DUAL-CHANNEL DEICING SYSTEM FOR A ROTARY WING AIRCRAFT

• US 20180037328A1
• Filed: 09/01/2017
• Published: 02/08/2018
• Est. Priority Date: 04/06/2005
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Houlihan, Michael, Flemming, JR., Robert J., Daniele, Antonio G., Budd, Timothy R., Eisenhauer, Mark P.
• Granted Patent: US 10,457,403 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface
• CPC Class Codes: B64D 15/22 Automatic initiation by icing detector
• CPC Class Codes: H05B 1/0236 for vehicles

Abstract

A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly.

Claims

1. A method of deicing a rotary wing aircraft, comprising:

providing a first electrothermal heating element located along a leading edge of a main rotor blade over a stagnation line, a second electrothermal heating element located aft of the first electrothermal heating element along an upper surface of the main rotor blade, and a third electrothermal heating element located aft of the first electrothermal heating element along a lower surface of the main rotor blade; and

operating the third electrothermal heating element prior to the first electrothermal heating element, and the first electrothermal heating element prior to a second electrothermal heating element in response to a heating cycle defined by a controller, the heating cycle including an on-time and an off-time.

2. The method of claim 1, further comprising providing a fourth electrothermal heating element located aft of the third electrothermal heating element along the lower surface of the main rotor blade, the fourth electrothermal heating element operated by the controller subsequent to the second electrothermal heating element and prior to the third electrothermal heating element to define the heating cycle, the off time defined between the fourth electrothermal heating element and a repetition of the heating cycle.

3. The method of claim 1, wherein the first, second, third, and fourth electrothermal heating elements provide spanwise coverage from a 20% blade radius position to a 92% blade radius position of the main rotor blade span.

4. The method of claim 3, wherein the first and the second electrothermal heating elements provide chordwise coverage of 10% of an upper surface of the main rotor blade chord.

5. The method of claim 3, wherein the first, the third and the fourth electrothermal heating elements provide chordwise coverage of 17% of a lower surface of the main rotor blade chord.

6. The method of claim 1, wherein the on-time is a function of outside air temperature (OAT).

7. The method of claim 1, wherein the off-time is a function of liquid water content (LWC).

8. The method of claim 1, wherein the off-time corresponds to 60 seconds/LWC.

9. The method of claim 1, wherein the on-time is a linear function of outside air temperature.

10. The method of claim 1, wherein the off-time corresponds to 60 seconds/LWC and the on-time is a linear function of outside air temperature.

11. A method of deicing a rotary wing aircraft, comprising:

operating a plurality of electrothermal heating elements in response to a heating cycle defined by a controller, the heating cycle including an on-time and an off-time for each of the plurality of electrothermal heating elements, the off-time a function of liquid water content (LWC),

wherein the multiple of electrothermal heating elements are located adjacent a leading edge of a main rotor blade.

12. The method of claim 11, wherein the plurality of electrothermal heating elements includes:

a first electrothermal heating element located along a leading edge of the main rotor blade over a stagnation line;

a second electrothermal heating element located aft of the first electrothermal heating element along an upper surface of the main rotor blade; and

a third electrothermal heating element located aft of the first electrothermal heating element along a lower surface of the main rotor blade, the controller in communication with the first electrothermal heating element, the second electrothermal heating element and the third electrothermal heating element.

13. The method of claim 12, further comprising operating a fourth electrothermal heating element within the plurality of electrothermal heating elements subsequent to the second electrothermal heating element and prior to the third electrothermal heating element to define the heating cycle,

the off time defined between the fourth electrothermal heating element and a repetition of the heating cycle,

the fourth electrothermal heating element located aft of the third electrothermal heating element along the lower surface of the main rotor blade.

14. The method of claim 12, further comprising operating the third electrothermal heating element prior to the first electrothermal heating element, and operating the first electrothermal heating element prior to the second electrothermal heating element in response to the heating cycle defined by the controller.

15. The method of claim 11, wherein the on-time is a function of outside air temperature (OAT).

16. A method of deicing a rotary wing aircraft, comprising:

activating a plurality of electrothermal heating elements of a electrothermal heating element system in a sequential order, the plurality of electrothermal heating elements including a first electrothermal heating element located along a leading edge of a main rotor blade, a second electrothermal heating element located aft of the first electrothermal heating element along an upper surface of the main rotor blade, a third electrothermal heating element located aft of the first electrothermal heating element along a lower surface of the main rotor blade, and a fourth electrothermal heating element located aft of the third electrothermal heating element along the lower surface of the main rotor blade, the sequential order being the third electrothermal heating element, the first electrothermal heating element;

the second electrothermal heating element;

then the fourth electrothermal heating element.

17. The method of claim 16, wherein the activating is in response to a heating cycle communicated to the electrothermal heating element system, the heating cycle defining a first electric pulse train associated with a first set of main rotor blades, and further comprising repeating the heating cycle after an off-time.

18. The method of claim 17, further comprising determining the off-time in accordance with a non-linear function of liquid water content (LWC).

19. The method of claim 17, further comprising communicating a second electric pulse train subsequent to the first electric pulse train, the first electric pulse train associated with the first set of main rotor blades and the second electric pulse train associated with a second set of main rotor blades.

20. The method of claim 17, further comprising determining an element on-time for the first pulse train, the heater element on-time being a linear function related to outside air temperature (OAT).