Linkage assemblies for moving tabs on control surfaces of aircraft
Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.
1. An aircraft comprising:
a wing including:
a fixed wing portion;
a trailing edge control surface including:
a fore panel rotatably coupled to the fixed wing portion; and
an aft panel rotatably coupled to the fore panel; and
a linkage assembly including:
a rocking lever rotatably coupled to a bottom side of the fore panel;
a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever; and
an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.
2. The aircraft of claim 1 , wherein the trailing edge control surface is an aileron.
3. The aircraft of claim 2 , wherein the aft panel is a tab.
4. The aircraft of claim 1 , wherein the rocking lever has a first arm and a second arm extending in different directions.
5. The aircraft of claim 4 , wherein the second end of the trailing edge link is rotatably coupled to the first arm, and the first end of the aft panel link is rotatably coupled to the second arm.
6. The aircraft of claim 5 , wherein the rocking lever is rotatably coupled to the bottom side of the fore panel at an intersection of the first and second arms.
7. The aircraft of claim 6 , wherein the first and second arms are about 90° apart.
8. The aircraft of claim 6 , wherein the first arm is longer than the second arm.
9. The aircraft of claim 1 , wherein the trailing edge link is curved between the first and second ends of the trailing edge link.
10. The aircraft of claim 1 , wherein the first end of the trailing edge link is rotatably coupled to a rib in the fixed wing portion.
11. The aircraft of claim 1 , further including an actuator to rotate the fore panel upward or downward relative to the fixed wing portion.
12. The aircraft of claim 1 , wherein the aft panel is disposed in a notch in the fore panel.
13. The aircraft of claim 12 , wherein an aft edge of the fore panel and an aft edge of the aft panel are aligned when the trailing edge control surface is in a neutral position.
14. An aircraft comprising:
a wing including:
a fixed wing portion;
a trailing edge control surface including:
a fore panel rotatably coupled to the fixed wing portion; and
an aft panel rotatably coupled to the fore panel; and
an actuator to rotate the fore panel relative to the fixed wing portion; and
a linkage assembly coupled between the fixed wing portion, the fore panel, and the aft panel, the linkage assembly configured to rotate the aft panel downward relative to the fore panel when the fore panel is rotated downward by the actuator, and rotate the aft panel upward relative to the fore panel when the fore panel is rotated upward by the actuator.
15. The aircraft of claim 14 , wherein the linkage assembly includes:
a rocking lever rotatably coupled to a bottom side of the fore panel;
a trailing edge link coupled between the fixed wing portion and the rocking lever; and
an aft panel link coupled between the rocking lever and the aft panel.
16. The aircraft of claim 15 , wherein the rocking lever has a first arm and a second arm extending in different directions, and wherein the trailing edge link is coupled to the first arm, and the aft panel link is coupled to the second arm.
17. The aircraft of claim 14 , wherein the actuator is a linear actuator.
18. The aircraft of claim 17 , wherein the actuator has a movable rod, and wherein a distal end of the rod is coupled to the fore panel.
19. A method comprising:
activating an actuator to rotate a fore panel of a trailing edge control surface downward relative to a fixed wing portion of a wing of an aircraft, the trailing edge control surface including an aft panel rotatably coupled to the fore panel, the wing further including a linkage assembly coupled between the fixed wing portion, the fore panel, and the aft panel, wherein, when the actuator rotates the fore panel downward relative to the fixed wing portion, the linkage assembly rotates the aft panel downward relative to the fore panel; and
activating the actuator to rotate the fore panel upward relative to the fixed wing portion, wherein, when the actuator rotates the fore panel upward relative to the fixed wing portion, the linkage assembly rotates the aft panel upward relative to the fore panel.
20. The method of claim 19 , wherein the linkage assembly includes:
a rocking lever rotatably coupled to a bottom side of the fore panel;
a trailing edge link coupled between the fixed wing portion and the rocking lever; and
an aft panel link coupled between the rocking lever and the aft panel.