Wing for an aircraft having a flap with a speed brake panel mounted in a rotatable manner
A wing for an aircraft has a main wing and a trailing edge high lift assembly which has a flap and a connection assembly movably mounting the flap to the main wing. The connection assembly has a first actuator unit for moving the flap between the retracted position and at least one extended position. The flap has a leading edge part and a trailing edge part pivotably mounted to the leading edge. The flap has a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position.
1. A wing for an aircraft comprising:
a main wing; and
a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly comprising:
a flap; and
a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position,
wherein the connection assembly comprises a first actuator unit for moving the flap between the retracted position and the at least one extended position,
wherein the flap comprises a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis,
wherein the flap comprises a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position,
wherein the flap is configured to be brought into a speed brake setting where the trailing edge part is moved relative to the leading edge part beyond the upper operating position or beyond the lower operating position to a speed brake position,
wherein the flap comprises a speed brake panel mounted to the leading edge part or to the trailing edge part in a manner rotatable about a panel axis between a stowed position and a deployed position,
wherein the panel axis is located at a trailing edge end of the speed brake panel.
2. The wing according to claim 1 , wherein the connection assembly is configured such that the flap is movable relative to the main wing in a rotational manner.
3. The wing according to claim 2 , wherein the second actuator unit is formed as a linear actuator that is mounted to the leading edge part and mounted to the trailing edge part in a position spaced apart from the pivot axis.
4. The wing according to claim 1 , wherein the flap is configured such that the speed brake panel is in the stowed position when the trailing edge part is operated within the operating range, and such that the speed brake panel is in the deployed position when the trailing edge part is in the speed brake position.
5. The wing according to claim 4 , wherein the speed brake panel and the trailing edge part extend in opposite directions or in partly opposite directions when the speed brake panel is in the deployed position and the trailing edge part is in the speed brake position.
6. The wing according to claim 5 , wherein the flap comprises an actuation mechanism for moving the speed brake panel between the stowed position and the deployed position by transferring movement of the trailing edge part or of the second actuator unit to the speed brake panel.
7. A wing for an aircraft comprising:
a main wing; and
a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly comprising:
a flap; and
a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position,
wherein the connection assembly comprises a first actuator unit for moving the flap between the retracted position and the at least one extended position,
wherein the flap comprises a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis,
wherein the flap comprises a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position,
wherein the flap is configured to be brought into a speed brake setting where the trailing edge part is moved relative to the leading edge part beyond the upper operating position or beyond the lower operating position to a speed brake position,
wherein the connection assembly is configured such that the flap is movable relative to the main wing in a rotational manner,
wherein the second actuator unit is formed as a linear actuator that is mounted to the leading edge part and mounted to the trailing edge part in a position spaced apart from the pivot axis,
wherein the flap comprises a speed brake panel mounted to the leading edge part or to the trailing edge part in a manner rotatable about a panel axis between a stowed position and a deployed position,
wherein the flap is configured such that the speed brake panel is in the stowed position when the trailing edge part is operated within the operating range, and such that the speed brake panel is in the deployed position when the trailing edge part is in the speed brake position,
wherein the speed brake panel and the trailing edge part extend in opposite directions or in partly opposite directions when the speed brake panel is in the deployed position and the trailing edge part is in the speed brake position, wherein the flap comprises an actuation mechanism for moving the speed brake panel between the stowed position and the deployed position by transferring movement of the trailing edge part or of the second actuator unit to the speed brake panel,
wherein the panel axis is located at a trailing edge end of the speed brake panel.
8. The wing according to claim 7 , wherein the speed brake panel is mounted to the leading edge part.
9. The wing according to claim 7 , wherein the speed brake panel is mounted to the trailing edge part.
10. An aircraft comprising the wing and the trailing edge high lift assembly according to claim 1 .