Aircraft ice protection system and method
Ice protection systems of aircraft and related methods are disclosed. In one embodiment of the present invention, the system includes a gas-discharge lamp and an electric power source. The gas-discharge lamp is configured to emit infrared radiation toward an inner surface of an aircraft skin. The electric power source is operatively connected to the gas-discharge lamp.
1. An ice protection system for an aircraft, the system comprising:
a skin of the aircraft, the skin having an outer surface exposed to a flow of ambient air during operation of the aircraft, and an opposite inner surface;
an infrared radiation emitter configured to emit infrared radiation toward the inner surface of the skin; and
an electric power source operatively connected to the infrared radiation emitter,
wherein the infrared radiation emitter is configured to emit infrared radiation toward a surface of a structural member of the aircraft where the surface of the structural member is more reflective of the infrared radiation than the inner surface of the skin, and
wherein the structural member supports part of the skin.
2. The system as claimed in claim 1 , wherein the infrared radiation emitter is a xenon gas-discharge lamp.
3. The system as claimed in claim 1 , wherein the infrared radiation emitter is a krypton gas-discharge lamp.
4. The system as claimed in claim 1 , comprising:
a sensor configured to generate a feedback signal representative of a temperature of the skin; and
a controller operatively connected to the infrared radiation emitter and to the sensor, the controller being configured to control the infrared radiation emitter based on the feedback signal from the sensor.
5. The system as claimed in claim 4 , wherein the sensor comprises a pyrometer configured to generate a feedback signal representative of a temperature of the inner surface of the skin.
6. The system as claimed in claim 5 , wherein the pyrometer is thermally conductively coupled to the skin.
7. The system as claimed in claim 4 , wherein the controller is configured to cause a pulsed activation of the infrared radiation emitter, wherein the pulsed activation has a duration of less than one second.
8. The system as claimed in claim 1 , comprising a reflector configured to direct at least some of the infrared radiation emitted by the infrared radiation emitter toward the inner surface of the skin.
9. The system as claimed in claim 1 , wherein the inner surface of the skin is black in color.
10. The system as claimed in claim 1 , wherein the inner surface of the skin has a matte finish.
11. The system as claimed in claim 1 , wherein the inner surface of the skin comprises paint.
12. The system as claimed in claim 1 , wherein the inner surface of the skin comprises an anodic coating.
13. The system as claimed in claim 1 , wherein the surface of the structural member comprises a polished metal.
14. The system as claimed in claim 1 , wherein the surface of the structural member comprises a mirror finish.
15. The system as claimed in claim 1 , wherein the structural member comprises at least one of a spar, a stiffener, or a bulkhead.
16. The system as claimed in claim 1 , wherein the skin comprises a fiber-reinforced composite material.
17. The system as claimed in claim 1 , wherein at least some of the infrared radiation emitted by the infrared radiation emitter has a wavelength within a range of 3.8 μm to 4.3 μm.
18. The system as claimed in claim 1 , wherein at least some of the infrared radiation emitted by the infrared radiation emitter has a wavelength within a mid-infrared range.
19. The system as claimed in claim 1 , wherein at least some of the infrared radiation emitted by the infrared radiation emitter has a wavelength within a near-infrared range.