Abstract: The invention relates to a fastening unit (100) for movably fastening an aircraft component (300) to a support structure (400) of an aircraft (500). The fastening unit (100) has a connection element (5) having a hole (5a). The fastening unit (100) also has a first support arm (1) having a first end (1a) for connecting to the support structure (400) of the aircraft (500) and having a second end (1b) for connecting to the connection element (5). The fastening unit (100) also has a second support arm (2) having a first end in (2a) for connecting to the support structure (400) of the aircraft (500) and having a second end (2b) for connecting to the connection element (5).

Abstract: A control surface of an aircraft comprises a fixed skin panel, a first flexurally elastic skin panel and a second flexurally elastic skin panel, which is connected to the first flexurally elastic skin panel and is configured to at least partially overlap the fixed skin panel. Furthermore, the control surface comprises an actuator system, which is configured to move the second flexurally elastic skin panel parallel to the fixed skin panel, wherein the actuator system has a fixed structural element arranged in a root region of the control surface, and a structural element that is movable relative to the fixed structural element.

Abstract: An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.

Abstract: A control surface of an aircraft comprises a fixed skin panel, a first flexurally elastic skin panel and a second flexurally elastic skin panel, which is connected to the first flexurally elastic skin panel and is configured to at least partially overlap the fixed skin panel. Furthermore, the control surface comprises an actuator system, which is configured to move the second flexurally elastic skin panel parallel to the fixed skin panel, wherein the actuator system has a fixed structural element arranged in a root region of the control surface, and a structural element that is movable relative to the fixed structural element.

Abstract: An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.

Abstract: A structural component, in particular for an aircraft, having a skin and at least one stiffening element for stiffening the skin. Opposite to a run-out of the stiffening element at least one supporting element is positioned. The at least one supporting element defines a supporting area that is opened to the stiffening element run-out in longitudinal direction of the stiffening element run-out and that is closed in transversal direction of the stiffening element run-out.

Abstract: A structural component, in particular for an aircraft, having a skin and at least one stiffening element for stiffening the skin. Opposite to a run-out of the stiffening element at least one supporting element is positioned. The at least one supporting element defines a supporting area that is opened to the stiffening element run-out in longitudinal direction of the stiffening element run-out and that is closed in transversal direction of the stiffening element run-out.