System and method for reducing airfoil vortices

1. A system for reducing wake turbulence of an aircraft during flight along a flight direction, the aircraft having a wing including an outer wing portion, an extremity and a top, the system comprising:

a component configured to be attached to the top of the wing at the extremity of the wing of the aircraft so as to disturb a rolling action of air at the outer wing portion, the component comprising:

a fixed element;

a first hingeable wing element having a first inner surface and a second hingeable wing element having a second inner surface,

wherein the first and second hingeable wing elements are configured to be hingedly positionable to a first position in which the first inner surface is positioned side-by-side with the second inner surface and downstream of the fixed element, and configured to be hingedly positionable to a second position in which the first and second hingeable elements are folded out relative to each other in the flight direction; and

a central aircraft control system configured to control rotary movement of the first and second hingeable wing elements between an outer end position and an inner end position, such that in the outer end position the first wing element is folded outward at a first predetermined deflection angle in relation to an axis in the flight direction and the second wing element extends parallel to the flight direction, and such that in the inner end position the second wing element is folded inward at a second predetermined deflection angle in relation to the axis in the flight direction and the first wing element extends parallel to the flight direction.

2. The system of claim 1 , wherein the first and second hingeable wing elements in the first position extend so as to be parallel to the flight direction, and in the second position the first hingeable wing element is folded outward at a first predetermined deflection angle in relation to an axis of the flight direction, and the second hingeable wing element is folded inward at a second predetermined deflection angle in relation to the axis of the flight direction.

3. The system of claim 2 , wherein the first and second hingeable wing elements are configured such that hinging from time to time in the second position the first and second hingeable wing elements to and fro at a predetermined speed between the outer end position and the inner end position disturbs the rolling action of the air at the outer wing.

4. The system of claim 3 , wherein during the hingeing in the second position, the first and the second deflection angle are such that a coefficient of resistance of the wing remains constant.

5. The system of claim 3 , wherein the wing comprises a distal lateral edge, and in the outer end position the first hingeable wing element extends beyond the distal lateral edge of the wing when viewed from the top.

6. The system of claim 3 , wherein an angle between the first hingeable wing element and the second hingeable wing element remains fixed during the hingeing in the second position.

7. The system of claim 1 , wherein the wing comprises a distal lateral edge, and the component is positioned at the distal lateral edge of the wing.

8. The system of claim 1 , wherein in the first position the first hingeable wing element and the second hingeable wing element are positioned directly posterior to the fixed element of the component in the flight direction.

9. The system of claim 1 , wherein the first hingeable wing element comprises a leading edge and a trailing edge and the second hingeable wing element comprises a leading edge and a trailing edge, and

wherein in the first position the first inner surface and the second inner surface are positioned along a first plane on an axis of the flight direction, and in the second position at least one of the trailing edge of the first hingeable wing element and the trailing edge of the second hingeable wing element is swung away from the first plane while the leading edge of the first hingeable wing element and the leading edge of the second hingeable wing element remain directly behind the fixed element of the component.

10. The system of claim 1 , wherein the first hingeable wing element and the second hingeable wing element are hinged to the fixed element along a plane perpendicular to the flight direction.

11. The system of claim 1 , wherein during the rotary movement a relative position of the first hingeable wing element is maintained in relation to the second hingeable wing element.

12. The system of claim 1 , wherein during the rotary movement the central aircraft control system controls the deflection angles of the first and second hingeable wing elements such that a coefficient of resistance remains constant.