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.

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.

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.

Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a discrete leading edge structure defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The discrete leading edge structure is coupled to the upper leading edge end of the upper skin panel and to the lower leading edge end of the lower skin panel. The upper skin panel may include a first panel bend adjacent the discrete leading edge structure, and the lower skin panel may include a second panel bend adjacent the discrete leading edge structure.

A wing includes: a main structural member; a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member; an eccentric bushing that has a circular through-hole and is shaped in a cylindrical shape; and a coupling member. The leading-edge member has a first hole prolonged in a specific direction. The main structural member has a second hole. The center axis of the eccentric bushing and the center axis of the through-hole are parallel to and offset from each other. The eccentric bushing is inserted to the first hole. The first coupling member is inserted to the through-hole and the second hole to couple the main structural member and the leading-edge member.

A wing includes: a main structural member; a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member; an eccentric bushing that has a circular through-hole and is shaped in a cylindrical shape; and a coupling member. The leading-edge member has a first hole prolonged in a specific direction. The main structural member has a second hole. The center axis of the eccentric bushing and the center axis of the through-hole are parallel to and offset from each other. The eccentric bushing is inserted to the first hole. The first coupling member is inserted to the through-hole and the second hole to couple the main structural member and the leading-edge member.

An aircraft structure protected from collisions with foreign objects includes a first support proximate to an aircraft structure root; first sheets attached to the first support to form a first leading edge portion of the aircraft structure; a second support proximate to an outer end of the aircraft structure; second sheets attached to the second support to form a second leading edge portion; and a door including one or more ribs disposed between the first and second supports and configured to give shape to a third leading edge portion of the aircraft structure; and third sheets, attached to the ribs to form the third portion of the leading edge; wherein the first support, the first sheets, the second support, the second sheets, the one or more ribs, and the third sheets are disposed to mitigate damage from a foreign object collision by absorbing kinetic energy from a collision.

An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.

An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.