Electrothermal wing ice protection system

1. An electro-thermal ice protection system for an aircraft with an electrical power system, surfaces with multiple heating zones each including multiple heating elements, which ice protection system comprises:

at least on master control unit (MCU) with an MCU processor, said MCU being connected to said power system and said heating elements;

said MCU being adapted to be programmed to selectively energize said heating elements;

said surfaces including a pair of wings;

multiple said heating zones interspaced throughout said surface, each heating zone being associated with a respective heating element;

a plurality of power control modules (PCMs) connected to said MCU, said PCMs including a PCM processor;

each said PCM associated with at least one said heating element;

each said PCM selectively instructed by said MCU to provide power to said associated heating element;

a communication link facilitating communication between said PCMs and said MCU;

a microcontroller adapted to interface major functional communication blocks communicating to and from said communication link;

said PCMs being functionally isolated from each other PCM such that the fault of one PCM does not affect the operation of remaining non-faulted PCMs;

each of said multiple PCMs being capable of feeding electrical output to a heating zone on a wing of an aircraft while simultaneously feeding electrical output to the complimentary heating zone on an opposing wing of the aircraft whereby said pair of aircraft wings are symmetrically heated;

solid-state switching within each of said multiple PCMs configured for proportional power control;

a dithering function in said MCU for increased control resolution of the proportional power control;

said PCM solid-state switching configured for implementing a zero-cross proportional power control scheme and reducing EMI emissions content and harmonic content;

a generator adapted to provide power to at least two of said multiple PCMs;

a coordinated synchronized power control scheme configured to minimize generator shock loads when said at least two PCMs are instructed to switch simultaneously;

said at least one MCU including an MCU microcontroller; and

wherein a hardware failsafe circuit is used to rapidly detect and isolate selected fault conditions independently from said microcontroller.

2. The system according to claim 1 , wherein said plurality of PCMs comprise modular elements which stack or scale to accommodate aircraft of varying sizes.

3. The system according to claim 1 , wherein said at least one MCU is enclosed in a single housing.

4. The system according to claim 1 , wherein said PCMs and MCU are arranged using a rack mount form factor.

5. The system according to claim 1 , wherein said PCMs and MCU are arranged using a card replaceable form factor.

6. The system according to claim 1 , wherein said microcontroller is used to provide fault diagnostics and reporting of major functional blocks within said MCU.

7. The system according to claim 1 , wherein desaturation detection in the solid state switch of the PCM is used to detect and isolate fault conditions.

8. The system according to claim 1 , wherein said PCM solid-state switch device temperature is monitored to detect and isolate fault conditions.

9. The system according to claim 1 , further comprising:

a delta-configured load is used in conjunction with a non-standard solid-state switch architecture; and

wherein said solid switch state results in reduced power dissipation.

10. The system according to claim 1 , wherein zone synchronization is provided through an interface connecting said multiple PCMs to said at least one MCU.

11. The system according to claim 1 , further comprising:

a current sensor capable of measuring current with a settling time less than three AC cycles.

12. The system according to claim 1 , further comprising:

a zone current sensor capable of measuring and reporting average current, imbalance current, and peak current.

13. The system according to claim 1 , further comprising:

a zone current sensor capable of detecting peak currents within a period of 10 micro-seconds or less; and

wherein said zone current sensor is further capable of reporting fault detection and isolation based upon said peak currents.

14. The system according to claim 1 , further comprising a composite heatsink construction adapted to provide thermal management and to reduce weight.

15. The system according to claim 1 , further comprising:

built-in test circuitry capable of providing fault detection of major functional blocks within said control unit.

16. The system according to claim 1 , further comprising:

said at least one MCU comprises;

a first MCU and a second MCU; and

wherein said first and second MCUs comprise a dual redundant design such that said second MCU is capable of activating upon the failure of said first MCU.

17. The system according to claim 16 , wherein said first and second MCUs are enclosed in a single housing.

18. The system according to claim 16 , further comprising:

wherein said first MCU is enclosed in a first housing; and

wherein said second MCU is enclosed in a second housing.

19. The system according to claim 1 , further comprising:

a voltage sensor adapted to measure and report the magnitude of supply voltage.

20. The system according to claim 19 , wherein said voltage is monitored at one or more of the times included in the list comprising:

on the input; between the isolation relay and solid-state switch; or after the solid state switch.

21. The system according to claim 19 , wherein one or more of the voltage sensor circuits are able to measure voltage with a settling time on the order of three AC cycles or less.

22. The system according to claim 1 , further comprising:

wherein said multiple PCMs are arranged into multiple PCM zones; and

wherein a plurality of input pins electronically encode a unique zone ID for each PCM zone.

23. The system according to claim 22 wherein parity is used to detect zone ID errors resulting from wiring errors or hardware failures.

24. The system according to claim 22 , wherein the Hamming method is used to detect zone ID errors resulting from wiring errors or hardware failures.