Wing for an aircraft
A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.
1. A wing for an aircraft, comprising
a fixed wing,
a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended position and a folded position, and
an actuation unit for actuating the foldable wing tip portion for movement about the first hinge axis,
wherein the actuation unit comprises a link, a first linear actuator and a second linear actuator,
wherein the link is rotatably mounted to the fixed wing via a second hinge,
wherein the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced apart from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced apart from the second hinge, and
the second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced apart from the second hinge.
2. The wing according to claim 1 ,
wherein the second hinge defines a second hinge axis, the third hinge defines a third hinge axis, the fourth hinge defines a fourth hinge axis, the fifth hinge defines a fifth hinge axis, the sixth hinge defines a sixth hinge axis, and
wherein the second hinge axis, the third hinge axis, the fourth hinge axis, the fifth hinge axis, and the sixth hinge axis extend in parallel to the first hinge axis.
3. The wing according to claim 1 , wherein the second hinge axis coincides with the first hinge axis.
4. The wing according to claim 1 , wherein the link is formed such that the fourth hinge and the sixth hinge are spaced apart from one another and are equally spaced apart from the second hinge.
5. The wing according to claim 4 , wherein the link is shaped as a Y or a T.
6. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the folded position, the first linear actuator and the second linear actuator extend relative to one another with an angle of between 70° and 110°.
7. The wing according to claim 6 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of between 30° and 60°.
8. The wing according to claim 6 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of between 40° and 50°.
9. The wing according to claim 6 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of approximately 45°.
10. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the folded position, the first linear actuator and the second linear actuator extend relative to one another with an angle of, between 80° and 100°.
11. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the folded position, the first linear actuator and the second linear actuator extend relative to one another with an angle of approximately 90°.
12. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the extended position, the first linear actuator and the second linear actuator extend relative to one another with an angle of between 140° and 180°.
13. The wing according to claim 12 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of between 70° and 90°.
14. The wing according to claim 12 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of between 80° and 90°.
15. The wing according to claim 12 , wherein the link extends relative to at least one of the first linear actuator and the second linear actuator with an angle of approximately 85°.
16. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the extended position, the first linear actuator and the second linear actuator extend relative to one another with an angle of between 160° and 180°.
17. The wing according to claim 1 , wherein the actuation unit is formed such that, when the foldable wing tip portion is in the extended position, the first linear actuator and the second linear actuator extend relative to one another with an angle of approximately 170°.
18. The wing according to claim 1 , wherein the third hinge is spaced apart from the first hinge axis such that the third hinge is positioned further inbound and further below than the first hinge axis.
19. The wing according to claim 1 , wherein the fifth hinge is spaced apart from the first hinge axis such that the fifth hinge is positioned further outbound and further below than the first hinge axis.
20. An aircraft comprising the wing according to claim 1 .