Dual-channel deicing system for a rotary wing aircraft

• US 8,550,402 B2
• Filed: 04/06/2005
• Issued: 10/08/2013
• 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, Robert J. Jr., Daniele, Antonio G., Budd, Timothy R., Eisenhauer, Mark P.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US11/101,269
• Publication Number:
  US 20060226292A1
• Time in Patent Office: 3,107 Days
• Field of Search: 244/134.D, 244/134.R, 244/134.F
• US Class Current: 244/134.D
• 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 deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.

Claims

1. A main rotor blade assembly for a rotary-wing aircraft comprising:

a main rotor blade;

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

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

a third electrothermal heating element located aft of said first electrothermal heating element along a lower surface of said main rotor blade;

a controller in communication with said first electrothermal heating element, said second electrothermal heating element and said third electrothermal heating element, said third electrothermal heating element operated prior to said first electrothermal heating element and said first electrothermal heating element operated prior to said second electrothermal heating element in response to a heating cycle defined by said controller, said heating cycle includes an on-time and an off-time.

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

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

4. The main rotor blade assembly as recited in claim 1, wherein said first and said second electrothermal heating elements provide chordwise coverage of 10% of an upper surface of said main rotor blade chord.

5. The main rotor blade assembly as recited in claim 1, wherein said first, said third and said fourth electrothermal heating elements provide chordwise coverage of 17% of a lower surface of said main rotor blade chord.

6. The main rotor blade assembly as recited in claim 1, wherein said on-time is a function of outside air temperature (OAT).

7. The main rotor blade assembly as recited in claim 1, wherein said off-time is a function of liquid water content (LWC).

8. The main rotor blade assembly as recited in claim 1, wherein said off-time corresponds to 60 seconds/LWC.

9. The main rotor blade assembly as recited in claim 1, wherein said on-time is a linear function of outside air temperature.

10. The main rotor blade assembly as recited in claim 1, wherein said off-time corresponds to 60 seconds/LWC and said on-time is a linear function of outside air temperature.

11. A main rotor blade assembly for a rotary-wing aircraft comprising:

a main rotor blade;

a multiple of electrothermal heating elements located adjacent a leading edge of said main rotor blade;

a controller in communication with said multiple of electrothermal heating elements, said multiple of electrothermal heating elements operated in response to a heating cycle defined by said controller, said heating cycle includes an on-time and an off-time for each of said multiple of electrothermal heating elements, said off-time a function of liquid water content (LWC).

12. The main rotor blade assembly as recited in claim 11, wherein said multiple of electrothermal heating element includes:

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

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

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

13. The main rotor blade assembly as recited in claim 12, further comprising a fourth electrothermal heating element located aft of said third electrothermal heating element along said lower surface of said main rotor blade, said fourth electrothermal heating element operated by said controller subsequent to said second electrothermal heating element and prior to said third electrothermal heating element to define said heating cycle, said off time defined between said fourth electrothermal heating element and a repetition of said heating cycle.

14. The main rotor blade assembly as recited in claim 12, wherein said third electrothermal heating element is operated prior to said first electrothermal heating element, said first electrothermal heating element operated prior to said second electrothermal heating element in response to said heating cycle defined by said controller.

15. The main rotor blade assembly as recited in claim 11, wherein said on-time is a function of outside air temperature (OAT).

16. A rotary-wing aircraft comprising:

a multiple of main rotor blades;

a controller in communication with at least one electrothermal heating element on each of said multiple of main rotor blades, said at least one electrothermal heating element operated in response to a heating cycle defined by said controller, said controller operable to initiate said heating cycle simultaneously on a first main rotor blade of said multiple of main rotor blades and a second main rotor blade of said multiple of main rotor blades, said first main rotor blade opposite said second main rotor blade;

a first electrothermal heating element located along a leading edge of each of said multiple of main rotor blades over a stagnation line;

a second electrothermal heating element located aft of said first electrothermal heating element along an upper surface of each of said multiple of main rotor blades; and

a third electrothermal heating element located aft of said first electrothermal heating element along a lower surface of each of said multiple of main rotor blade;

said controller in communication with said first electrothermal heating element, said second electrothermal heating element and said third electrothermal heating element on each of said multiple of main rotor blades, said third electrothermal heating element operated prior to said first electrothermal heating element and said first electrothermal heating element operated prior to said second electrothermal heating element in response to said heating cycle defined by said controller.

17. The rotary-wing aircraft as recited in claim 16, wherein said multiple of main rotor blades further comprises a third main rotor blade and a fourth main rotor blade, said controller operable to initiate said heating cycle simultaneously on said third main rotor blade of said multiple of main rotor blades and said fourth main rotor blade of said multiple of main rotor blades, said third main rotor blade opposite said fourth main rotor blade.