A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A wing for an aircraft includes: a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The connection assembly includes an elongate and curved slat track, wherein a first end section of the slat track is connected to the slat, a first bearing at least partly arranged outside the interior space of the main wing, a second bearing spaced apart from the first bearing and arranged within the interior space of the main wing. The slat track is movably and rotatably supported on the main wing by the first and second bearing, such that the first and second bearing support the predefined motion.

A wing for an aircraft includes: a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The connection assembly includes an elongate and curved slat track, wherein a first end section of the slat track is connected to the slat, a first bearing at least partly arranged outside the interior space of the main wing, a second bearing spaced apart from the first bearing and arranged within the interior space of the main wing. The slat track is movably and rotatably supported on the main wing by the first and second bearing, such that the first and second bearing support the predefined motion.

A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted to a flap support for rotation relative to a wing. A crankshaft assembly is rotatable about an axis and has a crankshaft eccentrically extending between an inboard cylindrical support and an outboard cylindrical support. A coupler link is rotatably engaged to the crankshaft and pivotally connected to the carrier beam. Rotation of the crankshaft from a first eccentric position to a second eccentric position translates the coupler link between a retracted position and a deployed position.

A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted to a flap support for rotation relative to a wing. A crankshaft assembly is rotatable about an axis and has a crankshaft eccentrically extending between an inboard cylindrical support and an outboard cylindrical support. A coupler link is rotatably engaged to the crankshaft and pivotally connected to the carrier beam. Rotation of the crankshaft from a first eccentric position to a second eccentric position translates the coupler link between a retracted position and a deployed position.

A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.

A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.