# US 2013/0157536 A1 · Aircraft interior lining component and method for producing an aircraft interior lining component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2013/0157536 A1 - Document ID: US20130157536A1 - Status: Published application - Kind: A1 - Application number: 13/763,141 - Filed: 2013-02-08 - Published: 2013-06-20 - Earliest claimed: 2010-08-12 - Assignees: Airbus Operations GmbH - Inventors: Hermann BENTHIEN; Axel Soeffker - Web page: https://patentgrep.com/patent/US20130157536A1 ## CPC - D06N 3/00: Artificial leather, oilcloth or {other} material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof - B29C 70/08: comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers - B64C 1/066: {Interior liners} - Y02T 50/40: Weight reduction - Y10T 428/249921: Web or sheet containing structurally defined element or component - Y10T 428/249944: Fiber is precoated - Y10T 428/249948: Fiber is precoated - Y10T 442/10: Scrim [e.g., open net or mesh, gauze, loose or open weave or knit, etc.] - Y10T 442/20: Coated or impregnated woven, knit, or nonwoven fabric which is not [a] associated with another preformed layer or fiber layer or, [b] with respect to woven and knit, characterized, respectively, by a particular or differential weave or knit, wherein the coating or impregnation is neither a foamed material nor a free metal or alloy layer - D06N: WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR - 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) - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract An aircraft interior lining component includes a composite material, wherein the composite material includes a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix. The strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres. ## Claims ### Claim 1 An aircraft interior lining component which consists at least partially of a composite material, wherein the composite material comprises: a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix, wherein the strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres, and wherein the strength of the interface between the surface of the second rein-forcing fibres and the matrix surrounding the surface of the second reinforcing fibres is lower than the strength of the second reinforcing fibres. ### Claim 2 (depends on 1) The aircraft interior lining component according to claim 1, wherein the matrix consists of a plastic material, in particular a plastic resin. ### Claim 3 (depends on 1) The aircraft interior lining component according to claim 1, wherein the first reinforcing fibres comprise the same core material as the second reinforcing fibres. ### Claim 4 (depends on 1) The aircraft interior lining component according to claim 1, wherein the first reinforcing fibres are provided with a surface layer of an adhesive agent which increases the strength of the interface between the surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fi-bres. ### Claim 5 (depends on 1) The aircraft interior lining component according to claim 1, wherein the second reinforcing fibres are not provided with a surface layer of an adhesive agent which increases the strength of the interface between the surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres. ### Claim 6 (depends on 1) The aircraft interior lining component according to claim 1, wherein the first reinforcing fibres are embedded in the matrix in the form of a fibre fabric or fibre mesh, in one layer or in a plurality of layers, in the form of a fibre pad or in the form of individual fibres, wherein the first reinforcing fibres are orientated uniformly or randomly in all three spatial directions or have a preferred orientation in one or two spatial direction(s). ### Claim 7 (depends on 1) The aircraft interior lining component according to claim 1, wherein the second reinforcing fibres are embedded in the matrix in the form of a fibre fabric or fibre mesh, in one layer or in a plurality of layers, in the form of a fibre pad or in the form of individual fibres, wherein the second reinforcing fibres are orientated uniformly or randomly in all three spatial directions or have a preferred orientation in one or two spatial direction(s). ### Claim 8 A method for producing an aircraft interior lining component, which consists at least partially of a composite material, wherein the production of the composite material comprises the steps: introducing first reinforcing fibres into a matrix and introducing second reinforcing fibres into the matrix, wherein the strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is selected so that it is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres, and wherein the strength of the interface between the surface of the second rein-forcing fibres and the matrix surrounding the surface of the second reinforcing fibres is adjusted so that it is lower than the strength of the second reinforcing fibres. ### Claim 9 (depends on 8) The method according to claim 8, wherein the matrix is made from a plastic material, in particular a plastic resin. ### Claim 10 (depends on 8) The method according to claim 8, wherein the first reinforcing fibres comprise the same core material as the second reinforcing fibres. ### Claim 11 (depends on 8) The method according to claim 8, wherein the first reinforcing fibres are provided with a surface layer of an adhesive agent which increases the strength of the interface between the surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fi-bres. ### Claim 12 (depends on 8) The method according to claim 8, wherein the second reinforcing fibres are introduced into the matrix material un-treated or are provided with a surface layer of an adhesive agent which reduces the strength of the interface between the surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres. ### Claim 13 (depends on 8) The method according to claim 8, wherein the first reinforcing fibres are introduced into the matrix in the form of a fibre fabric or fibre mesh, in one layer or in a plurality of layers, in the form of a fibre pad or in the form of individual fibres, wherein the first reinforcing fibres are orien-tated uniformly or randomly in all three spatial directions or have a preferred orientation in one or two spatial direction(s). ### Claim 14 (depends on 8) The method according to claim 8, wherein the second reinforcing fibres are introduced into the matrix in the form of a fibre fabric or fibre mesh, in one layer or in a plurality of layers, in the form of a fibre pad or in the form of individual fibres, wherein the second reinforcing fibres are orientated uniformly or randomly in all three spatial directions or have a preferred orientation in one or two spatial direction(s).