Vortex generator

Patent metadata

Field	Value
Publication number	US-11767104-B2
Application number	US-202217580934-A
Country	US
Kind code	B2
Filing date	Jan 21, 2022
Priority date	Apr 22, 2021
Publication date	Sep 26, 2023
Grant date	Sep 26, 2023

Abstract

A vortex generator, includes a vane, mountable on an aerodynamic surface of an aircraft, and an actuator that rotates the vane between a stowed position and a deployed position. The actuator includes a linear actuator, composed at least in part of a shape memory alloy (SMA), that when thermally activated facilitates rotation of the vane between the stowed position to the deployed position. Thermal activation of the SMA is caused via one or more of joule heating, conduction, and induction in response to one or more of an electronic command signal and a wireless command signal. The electronic command signal and the wireless command signal may be transmitted in response to ambient conditions, aircraft flight conditions, and aircraft mission.

First claim

What is claimed is:

1. An aircraft system, comprising:
a vortex generator that includes a vane, mountable on an aerodynamic surface of the aircraft for rotation between a stowed position and a deployed position, and an actuator module operatively connected to the vane, the actuator module including a linear actuator and a rotary actuator respectively composed at least in part of a shape memory alloy (SMA), wherein the linear actuator comprises a latch member, a bias member, and one or more wire members, wherein the latch member is operable to maintain the vane in the stowed position, wherein thermal activation of an SMA of the one or more wire members causes the latch member to alternate between disengagement and engagement by overcoming biasing force placed on the latch member by the bias member, and
a control module having one or more processors to execute a set of instructions that cause the one or more processors to conduct, in response to sensor data related to a flight environment of the aircraft and the vortex generator, flight environment analysis, and transmit, based on the flight environment analysis, a wireless command signal to cause thermal activation of the SMA to selectively move the vane between the stowed position and the deployed position.

2. The aircraft system of claim 1 , further comprising a sensor module, operatively coupled to the control module, to dynamically detect the flight environment of the aircraft and the vortex generator, wherein the flight environment comprises one or more of current flight altitude, current ambient temperature, current position of the vane, current deployment angle of the vane, and current aerodynamic load on the vane.

3. The aircraft system of claim 1 , wherein the vane comprises a substantially planar body having a recess formed at a side surface thereof.

4. The aircraft system of claim 3 , wherein:
the latch member being operable to engage the recess to maintain the vane in the stowed position, and the one or more wire members being operatively connected to the latch member, and
the rotary actuator comprises a substantially cylindrical body, composed of an SMA.

5. The aircraft system of claim 4 , wherein thermal activation of the SMA of the one or more wire members causes disengagement of the latch member from the recess and rotation of the vane from the stowed position and the deployed position.

6. The aircraft system of claim 4 , wherein thermal activation of the SMA of the substantially cylindrical body causes rotation of the substantially cylindrical body and rotation of the vane from the deployed position to the stowed position.

7. The aircraft system of claim 1 , further comprising:
a power source, including one or more rechargeable batteries, that is operatively connected to the control module and the actuator module; and
an energy harvesting module to deliver harvested energy to the one or more rechargeable batteries.

8. A vortex generator, comprising:
a vane, mountable on an aerodynamic surface of an aircraft for rotation between a stowed position and a deployed position; and
an actuator module operatively connected to the vane, the actuator module including a linear actuator and a rotary actuator respectively composed at least in part of a shape memory alloy (SMA) operable to, when thermally activated in response to a wireless command signal, selectively rotate the vane between the stowed position and the deployed position, wherein the linear actuator comprises a latch member, a bias member, and one or more wire members, wherein the latch member is operable to maintain the vane in the stowed position, wherein thermal activation of an SMA of the one or more wire members causes the latch member to alternate between disengagement and engagement by overcoming biasing force placed on the latch member by the bias member.

9. The vortex generator of claim 8 , wherein the wireless command signal is sent in response to an analysis of one or more of current flight altitude, current ambient temperature, current position of the vane, current deployment angle of the vane, and current aerodynamic load on the vane.

10. The vortex generator of claim 8 , wherein the vane comprises a substantially planar body having a recess formed at a side surface thereof.

11. The vortex generator of claim 10 , wherein:
the latch member being operable to engage the recess to maintain the vane in the stowed position, and the one or more wire members being operatively connected to the latch member, and
the rotary actuator comprises a substantially cylindrical body, composed of an SMA.

12. The vortex generator of claim 11 , wherein thermal activation of the SMA of the one or more wire members causes disengagement of the latch member from the recess and rotation of the vane from the stowed position and the deployed position.

13. The vortex generator of claim 11 , wherein thermal activation of the SMA of the substantially cylindrical body causes rotation of the substantially cylindrical body and rotation of the vane from the deployed position to the stowed position.

14. The vortex generator of claim 11 , further comprising:
a power source, including one or more rechargeable batteries, that is operatively connected to the actuator module; and
an energy harvesting module to deliver harvested energy to the one or more rechargeable batteries.

15. A method of operating an aircraft, the method, comprising:
dynamically detecting a flight environment of the aircraft and a vortex generator an aircraft and a vortex generator that is mountable on an aerodynamic surface of the aircraft, the vortex generator comprising a vane and an actuator module operatively connected to the vane, the actuator module including a linear actuator and a rotary actuator respectively composed at least in part of a shape memory alloy (SMA), wherein the linear actuator comprises a latch member, a bias member, and one or more wire members, wherein the latch member is operable to maintain the vane in a stowed position, wherein thermal activation of an SMA of the one or more wire members causes the latch member to alternate between disengagement and engagement by overcoming biasing force placed on the latch member by the bias member;
dynamically conducting, in response to the dynamic detection, a flight environment analysis; and
thermally activating on wireless command, based on the flight environment analysis, the SMA to selectively cause rotation of the vane between the stowed position and a deployed position.

16. The method of claim 15 , wherein the flight environment analysis is conducted on one or more of current flight altitude, current ambient temperature, current position of the vane, current deployment angle of the vane, and current aerodynamic load on the vane.

17. The method of claim 15 , wherein the vane comprises a substantially planar body having a recess formed at a side surface thereof.

18. The method of claim 17 , wherein the latch member being operable to engage the recess to maintain the vane in the stowed position.

19. The method of claim 18 , wherein:
the one or more wire members being operatively connected to the latch member, and
thermally activating the SMA comprises thermally activating the SMA of the one or more wire members to cause disengagement of the latch member and the recess and rotation of the vane from the stowed position and the deployed position.

20. The method of claim 15 , wherein:
the rotary actuator comprises a substantially cylindrical body, composed of an SMA, and
therm

Assignees

• Boeing Co

Inventors

• Calkins Frederick T
• Vijgen Paul M
• Nicholson Douglas E
• Fassmann Andrew Walter

Classifications

• B64C23/06 Primary

  by generating vortices · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C2230/00

  Boundary layer controls · CPC title