Abstract: A composite radius filler for use in an aircraft structure. The aircraft structure includes structural composite parts assembled together to form the aircraft structure. The composite radius filler is arranged between rounded sections of the structural composite parts for filling a gap formed between the structural composite parts. The composite radius filler is made structural by a nanostructure arranged within the composite radius filler for the reinforcement of the interface between the radius filler and the structural composite part. A method for producing an aircraft structure including a nano-reinforced radius filler.

Abstract: A device for shaping of an article of composite material. The device includes a tool including a top surface and side surface for shaping at least one blank of composite material into an article having a predetermined profile; and a air-tight foil. The device further includes at least one support arranged to be in supporting contact with the underside of the protruding part of the blank.

Abstract: A method of attaching a first portion and a second portion to each other. An adhesive is exposed to a low temperature in order to obtain a non-tacky adhesive. The non-tacky adhesive is arranged between the two portions. The adhesive is cured. Use of adhesive according to the method.

Abstract: A method for manufacturing an elongate stiffening element and a rigid shell structure integrated with at least one elongate stiffening element. The method includes providing a preformed, form-stable reinforcement member, which has a hat profile with two inwardly directed, opposing flange portions, covering the reinforcement member with a curable composite material to form an external hat profile having outwardly directed flanges, and integrating this assembly with either a curable or preformed shell structure of composite material.

Abstract: A method of forming an article on a tool and an article. The tool has one longitudinal direction and one transversal direction. A stack of plies including fibers is arranged so that when positioned on the tool a ply arranged closest to the tool and a ply arranged furthest away from the tool have fibers substantially orthogonal to the longitudinal direction of the tool. At least one ply is arranged having the fibers substantially in a same direction as the longitudinal direction of the tool between the plies having fibers substantially orthogonal to the longitudinal direction of the tool. The stack is conformed to the tool with a forming medium. The article is removed from the tool.

Abstract: A method and device for shaping of an article of composite material. The method includes arranging a blank of composite material on a top surface of a forming tool. A portion of the blank is arranged to protrude outside the top surface of the tool. At least one support is arranged in contact with an underside of the protruding portion of the blank. An air-tight foil is arranged over the arrangement. The air-tight foil is forced towards the blank. The support is lowered until the blank is shaped over the tool. The support is stopped and/or removed. The device includes a tool including a top surface and side surface for shaping at least one blank of composite material into an article having a predetermined profile; and a air-tight foil. The device further includes at least one support arranged to be in supporting contact with the underside of the protruding part of the blank.

Abstract: A method of manufacturing a composite structure including a plurality of sheets and a radius filler. The radius filler is adapted to fill a gap at least partially formed by the sheets of the composite structure. The radius filler includes a plastic material with a first curing temperature. The sheets include a plastic material with a second curing temperature. The method includes arranging the sheets in a desired shape, applying the radius filler material into the gap, exposing the sheets and the radius filler material to the first temperature, whereby the material of the radius filler cures, and exposing the sheets and the radius filler to the second temperature, which exceeds the first temperature, whereby the material of the sheets cures. A radius filler for filling gaps between sheets of a composite structure. The material of the radius filler has a curing temperature which is below the curing temperature of the sheets of the composite structure.

Abstract: A tool assembly including a male tool including an inner shape tool including a bag having a connection connectable to a depressurization source for providing a vacuum in the bag such that beads therein form a body of firm cohesion providing the inner shape tool rigid. The male tool further includes a flexible, hollow curing support arranged around the rigid inner shape tool, the inner shape tool is arranged to be removable from the flexible, hollow curing support by rupturing the vacuum.

Abstract: A curved beam of fiber composite material. The beam includes a first flange curved in a longitudinal direction, a second flange curved in a longitudinal direction and having a greater longitudinal extent than the first flange, and a web curved in a longitudinal direction and extending between the first flange and the second flange. The beam includes a fiber composite laminate including layers of fibers having different fiber directions, wherein a fiber density per unit of area of the second flange is lower than a fiber density per unit of area of the first flange, and wherein the first flange, the second flange and the web are seamless, continuous, and unfolded in a longitudinal direction.

Abstract: A method for fabricating a curved beam from fiber composite material. A flat fiber composite laminate including a plurality of layers and at least two different fiber directions is formed. The fiber composite laminate is disposed in contact with a male tool includes a first flange, a second flange and an intermediate web. The male tool is curved in its longitudinal direction with a radius of curvature in such a way that the first flange has a shorter longitudinal extent than the second flange. The fiber composite laminate is brought into contact with and secured to the first flange of the male tool. The male tool and the fiber composite laminate are then rotated relative to one another so that the fiber composite laminate is brought into contact with the intermediate web of the male tool in a first rotational movement, and brought into contact with the second flange of the male tool in a second rotational movement.

Abstract: A tool assembly including a male tool including an inner shape tool including a bag having a connection connectable to a depressurization source for providing a vacuum in the bag such that beads therein form a body of firm cohesion providing the inner shape tool rigid. The male tool further includes a flexible, hollow curing support arranged around the rigid inner shape tool, the inner shape tool is arranged to be removable from the flexible, hollow curing support by rupturing the vacuum.

Abstract: The present invention relates to a method of manufacturing a composite structure (3) comprising a plurality of sheets (1, 2, 5) and a radius filler (6), wherein the radius filler is adapted to fill a gap (4) at least partially formed by the sheets of the composite structure. The radius filler comprises a plastic material with a first curing temperature (T1) and the sheets comprise a plastic material with a second curing temperature (T2). The method includes the steps of arranging the sheets in a desired shape, applying the radius filler material into the gap, exposing the sheets and the radius filler material to the first temperature (T1), whereby the material of the radius filler cures, and exposing the sheets and the radius filler to the second temperature (T2), which exceeds the first temperature (T1), whereby the material of the sheets cures. The invention also relates to a radius filler (6) for filling gaps (4) between sheets (1, 2, 5) of a composite structure (3).

Abstract: A method and device for shaping of an article of composite material. The method includes arranging a blank of composite material on a top surface of a forming tool. A portion of the blank is arranged to protrude outside the top surface of the tool. At least one support is arranged in contact with an underside of the protruding portion of the blank. An air-tight foil is arranged over the arrangement. The air-tight foil is forced towards the blank. The support is lowered until the blank is shaped over the tool. The support is stopped and/or removed. The device includes a tool including a top surface and side surface for shaping at least one blank of composite material into an article having a predetermined profile; and a air-tight foil. The device further includes at least one support arranged to be in supporting contact with the underside of the protruding part of the blank.

Abstract: A method and an apparatus for manufacturing of a curved elongated structural element of composite material. The curved elongated structural element includes a first elongated portion and a second elongated portion in an angled relation. A substantially flat blank of composite material including a first and second elongated edge is provided. The blank is folded over a first portion forming surface and a second portion forming surface of a forming tool's flexible tool body for forming the first elongated portion and the second elongated portion. The forming tool's tool body is bent such that its bending moment center prevails essentially adjacent the first portion forming surface.

Abstract: A method and an apparatus for manufacture of an elongated beam profile element including a recess configured to accommodate a support element. The method includes forming the blank into the web portion with at least one first protrusion formed to extend across the web portion and to protrude outward from the web portion's outer surface; and into the first flange portion with at least one second protrusion formed to extend across the first flange portion and to protrude inward from the first flange portion's inner surface, wherein this second protrusion merges into the first protrusion and constitutes the recess for accommodating the support element under a wing.

Abstract: A method and an apparatus for manufacturing of a profile element including a web portion, a first and second flange portion, which extend from the web portion and are disposed essentially opposite each other. The method includes folding a blank of composite material about a first and second flange forming surface of a forming tool. The method includes setting at least one flange forming surface of a forming tool a distance from another flange forming surface greater than a desired distance between inner surfaces of the flange portions of a finished profile element. The folded blank is cured and a gradual decrease of the distance between the flange forming surfaces is simultaneously controlled. The cured profile element is removed from the forming tool.

Abstract: A method for producing an object of composite material comprising the steps of: placing one or several prepregs on a plane surface, forming a fibre stack; lifting over the fibre stack to a moulding tool; downforming the fibre stack; curing the downformed fibre stack; where the method also comprises the step of: orienting the fibre directions so that all fibres, when the fibre stack is lifted over to the moulding tool, will cross an edge of the moulding tool only once.

Abstract: A method for producing an article of composite material comprising the steps of: providing a moulding tool of male type; placing one or several prepregs on the moulding tool, forming a fibre stack; placing a dry layer, e.g. fabric, externally on the fibre stack, forming a fibre stack having a dry surface; providing a moulding tool of female type; overturning or tilting the stack having a dry surface from the male tool to the female tool. The method may further comprise the step of arranging said dry fibre layer so that this comprises the edge of the fibre stack. The dry layer may be made of a metal net or other suitable metal structures, or be made of glass fibre fabric or another similar glass fibre structure, or a combination of glass fibre and metal. The fact that metal is an electrically conducting material and that glass fibre is an electrical isolator may be exploited, particularly when producing aircraft components.

Abstract: The present invention relates to a method for the fabrication of a former for manufacture of composite articles. The method is characterized by the following steps: forming a wetted water-soluble fiber composite on a master tool such that the fiber composite material lies against a surface area of the master tool, allowing the water-soluble fiber composite to dry on the master tool and removing the dry water-soluble fiber composite from the master tool, wherein the dry fiber composite forms the walls of the thus fabricated former.

Abstract: The present invention relates to a stiffening element (1) and a method for manufacturing of a stiffening element (1) of composite material, which stiffening element (1) is provided for attachment to a curved shell surface (9). A substantial flat blank (29) of composite material comprising a first (13) and a second (15) essentially parallel elongated edge is provided for forming in the web (3) of the stiffening element (1) at least one rounded bulge (19) having a conical form tapering from the first edge (13) to a first folding line (17). Thereby is achieved a curved flange (5), which first folding line (17) essentially merges with an apex of the rounded bulge (19).