High stiffness shape memory alloy actuated aerostructure

Patent metadata

Field	Value
Publication number	US-10202939-B2
Application number	US-201313855721-A
Country	US
Kind code	B2
Filing date	Apr 3, 2013
Priority date	Aug 6, 2009
Publication date	Feb 12, 2019
Grant date	Feb 12, 2019

Abstract

A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.

First claim

The invention claimed is:

1. A method for operating a shape memory alloy actuated aerostructure comprising a first face sheet and a second face sheet, the method comprising:
determining at least one characteristic of a shape memory alloy actuated aerostructure to be optimized;
determining a flight condition temperature based on current flight conditions;
controlling a shape memory alloy temperature of at least one portion of at least one shape memory alloy actuator to optimize the at least one characteristic, comprising controlling the shape memory alloy temperature of the least one portion to select and maintain a shape of the at least one shape memory alloy according to the determined flight condition temperature,
the at least one shape memory alloy actuator comprising a lattice of shape memory alloy metal, located between the first face sheet and the second face sheet, and coupled at substantially maxima of the at least one shape memory alloy actuator to the first face sheet at two or more locations on the first face sheet, and coupled at substantially minima of the at least one shape memory alloy actuator to the second face sheet at two or more locations on the second face sheet, wherein the first face sheet and the second face sheet are each made of materials that differ from the shape memory alloy metal; and
obtaining an optimum area for a variable area fan nozzle by morphing the shape memory alloy actuated aerostructure thereby reducing noise.

2. The method according to claim 1 , wherein the at least one characteristic is optimized based on at least one flight condition.

3. The method according to claim 1 , wherein the at least one characteristic comprises at least one member selected from the group consisting of: aerodynamic noise, aerodynamic drag, and aerodynamic lift.

4. The method according to claim 1 , wherein the controlling step further comprises:
monitoring the temperature of the at least one portion of the at least one shape memory alloy actuator; and
providing a temperature change by heating or cooling of the at least one portion of the at least one shape memory alloy actuator.

5. The method according to claim 1 , wherein the controlling step further comprises thermally controlling the at least one portion of the at least one shape memory alloy actuator to change an area of the variable area fan nozzle by morphing the shape memory alloy actuated aerostructure based on at least one flight condition.

6. The method according to claim 1 , wherein the controlling step further comprises adjusting at least one temperature for each of a plurality of sections of the at least one shape memory alloy actuator respectively.

7. The method according to claim 1 , wherein the controlling step further comprises:
thermally controlling the at least one shape memory alloy actuated aerostructure to extend into a flow path of a gas flow emitted from the variable area fan nozzle for a first set of flight conditions; and
thermally controlling the at least one shape memory alloy actuated aerostructure to extend away from the flow path for a second set of flight conditions.

8. The method according to claim 1 , further comprising extending the at least one shape memory alloy actuated aerostructure from a lip area of the variable area fan nozzle in proximity to a flow path of a gas flow emitted from the variable area fan nozzle.

9. The method according to claim 8 , further comprising deforming the at least one shape memory alloy actuated aerostructure between a first position in proximity to the flow path to a second position extending into the flow path.

10. The method according to claim 8 , further comprising deforming the at least one shape memory alloy actuated aerostructure from a first position in proximity to the flow path to a second position extending away from the flow path.

11. The method according to claim 1 , wherein:
the lattice comprises a sinusoidal strip of shape memory alloy metal; and
the at least one location and the two or more locations are located at substantially maxima and minima of the sinusoidal strip respectively.

12. The method according to claim 1 , wherein controlling the shape memory alloy temperature of at least one portion of at least one shape memory alloy actuator comprises heating the shape memory alloy actuator to a plurality of temperatures that include the shape memory alloy temperature.

13. A method for configuring a shape memory alloy actuated aerostructure comprising a first face sheet and a second face sheet, the method comprising:
configuring at least one shape memory alloy actuator comprising a lattice of shape memory alloy metal;
locating the at least one shape memory alloy actuator between the first face sheet and the second face sheet, wherein the first face sheet and the second face sheet are each made of materials that differ from the shape memory alloy metal;
coupling the at least one shape memory alloy actuator at substantially maxima of the at least one shape memory alloy actuator to the first face sheet at two or more locations on the first face sheet;
coupling the at least one shape memory alloy actuator at substantially minima of the at least one shape memory alloy actuator to the second face sheet at two or more locations on the second face sheet; and
configuring the shape memory alloy actuated aerostructure to morph to obtain an optimum area for a variable area fan nozzle thereby reducing noise generated by the variable area fan nozzle using a controller configured to control a shape memory alloy temperature of least one portion of the shape memory alloy actuated aerostructure to select and maintain a shape of the shape memory alloy actuated aerostructure according to a determined flight condition temperature.

14. The method according to claim 13 , further comprising configuring the at least one shape memory alloy actuated aerostructure to extend from a lip area of the variable area fan nozzle in proximity to a flow path of a gas flow emitted from the variable area fan nozzle.

15. The method according to claim 14 , further comprising:
configuring the at least one shape memory alloy actuated aerostructure to deform between a first position in proximity to the flow path to a second position extending into the flow path; and
configuring the at least one shape memory alloy actuated aerostructure to deform from the first position in proximity to the flow path to a third position extending away from the flow path.

16. The method according to claim 13 , further comprising:
configuring the lattice to comprise a sinusoidal strip of shape memory alloy metal; and
locating the at least one location and the two or more locations at substantially maxima and minima of the sinusoidal strip respectively.

17. The method according to claim 13 , further comprising coupling the shape memory alloy actuated aerostructure to at least one part of a thrust reverser sleeve.

18. The method according to claim 13 , further comprising coupling the shape memory alloy actuated aerostructure to at least one member selected from the group consisting of: a fan nozzle, and a core nozzle.

19. The method according to claim 13 , further comprising configuring the shape memory alloy actuated aerostructure to comprise at least one member selected from the group consisting of: a variable area fan nozzle panel, and a variable geometry chevron.

20. The method according to claim 13 , wherein configuring the shape memory alloy actuated aerostructure comprising heating the shape memory alloy actuat

Assignees

• Boeing Co

Inventors

• Widdle Richard D
• Grimshaw Matthew T
• Crosson-Eltruan Kava S
• Mabe James Henry
• Calkins Frederick T
• Gravatt Lynn Marie
• Shome Moushumi

Classifications

• B64C2027/7288

  of the memory shape type · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02K1/10 Primary

  by distorting the jet pipe or nozzle · CPC title

• F02K1/386

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F05D2300/505

  Shape memory behaviour · CPC title