ICE PROTECTION FOR AIRCRAFT USING ELECTROACTIVE POLYMER SURFACES

• US 20130299637A1
• Filed: 05/08/2012
• Published: 11/14/2013
• Est. Priority Date: 05/08/2012
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Hoffenberg, Robert
• Application Number:
  US13/466,912
• Publication Number:
  US 20130299637A1
• Time in Patent Office: Days
• US Class Current: 244/134.A
• CPC Class Codes: B64D 15/163 using electro-impulsive devices

Abstract

An electro-active polymer (EAP) surface having a plurality of actuators adapted to prevent the formation of ice on an external surface, such as a leading edge of an aircraft. The EAP surface may also be adapted to remove ice formed on the external surface. The actuators of the EAP surface may be oscillated to prevent and/or remove ice from the surface of an aircraft. A signal generator may be used to individually oscillate the actuators in a first mode to prevent the formation of ice and a second mode to break up ice formed on the EAP surface. The signal generator may oscillate all of the actuators at the same frequency, may individually oscillate the actuators to form a pattern on the EAP surface, or may individually oscillate the actuators to form a wave along the EAP surface. The actuators may be dimple actuators, wrinkle actuators, and/or bump actuators.

Claims

1. A method of protecting an external surface from ice, the method comprising:

preventing the formation of ice on an external surface by oscillating at least a portion of a plurality of actuators on an electro-active polymer (EAP) surface.

2. The method of claim 1 further comprising applying the EAP surface to the external surface.

3. The method of claim 1 further comprising detecting conditions conducive to a formation of ice.

4. The method of claim 3 further comprising sending a signal to a signal generator to oscillate at least the portion of the plurality of actuators based on detecting conditions conducive to the formation of ice.

5. The method of claim 1, wherein the external surface is a leading edge of an aircraft.

6. The method of claim 1 further comprising oscillating each of the plurality of actuators at the same frequency to prevent the formation of ice on the external surface.

7. The method of claim 6 further comprising oscillating each of the plurality of actuators at a frequency between about 1 Hz to about 1 kHz.

8. The method of claim 1, wherein the actuators are dimple actuators, bump actuators, or wrinkle actuators.

9. The method of claim 1 further comprising individually oscillating a portion of the plurality of actuators to form a pattern on the external surface to prevent the formation of ice on the external surface.

10. The method of claim 1 further comprising individually oscillating the plurality of actuators to form a wave on the external surface to prevent the formation of ice on the external surface.

11. The method of claim 1 further comprising:

detecting the formation of ice on the external surface;

sending a signal to a signal generator based on the detection of the formation of ice; and

oscillating at least a portion of the actuators to remove the formation of ice from the external surface.

12. The method of claim 11 further comprising oscillating each of the plurality of actuators at the same frequency to remove the formation of ice from the external surface.

13. The method of claim 12 further comprising individually oscillating a portion of the plurality of actuators to form a pattern on the external surface to remove the formation of ice from the external surface.

14. The method of claim 11 further comprising individually oscillating the plurality of actuators to form a wave on the external surface to remove the formation of ice from the external surface.

15. An ice protection system for an external surface comprising:

an electro-active polymer (EAP) surface having a plurality of actuators; and

a signal generator connected to the EAP, the signal generator adapted to individually oscillate each of the plurality of actuators.

16. The system of claim 15, wherein the external surface comprises an external surface of a vehicle.

17. The system of claim 16, wherein the external surface is a leading edge of an aircraft.

18. The system of claim 15, wherein the plurality of actuators are dimple actuators, bump actuators, or wrinkle actuators

19. The system of claim 15, wherein the signal generator is adapted to oscillate the plurality of actuators in a first mode to prevent the formation of ice on the external surface of the aircraft and to oscillate the plurality of actuators in a second mode to remove ice formed on the external surface of the aircraft.

20. The system of claim 19, wherein the first mode oscillates each of the plurality of actuators at a first frequency and the second mode oscillates each of the plurality of actuators at a second frequency.

21. The system of claim 19, wherein the first mode individually oscillates a portion of the plurality of actuators to form a first pattern and the second mode individually oscillates a portion of the plurality of actuators to form a second pattern.

22. The system of claim 19, wherein the first mode individually oscillates the plurality of actuators to form a first wave and the second mode individually oscillates the plurality of actuators to form a second wave.

23. The system of claim 15 further comprising a sensor adapted to detect the formation of ice on the external surface of the aircraft.