Abstract: A method for manufacturing a profile rail including a base made of a first material and a top portion to be exposed during use of the profile rail in the floor of a vehicle including a second material that is harder and/or less corrosive as the first material. The method includes the steps of providing the base made of the first material, coating at least the top portion of the base with the second material by a cold spray process, and machining the coating to provide a predefined surface structure of the top portion.

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: A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.

Abstract: An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

Abstract: A shell component for an aircraft or spacecraft. The shell component includes a skin panel, a plurality of stringers which are arranged on the skin panel, a former which includes a fiber composite material and is arranged over the stringers so as to cross the stringers, and a former connection structure which includes a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers.

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: A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.

Abstract: An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

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: A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto.

Abstract: A transverse butt connection between two fuselage sections, more particularly for creating a fuselage cell for an aircraft, can have a number of stringers arranged spaced out uniformly parallel to one another inside on an outer skin. In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, both end areas of the fuselage sections can have on the inside oppositely inclined skin wedge surfaces and the connection of the two end areas is carried out by a circumferential transverse butt strap which is provided with two oppositely inclined transverse butt strap wedge surfaces in the underneath area wherein a wedge can be pushed in between each one transverse butt strap wedge surface and a skin wedge surface for tolerance compensation between the fuselage sections.

Abstract: The invention relates to an interconnection, including: a T-stringer which has a web portion and two foot portions; a ?-stringer which has a comb portion and two foot portions; and a connection arrangement which joins together the foot portions of the T-stringer and of the ?-stringer, wherein the connection arrangement joins together the T-stringer and the ?-stringer, wherein the connection arrangement has a first and a second connection element, the connection elements connecting a first foot portion of the T-stringer to a first foot portion of the ?-stringer, respectively, wherein the connection elements together have a substantially H-shaped outline, and wherein at least one angle bracket, in particular for connecting a former to the ?-stringer and the T-stringer, is connected to the widening foot portions of the first and second connection elements.

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: A connection arrangement for connecting a first and second reinforcing element of an aircraft or spacecraft, the reinforcing elements each have profiled cross-sections comprising at least one foot portion and at least one web portion. They are spaced from one another at their end connection faces by a strap element. The connection arrangement comprises at least one foot portion connection element, which can be adjusted and firmly joined on one side to the geometrical shape of the foot portion of the first reinforcing element, on the other side to the geometrical shape of the foot portion of the second reinforcing element and to the interposed strip element, and comprising at least one web coupling element, which can be adjusted and firmly joined on one side to the geometrical shape of the web portion of the first reinforcing element, and on the other side to the strap element.

Abstract: The present invention provides a shell component for an aircraft or spacecraft. The shell component comprises a skin panel, a plurality of stringers which are arranged on the skin panel, a former which comprises a fibre composite material and is arranged over the stringers so as to cross said stringers, and a former connection structure which comprises a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers.

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 an interconnection, in particular in the field of aerospace. The interconnection has a T-stringer, an ?-stringer and a connecting arrangement. The connecting arrangement connects base sections of the T-stringer and of the ?-stringer to one another. This provides a coupling of an ?-stringer to a T-stringer which is comparatively insensitive with respect to tolerances relating to the orientation of the ?-stringer in relation to the T-stringer.

Abstract: A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with in each case at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto in each case.

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.