Self-latching piezocomposite actuator

Patent metadata

Field	Value
Publication number	US-9741922-B2
Application number	US-201414571823-A
Country	US
Kind code	B2
Filing date	Dec 16, 2014
Priority date	Dec 16, 2013
Publication date	Aug 22, 2017
Grant date	Aug 22, 2017

Abstract

A self-latching piezocomposite actuator includes a plurality of shape memory ceramic fibers. The actuator can be latched by applying an electrical field to the shape memory ceramic fibers. The actuator remains in a latched state/shape after the electrical field is no longer present. A reverse polarity electric field may be applied to reset the actuator to its unlatched state/shape. Applied electric fields may be utilized to provide a plurality of latch states between the latched and unlatched states of the actuator. The self-latching piezocomposite actuator can be used for active/adaptive airfoils having variable camber, trim tabs, active/deformable engine inlets, adaptive or adjustable vortex generators, active optical components such as mirrors that change shapes, and other morphing structures.

First claim

The invention claimed is:

1. A method of controlling a self-latching piezocomposite actuator having a layer of shape memory ceramic fibers and first and second layers including conductive patterns disposed on opposite sides of the layer of shape memory ceramic fibers, the method comprising:
causing the layer of shape memory ceramic fibers to have a first strain state by at least partially poling the layer of shape memory ceramic fibers utilizing a first electric field that is induced by causing a voltage difference in the conductive patterns of the first and second layers;
followed by removing the voltage difference whereby the shape memory ceramic fibers remain in the first strain state;
followed by at least partially depoling the shape memory ceramic fibers utilizing a second electric field having a polarity that is substantially opposite a polarity of the first electric field to thereby cause the shape memory ceramic fibers to have a second strain state that is not equal to the first strain state;
and
wherein the shape memory ceramic fibers remain in the second strain state after the electric field is removed.

2. The method of claim 1 , wherein:
the shape memory ceramic fibers are fully poled in the first strain state.

3. The method of claim 2 , wherein:
the shape memory ceramic fibers are completely depoled in the second strain state.

4. The method of claim 3 , including:
determining a present strain state of the shape memory ceramic fibers;
determining a required intermediate strain state between the first and second states; and
causing the shape memory ceramic fibers to change from the present strain state to the required intermediate strain state by applying an electric field to the shape memory ceramic fibers.

5. The method of claim 1 , wherein:
the self-latching piezocomposite actuator defines a first curvature corresponding to the first strain state, and a second curvature that is not equal to the first curvature corresponding to the second strain state.

6. The method of claim 1 , wherein:
the piezocomposite actuator is operably coupled to a structure that is capable of changing shapes;
determining a desired change in shape of the structure;
temporarily applying an electrical field to the shape memory ceramic fibers to change the strain state of the piezocomposite actuator to cause the desired change in shape of the structure from a first shape to a second shape; and
wherein the structure maintains the second shape after the electric field is removed.

7. The method of claim 6 , wherein:
the structure comprises an airfoil and the first and second shapes define first and second cambers, respectively; and
the desired change in shape is determined, at least in part, on at least one of a desired lift and drag of the airfoil.

8. The method of claim 6 , wherein:
the structure comprises a reflector having a concave reflective surface defining the first and second shapes; and
determining the desired change in shape is determined based on a desired change in optical properties of the concave reflective surface.

9. The self-latching structure of claim 1 , wherein:
the shape memory ceramic fibers comprise a PZT-5H material.

10. A method of controlling the shape of a structure capable of defining at least first and second shapes, the method comprising:
providing a self-latching piezocomposite actuator comprising a plurality of aligned shape memory ceramic fibers defining first and second strain states;
operably connecting the self-latching piezocomposite actuator to the structure;
changing the strain state of the shape memory ceramic fibers from the first strain state to a second strain state by applying a first electrical field to the shape memory ceramic fibers such that the shape of the structure changes from the first shape to the second shape;
removing the first electrical field after the fibers are in the second strain state, wherein the actuator continues to maintain the structure in the second shape after the first electrical field is removed;
applying a second electrical field to the shape memory ceramic fibers to cause the shape memory ceramic fibers to change from the second strain state to a third strain state that is between the first and second strain states or equal to the first strain state, and wherein the structure defines a third shape corresponding to the third strain state that is between the first and second shapes or the same as the first shape, wherein the second electrical field has a reverse polarity relative to the first electric field;
maintaining the structure in the third shape by removing the second electrical field to maintain the shape memory ceramic fibers of the actuator in the third strain state.

11. The method of claim 10 , including:
applying one or more electric fields to the fibers to control poling and depoling of the shape memory ceramic fibers to provide a predefined strain state between the first and second strain states.

12. The method of claim 10 , including:
utilizing one or more sensors to determine an existing shape of the structure;
determining a required shape of the structure;
applying an electric field to change the strain state of the fibers to a strain state that results in the structure changing to the required shape from the existing shape.

13. The method of claim 10 , wherein:
the fibers comprise an 8/65/35 PLZT material.

14. The method of claim 10 , wherein:
the structure comprises an aircraft wing having a layer of flexible material defining an aerodynamic surface; and including:
actuating the actuator to control at least one of lift and drag by changing the shape of the flexible material.

15. The method of claim 10 , wherein:
the structure includes a first portion and a control surface movably connected to the first portion; and including:
actuating the actuator to control the position of the control surface relative to the first portion.

16. The method of claim 10 , wherein:
the structure comprises an inlet to an aircraft engine having a layer of flexible material defining an aerodynamic surface; and including:
actuating the actuator to control the shape of the inlet by changing the shape of the flexible material.

17. The method of claim 10 , wherein:
the structure comprises a mirror defining a reflective surface; and including:
actuating the actuator to control the shape of the reflective surface.

18. A method of controlling a self-latching piezocomposite actuator, the method comprising:
providing a self-latching piezocomposite actuator comprising a plurality of aligned shape memory ceramic fibers defining first and second strain states and a plurality of intermediate strain states between the first and second strain states;
determining a required intermediate strain state of the shape memory ceramic fibers corresponding to a required shape of a structure incorporating the actuator;
determining a present strain state of the shape memory ceramic fibers;
changing the strain state of the shape memory ceramic fibers from the present strain state to the required intermediate strain state by applying an electrical field to the shape memory ceramic fibers;
removing the electrical field after the fibers are in the required strain state, and wherein the shape memory ceramic fibers remain in the required strain state.

19. The method of claim 18 , including:
causing the shape memory ceramic fibers to change from the required strain state to the first strain state by applying a reverse polarity electrical field to

Assignees

• Nasa

Inventors

• Wilkie William K
• Bryant Robert G
• Lynch Christopher S

Classifications

• B64C27/72

  Means acting on blades · CPC title

• B64C3/48

  by relatively-movable parts of wing structures · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• G02B26/0858

  the reflecting means being moved or deformed by piezoelectric means · CPC title

• H01L41/082

  Electricity · mapped topic