Method and apparatus for actively manipulating aerodynamic surfaces
A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
1. An apparatus for manipulating an aerodynamic surface, comprising:
a first linear actuator having a first fixed element and a first sliding element;
a second linear actuator having a second fixed element and a second sliding element;
a beam element connected on a first end to the first sliding element and connected on a second end to the second sliding element;
a pivot element connected to the beam element between the first sliding element and the second sliding element; and
an arm element coupled to the aerodynamic surface and having a first end connected to the beam element;
wherein the pivot element is offset from the beam element.
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. 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 counterbalanced by each other through a pivot element;
wherein the sliding elements are movably disposed within fixed elements and connected to a crank element, the crank element comprising a beam element offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
6. An aircraft, comprising:
a fuselage;
a wing having span-wise axis, a frame connected to the fuselage, and an active element;
a first linear actuator having a first stator element and a first sliding element;
a second linear actuator having a second stator element and a second sliding element;
a beam element connected on a first end to the first sliding element and connected on a second end to the second sliding element;
a pivot element connected to the beam element between the first sliding element and the second sliding element the pivot element being offset from the beam element; and
an arm element having a first end connected to the beam element and a second end connected to the active element;
wherein the first stator element and the second stator element are rigidly connected to the wing frame.
7. The aircraft of claim 6 , 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.
8. The aircraft of claim 6 , wherein the wing is rotatable about a hub connected to the fuselage.
9. The aircraft of claim 6 , 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.
10. The aircraft of claim 6 , wherein the first linear actuator and the second linear actuator are electromagnetic motors.
11. The apparatus of claim 6 , wherein the first linear actuator is aligned parallel to the second linear actuator.
12. The aircraft of claim 6 , wherein the first linear actuator is aligned in series with the second linear actuator.
13. The aircraft of claim 6 , 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.
14. The aircraft of claim 6 , 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 6 , 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.
16. The aircraft of claim 6 , 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.