Abstract: This disclosure relates to power sources that are structurally integrated with an airplane wing. The power sources include rechargeable batteries, such as Ni-Cd, NiMH, and/or Li-ion batteries; and/or hydrogen fuel cells. The power sources can be located on the airplane wing, inside of the wing, and/or located on the bottom of the wing, and combinations thereof. The airplane wing can be made of a metallic structural material or a composite structural material. Layers of a Li-ion battery can conformally overlay the upper metallic structural skin of a metallic wing, and the electrically-conductive metallic airplane wing itself acts as a cathode (or anode) of the battery. The airplane wing can be made of laminated sheets of carbon-fiber composites (CFCs). The power sources can be sandwiched inside of an upper and/or a lower section of the composite airplane wing. Lithium-ion batteries can be connected in series to provide a greater voltage.

Abstract: The aerospace component joints comprise a first component member comprising a first bonding face, a second component member comprising a second bonding face, one or more bond-enhancing features, and an adhesive layer forming a bond between the first and second bonding faces. The one or more bond-enhancing features comprises a plurality of reinforcing protrusions integral with the first component member, projecting from the first bonding face through the adhesive layer, and into the component member and/or one or more adhesive-receiving recesses defined in the first or second bonding faces and filled by the adhesive layer. The methods of preparing a component member for an aerospace component joint comprise integrating one or more bond-enhancing features into the component member. The methods of forming the aerospace component joint comprise positioning and adhesive-bonding the first bonding face to the second bonding face, and integrating the bond-enhancing feature(s) into the aerospace component joint.

Abstract: Systems and methods are provided for fabricating preforms for composite parts. One embodiment is a method of creating a preform. The method includes conveying a web of fiber reinforced composite material in a process direction, disposing fiber reinforced composite material atop the web, conveying the web and the tow in the process direction to a cutting tool, and cutting out a preform comprising a combination of the tow and the web.

Abstract: A structure and corresponding method of manufacturing are described, where the structure is fabricated via additive manufacturing. The structure includes a plurality of sub-structures integrally formed via additive manufacturing. The plurality of sub-structures provides the structure with at least three load paths in an instance in which a load is applied to the structure and is thus capable of continuing to support the load following failure of one of the sub-structures. In some cases, at least one sub-structure is designed to arrest propagation of a material failure of the structure resulting from the load.

Abstract: Systems and methods are provided for fabricating preforms for composite parts. One embodiment is a method of creating a preform. The method includes conveying a web of fiber reinforced composite material in a process direction, disposing fiber reinforced composite material atop the web, conveying the web and the tow in the process direction to a cutting tool, and cutting out a preform comprising a combination of the tow and the web.

Abstract: A composite component (110) for a vehicle seat (1), in particular a motor vehicle seat, having a plurality of fabric layers (116) of a fiber material and a matrix material (118) fixing the fabric layers (116). The outer component contour of the composite component (110) is at least in some sections formed by a fabric strand (125) embedded into the matrix material (118). A vehicle seat (1), in particular a motor vehicle seat, includes a composite component, in particular with a backrest structure (110) designed as the composite component.

Abstract: A composite component (110) for a vehicle seat (1), in particular for a motor vehicle seat, includes a plurality of fabric layers (116) of a fibrous material, a matrix material (118) securing the fabric layers (116), and an insert part (140), disposed between at least two of the fabric layers (116), for locally reinforcing the composite component. An insert strand (150) is disposed at least in sections along an edge or an edge surface (141.1) of the insert part (140). A vehicle seat (1) includes the composite component, in particular with a back structure (110) designed as a composite component.

Abstract: A composite component (110) for a vehicle seat (1), in particular a motor vehicle seat, having a plurality of fabric layers (116) of a fiber material and a matrix material (118) fixing the fabric layers (116). The outer component contour of the composite component (110) is at least in some sections formed by a fabric strand (125) embedded into the matrix material (118). A vehicle seat (1), in particular a motor vehicle seat, includes a composite component, in particular with a backrest structure (110) designed as the composite component.

Abstract: A composite component (110) for a vehicle seat (1), in particular for a motor vehicle seat, includes a plurality of fabric layers (116) of a fibrous material, a matrix material (118) securing the fabric layers (116), and an insert part (140), disposed between at least two of the fabric layers (116), for locally reinforcing the composite component. An insert strand (150) is disposed at least in sections along an edge or an edge surface (141.1) of the insert part (140). A vehicle seat (1) includes the composite component, in particular with a back structure (110) designed as a composite component.

Abstract: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Abstract: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Abstract: A method for making a window frame for installation in the exterior shell of an aircraft, which comprises at least one outer flange, an inner flange, and a vertical flange arranged perpendicular to and between these two flanges, contemplates that first a semifinished part comprising multiple, individual substructures is made, which next is inserted into a molding tool, into which, under pressure and temperature, resin is injected, and that the component made in this manner subsequently is hardened in the molding tool. The semifinished part has a layer structure, which comprises a web material, fiber bundles, or a combination of fiber bundles and web material.

Abstract: A window frame (1) for installation in the exterior (5) of an aircraft, which comprises in each case at least one outer flange (2), one inner flange, and one vertical flange (4) arranged perpendicular between these flanges, is manufactured from a fiber-reinforced synthetic resin, in which, first, a semifinished part comprising fiber material is inserted into a molding tool, in which, under pressure and temperature, resin is injected, and subsequently, the component made in this manner is hardened in the molding tool. The semifinished part can have a layer structure either made from a webbing material, from fiber bundles, or from a combination of fiber bundles and a webbing material.

Abstract: A window frame for installation in the exterior shell of an aircraft, which comprises one outer flange, an inner flange, and a vertical flange extending between flanges. A window frame is fixed in its position via a plurality of holder elements being arranged substantially equidistance from each other over the periphery of the window frame, being distributed on the outer flange of the window frame. Each of the holder elements comprises a base plate having a face, a pin, a pin extending outwardly from the face of the base plate and a pin to, a downholder clip. The clip may be adapted for a press fit engagement with the pin. The outer surfaces of the pin include a sawtooth-like structure, which engages with hook-shaped clamping elements flexibly formed on the downholder clip and over which an annular locking element is displaced. The holder elements may include a thermoplastic material, which may be provided with reinforcement fibers and may be die cast.

Abstract: A window frame (1) for installation in the exterior shell of an aircraft comprises in each case at least one outer flange (2), one inner flange (3), and one vertical flange (4) arranged perpendicular to and between these flanges (2, 3), wherein the connection with the aircraft structure (5) is realized via the outer flange (2) and wherein on the inner flange (3), a window element (7, 8) to be held is attached, which is held via the vertical flange (4). The window frame (1) comprises resin reinforced with unidirectionally arranged fiber bundles (20), wherein the progression of the fiber bundles in the three regions of the outer flange (2), inner flange (3), and vertical flange (4), respectively, follow the mechanical load direction. For manufacturing, a semifinished part made from unidirectionally arranged fiber bundles is inserted into a molding tool (11), in which, under pressure and temperature, resin is injected, and the component made in this manner is hardened subsequently in the molding tool(11).

Abstract: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Abstract: A method for making a window frame for installation in the exterior shell of an aircraft, which comprises at least one outer flange, an inner flange, and a vertical flange arranged perpendicular to and between these two flanges, contemplates that first a semifinished part comprising multiple, individual substructures is made, which next is inserted into a molding tool, into which, under pressure and temperature, resin is injected, and that the component made in this manner subsequently is hardened in the molding tool. The semifinished part has a layer structure, which comprises a web material, fiber bundles, or a combination of fiber bundles and web material.

Abstract: A window frame (1) for installation in the exterior shell of an aircraft comprises in each case at least one outer flange (2), one inner flange (3), and one vertical flange (4) arranged perpendicular to and between these flanges (2, 3), wherein the connection with the aircraft structure (5) is realized via the outer flange (2) and wherein on the inner flange (3), a window element (7, 8) to be held is attached, which is held via the vertical flange (4). The window frame (1) comprises resin reinforced with unidirectionally arranged fiber bundles (20), wherein the progression of the fiber bundles in the three regions of the outer flange (2), inner flange (3), and vertical flange (4), respectively, follow the mechanical load direction. For manufacturing, a semifinished part made from unidirectionally arranged fiber bundles is inserted into a molding tool (11), in which, under pressure and temperature, resin is injected, and the component made in this manner is hardened subsequently in the molding tool(11).

Abstract: A window frame (1) for installation in the exterior (5) of an aircraft, which comprises in each case at least one outer flange (2), one inner flange, and one vertical flange (4) arranged perpendicular between these flanges, is manufactured from a fiber-reinforced synthetic resin, in which, first, a semifinished part comprising fiber material is inserted into a molding tool, in which, under pressure and 2 temperature, resin is injected, and subsequently, the component made in this manner is hardened in the molding tool. The semifinished part can have a layer structure either made from a webbing material, from fiber bundles, or from a combination of fiber bundles and a webbing material.

Abstract: A window frame (1) for installation in the exterior shell (5) of an aircraft comprises at least one outer flange (2), an inner flange (3), and a vertical flange (4) arranged perpendicular to and between these flanges, whereby the connection with the aircraft structure takes place via the outer flange (2) and whereby on the inner flange (3), a window element to be held is attached, which is held via the vertical flange (4). The window frame (1) comprises resin reinforced with fiber web semifinished parts, whereby the progression of the layers of the webs in the three regions of the outer flange, inner flange, and vertical flange, respectively, follow the mechanical load direction. For manufacturing, a semifinished part (10) made from reinforced web (20, 21, 22) is inserted into a molding tool (11), in which, under pressure and temperature, resin is injected, and the component made in this manner is hardened subsequently in the molding tool.