Method and apparatus for actively manipulating aerodynamic surfaces

1. An apparatus for actuating a moveable member on a wing member, comprising:

a base;

a first linear actuator having a first fixed element and a first sliding element movable within the base;

a second linear actuator having a second fixed element and a second sliding element movable within the base;

a crank element coupled to a link element at a link attachment location, the link element extending approximately chordwise, the link element being operably associated with the moveable member;

a first sleeve element connected to the first sliding element and to the crank element;

a second sleeve element connected to the second sliding element and to the crank element;

a first flexure strap and a second flexure strap each connected to the base and to the crank element such that the first flexure strap and the second flexure strap diagonally cross each other at a pivot point, the pivot point being located an approximately spanwise distance from the link attachment location.

2. The apparatus of claim 1 , wherein the first linear actuator and the second linear actuator are electromagnetic actuators.

3. The apparatus of claim 1 , wherein the first linear actuator is aligned parallel to the second linear actuator.

4. The apparatus of claim 1 , wherein the first linear actuator is aligned in series with the second linear actuator.

5. The apparatus of claim 1 , wherein the first flexure strap is connected to the base at first beam attachment point and the second flexure strap is connected to the base at a second beam attachment point.

6. An aircraft, comprising:

a fuselage;

a wing having span-wise axis, a frame connected to the fuselage, and an active element; and

an actuator system connected to the frame and the active element, the actuator system having sliding elements movable along an axis parallel to the span-wise axis of the wing and a cross-axis flexure pivot element;

wherein the sliding elements are connected to fixed elements and a crank element, the crank element comprising a beam element offset from a pivot point of the cross-axis flexure pivot element so that the crank element is rotatable about the pivot point with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements; and

wherein the cross-axis flexure pivot element comprises a first flexure strap and a second flexure strap each connected to the base and to the crank element such that the first flexure strap and the second flexure strap diagonally cross each other at a pivot point.

7. An aircraft, comprising:

a fuselage;

a wing having a span-wise axis, a frame connected to the fuselage, and an active element;

a base connected to the frame;

a first linear actuator having a first fixed element connected to the base and a first sliding element movable within the base;

a second linear actuator having a second fixed element connected to the base and a second sliding element movable within the base;

a crank element;

a first sleeve element connected to the first sliding element and to the crank element;

a second sleeve element connected to the second sliding element and to the crank element;

a cross-axis flexure pivot element connected to the base and to the crank element at the sleeve elements; and

a link element connected on a first end to the crank element and on a second end to the active element.

8. The aircraft of claim 7 , wherein the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing.

9. The aircraft of claim 7 , wherein the wing is rotatable about a hub connected to the fuselage.

10. The aircraft of claim 7 , wherein the wing is rotatable about a hub connected to the fuselage and the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing.

11. The aircraft of claim 7 , wherein the first linear actuator and the second linear actuator are electromagnetic motors.

12. The apparatus of claim 7 , wherein the first linear actuator is aligned parallel to the second linear actuator.

13. The aircraft of claim 7 , wherein the first linear actuator is aligned in series with the second linear actuator.

14. The aircraft of claim 7 , wherein:

the wing is rotatable about a hub connected to the fuselage;

the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing; and

the first linear actuator is aligned parallel to the second linear actuator.

15. The aircraft of claim 7 , wherein:

the wing is rotatable about a hub connected to the fuselage;

the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing;

the first linear actuator is aligned parallel to the second linear actuator; and

the cross-axis flexure pivot element comprises an offset pivot point.

16. The aircraft of claim 7 , wherein:

the wing is rotatable about a hub connected to the fuselage;

the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing; and

the first linear actuator is aligned in series with the second linear actuator.

17. The aircraft of claim 7 , wherein:

the wing is rotatable about a hub connected to the fuselage;

the first sliding element and the second sliding element are aligned to be movable along an axis parallel to the span-wise axis of the wing;

the first linear actuator is aligned in series with the second linear actuator; and

the cross-axis flexure pivot element comprises an offset pivot point.