A method and system for actuating an aircraft component is disclosed including an actuating material in which an actual deformation change undergone by the actuating material in response to an activation input signal is determined by analysis of an output signal generated by the actuating material in response to the actual deformation. At least a portion of the aircraft component includes an actuating material which undergoes deformation in response to the application of an electrical signal thereto, and which generates an electrical signal in response to a deformation of the actuating material. The method includes applying an activation input signal to the actuating material of the aircraft component, the activation input signal corresponding to a desired deformation of the actuating material, the actuating material of the aircraft component undergoing an actual deformation in response to the activation input signal, and generating an output signal representative of the actual deformation of the actuating material.

Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.

This disclosure provides construction variants of a cruise miniflap of an aircraft wing that is added to trailing edge flap of an aircraft wing and can be used for improving the aerodynamic properties of an aircraft. In the rear edge of the cruise miniflap there is a cavity with a height of up to 1% of the wing chord.

A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

The present application relates to a pushing device, a moving mechanism and an aircraft. According to an aspect of the present application, a pushing device for a moving mechanism of an aircraft is provided, the moving mechanism including a primary moving device and an auxiliary moving device assisting the primary moving device, the pushing device including a support member and a pushing assembly supported by the support member, and the pushing assembly including a pushing element and an energy storage element. The pushing element is adapted to push a broken part of the auxiliary moving device to an offset position from a normal working position by means of energy from the energy storage element when the auxiliary moving device breaks. According to the present application, it is possible to provide an effective fault protection to the moving mechanism of the aircraft.

A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.

In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and/or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.

An aircraft wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.

A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.