Abstract: A device for the attachment of seats in passenger cabins of aeroplanes, road coaches, ships, railways, and similar, with at least one seat track, which has at least one exterior latching section, and with at least one holding device for purposes of attaching the seat to the at least one seat track. The at least one holding device has two integrated arms to engage around the latching sections and a multiplicity of teeth to fix it in position. The teeth can be moved in the vertical direction of the seat track. A seat track thermally is coated on at least some sections with exterior latching sections. A method is disclosed for the attachment of seats in passenger cabins.

Abstract: A method for producing a connecting element for at least two components of an aircraft structure. A hollow initial profile is formed comprising a wall following a closed path in the initial profile cross-section. The wall has a first, second and third section. Material is removed from the wall in one region of the initial profile, to obtain one opening in the one region, the opening extending at least partially within the first section. A portion of the second section and a portion of the third section form part of the connecting element and are each formed so as to be adapted to at least partially abut against the structure. The one opening is formed such that material initially forming part of the wall in the first section and remaining after the formation of the opening forms a stabilizing section connecting the portions of the second and third sections.

Abstract: In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type.

Abstract: The invention provides a stiffening element, in particular for a shell component of an aircraft or spacecraft, which has a stiffening profile part and a foot part. The stiffening profile part is in this case composed of a lightweight metal material, and the foot part is composed of a material which is highly resistant to corrosion. A method is also provided for production of a stiffening element, in particular for a shell component of an aircraft or spacecraft. A stiffening profile semi-finished product is first of all produced from a lightweight metal material, and a foot part is produced from a material which is highly resistant to corrosion. The foot part and the stiffening profile semi-finished product are then integrally connected. The stiffening profile semi-finished product together with the foot part is then subjected to machining to form an intended shape for the stiffening element.

Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component.

Abstract: A method for producing a connecting element for at least two components of an aircraft structure. A hollow initial profile is formed comprising a wall following a closed path in the initial profile cross-section. The wall has a first, second and third section. Material is removed from the wall in one region of the initial profile, to obtain one opening in the one region, the opening extending at least partially within the first section. A portion of the second section and a portion of the third section form part of the connecting element and are each formed so as to be adapted to at least partially abut against the structure. The one opening is formed such that material initially forming part of the wall in the first section and remaining after the formation of the opening forms a stabilizing section connecting the portions of the second and third sections.

Abstract: This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.

Abstract: An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region of the fuselage frame (11) and the main deck cross member (14), the fuselage frame (11) and a region (14a) of the main deck cross member (14) that spans at least an essential part of the width of the main deck and merges on both sides into the fuselage frame (11) being premanufactured in the form of an integral component.

Abstract: A device for the attachment of seats in passenger cabins of aeroplanes, road coaches, ships, railways, and similar, with at least one seat track, which has at least one exterior latching section, and with at least one holding device for purposes of attaching the seat to the at least one seat track. The at least one holding device has two integrated arms to engage around the latching sections and a multiplicity of teeth to fix it in position. The teeth can be moved in the vertical direction of the seat track. A seat track thermally is coated on at least some sections with exterior latching sections. A method is disclosed for the attachment of seats in passenger cabins.

Abstract: A seat rail for attaching seats in aircraft is provided. The seat rail includes a profile element for attaching the seats, and a support element for attaching the seat rail in an aircraft. At least the support element is manufactured from aluminum or an aluminum alloy. The surface of the aluminum or the aluminum alloy includes, an oxide layer, and the oxide layer has been manufactured by means of hard anodic oxidation.

Abstract: A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component.

Abstract: The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

Abstract: A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

Abstract: The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

Abstract: The present invention provides a floor structure for a fuselage comprising a plurality of cross beams to which respectively at least one first strut and at least one second strut are associated for connecting the respective cross beam to the fuselage. The at least one first strut is aligned in a corresponding first direction vector and the at least second strut is aligned corresponding to a second direction vector. The projections of the first direction vector and of the second direction vector onto the longitudinal direction of the fuselage are different for absorbing a force acting in the longitudinal direction of the fuselage on the floor structure, through the first and second struts.

Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: A door arrangement for tightly closing a door opening comprises a door frame, a door which, when closed, is arranged in the door frame, and inner and outer sealing lips. The inner and outer sealing lips run next to each other along a periphery of the door opening between a first surface of the door and a second surface of the door frame, wherein the first and second surfaces face each other. The inner and outer sealing lips bound a space formed between them. The door arrangement further comprises a pressure-reducing device configured to reduce pressure in the space.

Abstract: In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type.

Abstract: The present invention provides a stiffening element for stiffening a step-like substructure, in particular in an aircraft or spacecraft, having a foot section which is composed of a fiber composite material and is shaped in the form of a step such that it essentially fills the substructure. A method is also provided for production of a stiffening element for stiffening of a step-like substructure in an aircraft or spacecraft, according to which a profile part with a foot section which is composed of a carbon-fiber-reinforced plastic is provided, at least one layer of a glass-fiber-reinforced plastic is laminated onto the foot section, and the glass-fiber-reinforced plastic is milled corresponding to a step-like shape which essentially fills the substructure.