A shape memory structure includes a plurality of bases directly attached to a composite structure and arranged along a first line at a first edge of the composite structure. A plurality of buckle-shaped shape memory structures are attached to corresponding ones of the plurality of bases, such that first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure. Second ends of the plurality of buckle-shaped shape memory structures are directly attached to the composite structure along a second line at a second edge of the composite structure, the second edge being opposite the first edge. When activated, the shape memory structure changes from a buckled shape to an original shape to cause the composite structure to assume a deployed shape; when deactivated, the shape memory structure to resumes a buckled shape and the composite structure an undeployed shape.

A shape memory structure includes a plurality of bases directly attached to a composite structure and arranged along a first line at a first edge of the composite structure. A plurality of buckle-shaped shape memory structures are attached to corresponding ones of the plurality of bases, such that first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure. Second ends of the plurality of buckle-shaped shape memory structures are directly attached to the composite structure along a second line at a second edge of the composite structure, the second edge being opposite the first edge. When activated, the shape memory structure changes from a buckled shape to an original shape to cause the composite structure to assume a deployed shape; when deactivated, the shape memory structure to resumes a buckled shape and the composite structure an undeployed shape.

The present disclosure relates to a sealing device and an associated flight control surface mechanism and an associated aircraft. According to an aspect of the present disclosure, a sealing device (100, 100′) for a flight control surface mechanism (10) of an aircraft (1) is provided, the flight control surface mechanism includes a fixed part (20) and a movable wing surface (40), the movable wing surface is attached to the fixed part in a manner of being movable relative to the fixed part. The sealing device includes a fixed seal (120) attached to the fixed part and a movable seal (140, 140′) attached to the movable wing surface so as to move with the movement of the movable wing surface, the movable seal and the fixed seal cooperate with each other in order to provide an aerodynamic sealing for the flight control surface mechanism.

A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in. Consequently there is no need to provide complex stiffening structures within the fairing element.

A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.

A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.

A control mechanism includes an existing aerodynamic device, such as a slat 5, that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18, such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4. The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

A control mechanism includes an existing aerodynamic device, such as a slat 5, that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18, such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4. The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a centralized drive device for centralized actuation control of an inboard high-lift surface of a first wing and a second wing, respectively, and at least two independent drive devices for individual actuation control of an outboard high-lift surface of the first wing and the second wing, respectively. The centralized drive device may include a central power drive unit (PDU) operably coupled to a common central driveline for driving the inboard high-lift surfaces, and the common central driveline may be separate and spaced apart from a respective driveline of the independent drive devices. The common central driveline may mechanically synchronize movement of the inboard high-lift surfaces, and a controller may electronically coordinate synchronized movement and controlled differential movement of the plurality of high-lift surfaces.

A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a centralized drive device for centralized actuation control of an inboard high-lift surface of a first wing and a second wing, respectively, and at least two independent drive devices for individual actuation control of an outboard high-lift surface of the first wing and the second wing, respectively. The centralized drive device may include a central power drive unit (PDU) operably coupled to a common central driveline for driving the inboard high-lift surfaces, and the common central driveline may be separate and spaced apart from a respective driveline of the independent drive devices. The common central driveline may mechanically synchronize movement of the inboard high-lift surfaces, and a controller may electronically coordinate synchronized movement and controlled differential movement of the plurality of high-lift surfaces.