Abstract: A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

Abstract: A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

Abstract: An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fiber reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fiber reinforced adhesive layer comprises fiber elements embedded in a matrix structure. One of the at least one fiber reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibers.

Abstract: A sheet entity, in particular for use as a skin panel for an aircraft fuselage, with a carbon fiber-reinforced plastic laminate and an aluminum-based metal laminate in the edge region, which are connected with one another by means of an adhesive bond, and thereby are electrically insulated from one another, and are stepped back by layers. Also disclosed is a fuselage cell of an aircraft with at least one sheet entity of this type.

Abstract: An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fibre reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fibre reinforced adhesive layer comprises fibre elements embedded in a matrix structure. One of the at least one fibre reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibres.

Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fiber-reinforced layer material or fiber metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fiber metal laminate or layer material is made of a plurality of metal layers and fiber-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fiber-reinforced adhesive layer.

Abstract: This invention provides a fuselage of an aircraft or space vehicle with a fuselage section having an outer skin, wherein at least the outer skin of the fuselage section consists of a glass-fiber reinforced aluminum laminate to form a safety zone for passengers in the event of a fire.

Abstract: A sheet entity, in particular for use as a skin panel for an aircraft fuselage, with a carbon fibre-reinforced plastic laminate and an aluminum-based metal laminate in the edge region, which are connected with one another by means of an adhesive bond, and thereby are electrically insulated from one another, and are stepped back by layers. Also disclosed is a fuselage cell of an aircraft with at least one sheet entity of this type.

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: The present invention provides a casing structure of low weight provided with a laminate stringer of high rigidity. The stringer has the form of a laminate with a plurality of metallic layers and at least one synthetic fiber layer, which is produced at least partially from Zylon fibers, provided between two metallic layers.

Abstract: A fiber metal laminate panel with a number of layers, arranged in the form of a laminate, of a planar metal material and a fiber material, the planar metal material being joined at splices by a metal-metal connection to overlapping metal layers, and, in reinforced regions which are used to attach the panel to a support structure with longitudinally extending support elements, additional layers of at least the planar metal material being provided. The additional metal layers reinforcing the panel are formed by overlapping metal-metal connections of the splices.

Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fibre-reinforced layer material or fibre metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fibre metal laminate or layer material is made of a plurality of metal layers and fibre-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fibre-reinforced adhesive layer.

Abstract: This invention provides a fuselage of an aircraft or space vehicle with a fuselage section having an outer skin, wherein at least the outer skin of the fuselage section consists of a glass-fibre reinforced aluminium laminate to form a safety zone for passengers in the event of a fire.

Abstract: The present invention provides a casing structure of low weight provided with a laminate stringer of high rigidity. The stringer has the form of a laminate with a plurality of metallic layers and at least one synthetic fibre layer, which is produced at least partially from Zylon fibres, provided between two metallic layers.

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: A fibre metal laminate panel with a number of layers, arranged in the form of a laminate, of a planar metal material and a fibre material, the planar metal material being joined at splices by a metal-metal connection to overlapping metal layers, and, in reinforced regions which are used to attach the panel to a support structure with longitudinally extending support elements, additional layers of at least the planar metal material being provided. The additional metal layers reinforcing the panel are formed by overlapping metal-metal connections of the splices.