Thermal actuation of riblets

Patent metadata

Field	Value
Publication number	US-9764824-B2
Application number	US-201514858600-A
Country	US
Kind code	B2
Filing date	Sep 18, 2015
Priority date	Sep 18, 2015
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

Thermal actuation of riblets is described herein. One disclosed example apparatus includes a riblet defining an aerodynamic surface of a vehicle. The disclosed example apparatus also includes a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle.

First claim

What is claimed is:

1. An apparatus comprising:
a riblet defining an aerodynamic surface of a vehicle; and
a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle, and wherein the thermal expansion element includes a negative thermal expansion material.

2. The apparatus as defined in claim 1 , further including apertures of the aerodynamic surface to allow the thermal expansion element to extend therethrough.

3. The apparatus as defined in claim 1 , further including a shape element to be displaced by the thermal expansion element when the thermal expansion element changes shape.

4. The apparatus as defined in claim 1 , further including an elastomeric film to expand and displace with the movable portion of the riblet when the movable portion of the riblet displaces relative to the aerodynamic surface.

5. The apparatus as defined in claim 1 , wherein the movable portion of the riblet is disposed beneath the aerodynamic surface and extends from the aerodynamic surface when the thermal expansion element expands.

6. The apparatus as defined in claim 1 , wherein the thermal expansion element includes one or more of a silicate material, zirconium tungstate material, or a cyanide-based material.

7. The apparatus as defined in claim 1 , wherein the thermal expansion element includes a negative thermal expansion liquid.

8. The apparatus as defined in claim 1 , wherein the thermal expansion element includes one or more of a film or a wire.

9. An apparatus comprising:
a thermal expansion element embedded within or proximate a riblet structure, wherein the riblet structure is to define an aerodynamic surface of a vehicle, wherein the thermal expansion element expands, based on temperature, to cause one or more of a movable portion of the riblet structure or the thermal expansion element to displace away from the aerodynamic surface to alter an aerodynamic characteristic of the vehicle, and wherein the thermal expansion element includes a negative thermal expansion material.

10. The apparatus as defined in claim 9 , wherein the thermal expansion element includes a fluid with expansion properties, wherein the fluid is stored in an expandable casing and expands as the fluid is cooled.

11. The apparatus as defined in claim 10 , wherein the fluid includes a derivative of hexa-peri-hexabenzocoronene.

12. The apparatus as defined in claim 9 , the thermal expansion element and the movable portion of the riblet structure are unitary.

13. The apparatus as defined in claim 9 , wherein the thermal expansion element causes a shape element of the riblet structure to alter a geometry of the riblet structure.

14. A method comprising:
using a thermal expansion element within or proximate a riblet structure; and
allowing the thermal expansion element to displace at least a portion of the riblet structure relative to an aerodynamic surface to alter an aerodynamic characteristic of a vehicle, wherein the thermal expansion element includes a negative thermal expansion material.

15. The method as defined in claim 14 , wherein the riblet structure further includes a protective layer or coating over the aerodynamic surface, wherein the thermal expansion element is to cause the protective layer to displace when the portion of the riblet structure displaces relative to the aerodynamic surface.

16. The method as defined in claim 15 , wherein the protective layer includes an elastomeric film.

17. The method as defined in claim 14 , wherein the thermal expansion element includes a negative thermal expansion liquid.

18. The method as defined in claim 14 , wherein the thermal expansion element pushes a shape element of the riblet structure to alter a geometry of the riblet structure.

Assignees

• Boeing Co

Inventors

• Song Weidong

Classifications

• B64C2230/26

  by using rib lets or hydrophobic surfaces · CPC title

• B64C2230/10

  by influencing fluid flow by heating using other means than combustion · CPC title

• B64C23/005

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title

• B64C21/10 Primary

  using other surface properties, e.g. roughness · CPC title

• B64C2003/148

  comprising protuberances, e.g. for modifying boundary layer flow · CPC title