Aircraft interior lining component and method for producing an aircraft interior lining component

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.

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.   
     
     
         2 . The aircraft interior lining component according to  claim 1 , wherein the matrix consists of a plastic material, in particular a plastic resin. 
     
     
         3 . The aircraft interior lining component according to  claim 1 , wherein the first reinforcing fibres comprise the same core material as the second reinforcing fibres. 
     
     
         4 . 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. 
     
     
         5 . 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. 
     
     
         6 . 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). 
     
     
         7 . 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). 
     
     
         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.   
     
     
         9 . The method according to  claim 8 , wherein the matrix is made from a plastic material, in particular a plastic resin. 
     
     
         10 . The method according to  claim 8 , wherein the first reinforcing fibres comprise the same core material as the second reinforcing fibres. 
     
     
         11 . 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. 
     
     
         12 . 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. 
     
     
         13 . 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). 
     
     
         14 . 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).