layer.

### Claim 7 (depends on 1)

The method of manufacturing a structure of composite material according to claim 1, wherein the third layer is added on top of the second layer by bonding the third layer with an adhesive, the surface thereof having been previously prepared; a curing or setting of the adhesive is to be used for gluing the third layer.

### Claim 8 (depends on 7)

The method of manufacturing a structure of composite material according to claim 7, wherein the adhesive is cured in the same curing or setting cycle of the assembly comprising the second layer on the first layer.

### Claim 9 (depends on 7)

The method of manufacturing a structure of composite material according to claim 7, wherein the adhesive is cured in a cycle different from the curing or setting cycle of the assembly comprising the second layer on the first layer.

### Claim 10 (depends on 9)

The method of manufacturing a structure of composite material according to claim 9, wherein the cured or set assembly comprising the second layer on the first layer is subjected to a surface treatment process prior to gluing, such as treatment by sanding, use of a peelable, or atmospheric pressure plasma treatment.

### Claim 11 (depends on 6)

The method of manufacturing a structure of composite material according to claim 6, wherein the third layer is mechanically attached by rivets.

### Claim 12 (depends on 7)

The method of manufacturing a structure of composite material according to claim 7, wherein the previous preparation of the surface of the third layer comprises a process of descaling or anodizing.

### Claim 13

A method of manufacturing a structure of composite material comprising:
a structural component in a form of a matrix;
a structural component in a form of fiber;
a layer of viscoelastic material, which comprises a polymer with glass transition temperature that is less than −55° C. and with a melting temperature for a thermoplastic polymer or degradation temperature for a thermostable polymer that is greater than 180° C.; and
a layer of impact-protection material;
the method comprising:
A) laminating the matrix and the fiber by an automatic method, such as an automatic tape lay-up method or fiber placement method, to produce a laminated part, the laminated part being subjected to an autoclave curing or setting cycle to produce a first layer comprising laminated material;
B) adding a second layer comprising viscoelastic material to produce an assembly comprising the second layer on the first layer;
C) adding a third layer comprising impact-protection material on top of the assembly comprising the second layer on the first layer, the third layer forming an outermost layer of the structure of composite material, and the third layer being electrically conductive;
wherein:
a thickness of the second layer is 0.1-0.2 mm,
the third layer has a maximum thickness substantially equal to one-third of a total thickness of the structure of composite material, and
the third layer has a minimum thickness greater than 0.8 mm, such that a flexural rigidity of the first layer and the third layer is equalized, so that the interlaminar shear between the first layer and the third layer is increased.