Shape memory alloy actuator system for composite aircraft structures

Patent metadata

Field	Value
Publication number	US-9776705-B2
Application number	US-201414446187-A
Country	US
Kind code	B2
Filing date	Jul 29, 2014
Priority date	Jul 29, 2014
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A shape memory structure includes a plurality of bases directly attached to a composite structure and arranged along a first line at a first edge of the composite structure. A plurality of buckle-shaped shape memory structures are attached to corresponding ones of the plurality of bases, such that first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure. Second ends of the plurality of buckle-shaped shape memory structures are directly attached to the composite structure along a second line at a second edge of the composite structure, the second edge being opposite the first edge. When activated, the shape memory structure changes from a buckled shape to an original shape to cause the composite structure to assume a deployed shape; when deactivated, the shape memory structure to resumes a buckled shape and the composite structure an undeployed shape.

First claim

What is claimed is:

1. An apparatus comprising:
a composite structure of an aircraft;
a plurality of bases directly attached to the composite structure and arranged along a first line substantially at a first edge of the composite structure;
a plurality of buckle-shaped shape memory structures;
a plurality of first ends of the buckle-shaped shape memory structures, each first end of the buckle-shaped shape memory structures directly attached to a surface of a corresponding one of the plurality of bases such that the first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure;
a plurality of second ends of the buckle-shaped shape memory structures directly attached to the composite structure along a second line substantially at a second edge of the composite structure, the second edge being opposite the first edge, the second line being opposite the first line; and
a plurality of middle sections of the buckle-shaped shape memory structures, each middle section having a controllable curve.

2. The apparatus of claim 1 , wherein the plurality of buckle-shaped shape memory structures apply loads to the composite structure when the plurality of buckle-shaped shape structures are in an activated state.

3. The apparatus of claim 1 , wherein the plurality of buckle-shaped shape memory structures do not apply loads to the composite structure when the plurality of buckle-shaped shape structures are in a deactivated state.

4. The apparatus of claim 1 , wherein the plurality of buckle-shaped shape memory structures are unitary structures.

5. The apparatus of claim 1 , further comprising:
a plurality of additional shape memory structures disposed along the second line and alternating between corresponding ones of the plurality of second ends of the buckle-shaped shape memory structures.

6. The apparatus of claim 5 , wherein the plurality of buckle-shaped shape memory structures in an original shape causes the composite structure to have a group of desired values for a group of parameters, and wherein the group of parameters is selected from at least one of rigidity, stability, airflow, noise, vibration, lift, drag, and angle of attack.

7. The apparatus of claim 1 further comprising:
an activation system that causes the plurality of buckle-shaped shape memory structures to shift from a deactivated state to an activated state.

8. The apparatus of claim 7 , wherein the activation system includes at least one of a wire, a resistive element, a heating unit, a bleed air system, an electromagnetic induction unit, an infrared emitter, and a laser unit.

9. The apparatus of claim 1 , wherein the composite structure is selected from a group consisting of an airfoil, a control surface, a skin panel, a flap, an aileron, a wing tip, a trailing edge of a wing, a leading edge of the wing, a horizontal or vertical stabilizer, an engine nacelle, engine nozzles, spoilers, vortex generators, and a winglet.

10. The apparatus of claim 1 , wherein the plurality of buckle-shaped shape memory structures are comprised of a material selected from a group consisting of a shape memory metal alloy, a shape memory polymer, copper-aluminum-nickel, and nickel-titanium.

11. A method for controlling a shape of a composite structure of an aircraft using an apparatus, the apparatus comprising:
the composite structure having an original shape;
a plurality of bases directly attached to the composite structure and arranged along a first line substantially at a first edge of the composite structure;
a plurality of buckle-shaped shape memory structures;
a plurality of first ends of the buckle-shaped shape memory structures, each first end of the buckle-shaped shape memory structures directly attached to a surface of a corresponding one of the plurality of bases such that the first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure;
a plurality of second ends of the buckle-shaped shape memory structures directly attached to the composite structure along a second line substantially at a second edge of the composite structure, the second edge being opposite the first edge, the second line being opposite the first line; and
a plurality of middle sections of the buckle-shaped shape memory structures, each middle section having a controllable curve;

and wherein the method comprises:
activating the plurality of buckle-shaped shape memory structures to apply a load to the composite structure in a manner that deforms the composite structure from the original shape and into a predetermined curved shape.

12. The method of claim 11 , further comprising:
deactivating the plurality of buckle-shaped shape memory structures, whereby the load is removed, and the composite structure returns to the original shape.

13. The method of claim 12 , wherein the activating step and the deactivating step occur during different phases of flight.

14. The method of claim 12 , wherein the activating step occurs during take-off of an aircraft and the deactivating step occurs during cruising of the aircraft.

15. An aircraft comprising:
a composite wing;
a plurality of bases directly attached to the composite wing and arranged along a first line substantially at a first edge of the composite wing;
a plurality of buckle-shaped shape memory structures;
a plurality of first ends of the buckle-shaped shape memory structures, each first end of the buckle-shaped shape memory structures directly attached to a surface of a corresponding one of the plurality of bases such that the first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite wing;
a plurality of second ends of the buckle-shaped shape memory structures directly attached to the composite wing along a second line substantially at a second edge of the composite wing, the second edge being opposite the first edge, the second line being opposite the first line; and
a plurality of middle sections of the buckle-shaped shape memory structures, each middle section having a controllable curve.

16. The aircraft of claim 15 , wherein the plurality of buckle-shaped shape memory structures apply loads to the composite wing when the plurality of buckle-shaped shape structures are in an activated state.

17. The aircraft of claim 15 , wherein the plurality of buckle-shaped shape memory structures do not apply loads to the composite wing when the plurality of buckle-shaped shape structures are in a deactivated state.

18. The aircraft of claim 15 , wherein the plurality of buckle-shaped shape memory structures are unitary structures.

19. The aircraft of claim 15 , further comprising:
a plurality of additional shape memory structures disposed along the second line and alternating between corresponding ones of the plurality of second ends of the buckle-shaped shape memory structures.

20. The aircraft of claim 19 , wherein the plurality of buckle-shaped shape memory structures in an original shape causes the composite wing to have a group of desired values for a group of parameters, and wherein the group of parameters is selected from at least one of rigidity, stability, airflow, noise, vibration, lift, drag, and angle of attack.

Assignees

• Boeing Co

Inventors

• Dilligan Matthew Anthony
• Calkins Frederick T
• Zimmerman Tyler Jacob
• Mabe James Henry
• Blohowiak Kay Y

Classifications

• F03G7/0614

  using shape memory elements · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C3/48 Primary

  by relatively-movable parts of wing structures · CPC title

• F03G7/065

  using a shape memory element · CPC title

• B64C2003/445

  by changing shape according to the speed, e.g. by morphing · CPC title