The present invention relates to fiber composite plastic (11, 13) comprising a polymer (40, 41) and at least one textile (50), which has at least one palpably inhomogeneous surface (60, 61) with a textile structure and is entirely surrounded by polymer (40, 41), wherein the fiber composite plastic (11, 13) has at least one palpably inhomogeneous surface (60, 61), wherein inhomogeneities of this fiber composite plastic surface are caused by the textile structure, and a method for producing the fiber composite plastic (11, 13).

The present invention relates to fiber composite plastic (11, 13) comprising a polymer (40, 41) and at least one textile (50), which has at least one palpably inhomogeneous surface (60, 61) with a textile structure and is entirely surrounded by polymer (40, 41), wherein the fiber composite plastic (11, 13) has at least one palpably inhomogeneous surface (60, 61), wherein inhomogeneities of this fiber composite plastic surface are caused by the textile structure, and a method for producing the fiber composite plastic (11, 13).

A method and system for the characterization of equibiaxial compressive strength in 2D woven composites, such as carbon fiber reinforced laminate composites, is disclosed using induced biaxial flexure, the strain measurements from which are used to determine the equibiaxial compressive strength of the composite.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

The present invention discloses a foldable FRP plate, comprising a plurality of first regions and one or a plurality of second regions which are integrated in one piece; the second region is located between two adjacent first regions, so that the adjacent first regions being folded and unfolded relative to each other with the second region as a rotating shaft; the first regions are plate-like products manufactured by impregnating fiber woven fabric with resin for curing, are rigid and cannot be folded; the second region is flexible fiber woven fabric and has a width being two times a design thickness of the FRP plate. The present invention also discloses a manufacturing method, including laying the fiber woven fabric according to a design thickness and a layer layout; dividing the first regions and the second region according to an origami design method.

The present invention discloses a foldable FRP plate, comprising a plurality of first regions and one or a plurality of second regions which are integrated in one piece; the second region is located between two adjacent first regions, so that the adjacent first regions being folded and unfolded relative to each other with the second region as a rotating shaft; the first regions are plate-like products manufactured by impregnating fiber woven fabric with resin for curing, are rigid and cannot be folded; the second region is flexible fiber woven fabric and has a width being two times a design thickness of the FRP plate. The present invention also discloses a manufacturing method, including laying the fiber woven fabric according to a design thickness and a layer layout; dividing the first regions and the second region according to an origami design method.