Abstract: An assembly for guiding a cable between a structural part of an aircraft and a movable aerodynamic body includes a chain of pivotally connected links, a first coil device arranged between each pair of the links for guiding the cable between two angular positions, and a second coil device arranged at the first end of the chain for passing the cable from the chain to the aerodynamic body. The support of the assembly is statically determinate through the use of a bracket pivotally connected to one of the links at the structural part, which bracket does not permit a translative motion relative to the structural part. This is further supported by a bearing located at one of the links which is connected to the second coil device, which bearing permits angular rotation at least in two orthogonal directions, but no translative motion relative to the aerodynamic body.

Abstract: A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.

Abstract: A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.

Abstract: A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high- energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.

Abstract: A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.

Abstract: A wing assembly and method for operating the wing assembly, the assembly having a main wing and high-lift body movably coupled to the leading edge of the main wing, the coupling achieved by a driving device, an adjusting lever arrangement having a first main wing lever coupled to the main wing formed between a first adjusting lever pivot joint and the high-lift body as well as a second main wing lever coupled to the main wing so as to form an effective lever arm between a second adjusting lever pivot joint and a first adjusting lever pivot joint, and at least one adjusting lever non-rotatably coupled to the high-lift body, the high-lift body being movable between an initial position and a maximally adjusted position with respect to the initial position, at least one guide mechanism aiding movement of the high-lift body.

Abstract: A device and a method are disclosed for measuring sectional forces on a single-piece structural element in respect of a sectional plane by strain gauges, wherein a first and a second strain gauge of the plurality of strain gauges are arranged on a first outer wall, and a third and a fourth strain gauge are arranged on a second outer wall, with the result that, when the structural element is loaded with a first force, the change in length of the first and third strain gauges is opposite to the change in length of the second and fourth strain gauges, wherein the first outer wall and the second outer wall have, in the region of a cavity, at least three openings, which are separated from each other by webs, and wherein the first, second, third and fourth strain gauges are arranged on the webs.

Abstract: The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided.

Abstract: A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.

Abstract: An assembly for guiding a cable between a structural part of an aircraft and a movable aerodynamic body includes a chain of pivotally connected links, a first coil device arranged between each pair of the links for guiding the cable between two angular positions, and a second coil device arranged at the first end of the chain for passing the cable from the chain to the aerodynamic body. The support of the assembly is statically determinate through the use of a bracket pivotally connected to one of the links at the structural part, which bracket does not permit a translative motion relative to the structural part. This is further supported by a bearing located at one of the links which is connected to the second coil device, which bearing permits angular rotation at least in two orthogonal directions, but no translative motion relative to the aerodynamic body.

Abstract: A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap.

Abstract: An aerofoil wing with a main aerofoil, a high-lift flap movably arranged on the aerofoil wing by adjustment mechanisms. Each of the adjustment mechanisms including a first adjustment lever hinged to the main aerofoil via a first rotary linkage, with the formation of a first axis of rotation, a second adjustment lever hinged to the high-lift flap via a second rotary linkage, with the formation of a second axis of rotation, and a central linkage, with the formation of a third axis of rotation, such that the first, second and third axes of rotation pass through a common pole. The aerofoil wing further includes a drive device with a drive module mounted on the main aerofoil, and movable with respect to the drive module a drive lever coupled to the high-lift flap, and a stop device to limit the maximum extended setting of the high-lift flap.

Abstract: A wing of an aircraft provided with a main wing and an arrangement of leading edge lifting bodies, which as seen with reference to the incident flow direction are arranged on the leading edge, which are adjustably arranged on the main wing one behind another as seen in the spanwise direction of the main wing by means of respectively two positioning devices spaced apart from one another in the spanwise direction of the main wing. The wing has a connecting device, which is coupled to each of two adjacent leading edge lifting bodies, wherein the connecting device is configured such that in the event of a fracture of a positioning device of a positioning body external forces acting on the latter are transferred via the respective connecting device to the leading edge lifting bodies coupled up via the latter.

Abstract: An airfoil and method with a main wing and high-lift body on the leading edge of the main wing movable between an initial adjusting position and a maximally changed adjusting position referred to the initial adjusting position, with at least one guide mechanism. The high-lift body is movably coupled to the main wing and with a driving device. An adjusting lever arrangement and adjusting lever are coupled to the high-lift body. A first main wing lever coupled to the main wing is formed between the first adjusting lever pivot joint and the high-lift body, and a second main wing lever is coupled to the main wing such that an effective lever arm is formed between a second adjusting lever pivot joint and a first adjusting lever pivot joint.

Abstract: A device and a method are disclosed for measuring sectional forces on a single-piece structural element in respect of a sectional plane by strain gauges, wherein a first and a second strain gauge of the plurality of strain gauges are arranged on a first outer wall, and a third and a fourth strain gauge are arranged on a second outer wall, with the result that, when the structural element is loaded with a first force, the change in length of the first and third strain gauges is opposite to the change in length of the second and fourth strain gauges, wherein the first outer wall and the second outer wall have, in the region of a cavity, at least three openings, which are separated from each other by webs, and wherein the first, second, third and fourth strain gauges are arranged on the webs.

Abstract: A load introduction element for a movable surface of an aircraft comprises a load introduction body that is connectable with the surface. A fitting connected with the load introduction body with a first section and a second section. The first section comprises a first bearing means, the second section comprises a second bearing means, and the first or second section comprises a third bearing means. The fitting is pivotally connected with the load introduction body by way of the first bearing means. An adjustment unit connects the second bearing means with the load introduction body in a variable position and is positioned on a side of the load introduction body that is opposite the fitting. In this manner adjustment of a reference position of a surface takes place without the need for an access flap. By loosening the adjustment unit the movable surface is pivotable without moving a flap drive.

Abstract: A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.

Abstract: A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.

Abstract: A trailing-edge flap system is described. The trailing-edge flap system includes a trailing-edge flap and a movement device. The movement device includes at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.

Abstract: An mechanism for kinematic guidance of a body during its adjustment on a supporting structure. The body is moved between a refracted position and an extended position while performing a movement in a longitudinal direction in combination with a rotary movement. The mechanism includes first and second transmission levers for coupling to the supporting structure, a base connection lever to which these levers are coupled, third and fourth transmission levers coupled to the base connection lever, an adjusting lever coupled to the third and fourth transmission levers for attachment of the adjustable body, to adjust the body by a movement of the adjusting lever, and a coupling lever coupled to the first or second transmission lever and to the third or fourth transmission lever. During a movement of the adjusting lever, the first and second transmission levers each move opposite to the third and fourth transmission levers.