Anti-icing system for an aircraft
An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.
1. An anti-icing system for an aircraft comprising:
an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft, wherein the first exposed surface is located on an engine inlet, a booster, a splitter nose, an outer fan case, or a nacelle;
an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes; and
an insulation layer having opposing first and second sides, the second side being coupled to the first exposed surface of the aircraft.
2. The anti-icing system of claim 1 wherein the array of solar cells further comprises carbon nanotubes embedded within conducting polymers.
3. The anti-icing system of claim 1 wherein the array of solar cells is provided on a second exposed surface of the aircraft remote from the first exposed surface.
4. The anti-icing system of claim 1 further comprising a transmissive layer overlying the array of solar cells.
5. The anti-icing system of claim 1 further comprising a channel in the insulation layer, the channel having an inner surface spaced from the second side.
6. The anti-icing system of claim 5 wherein a heat-generating layer is positioned within the channel and coupled to the inner surface of the channel.
7. The anti-icing system of claim 6 wherein the array of carbon nanotubes is disposed within the heat-generating layer coupled to the inner surface of the channel.
8. The anti-icing system of claim 5 wherein at least a portion of the channel has a serpentine profile.
9. The anti-icing system of claim 1 wherein the array of carbon nanotubes is disposed within a heat-generating layer coupled to the insulation layer.
10. The anti-icing system of claim 9 further comprising an erosion protection layer coupled to the heat-generating layer.
11. The anti-icing system of claim 10 wherein the insulation layer comprises an insulation layer thickness, the heat-generating layer comprises a heating layer thickness, and the erosion protection layer comprises a protection layer thickness.
12. The anti-icing system of claim 11 wherein at least one of the insulation layer thickness, the heating layer thickness, and the protection layer thickness is between 200 and 1400 μm.
13. The anti-icing system of claim 11 wherein the heating layer thickness is at least twice as large as one of the insulation layer thickness or the protection layer thickness.
14. An aircraft, comprising:
at least one an aircraft component; and
an anti-icing system for an aircraft comprising:
an array of carbon nanotubes thermally coupled to at least a first exposed surface of the at least one aircraft component, the at least one aircraft component comprising at least one of an engine inlet, a booster, a splitter nose, an outer fan case, and a nacelle;
an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes; and
an insulation layer having opposing first and second sides, the second side being coupled to the first exposed surface of the aircraft.
15. The aircraft of claim 14 wherein the array of carbon nanotubes is thermally coupled to a first aircraft component and the array of solar cells is provided on a second aircraft component.
16. The aircraft of claim 14 wherein the at least one aircraft component comprises a carbon-filled epoxy composite material.
17. The aircraft of claim 14 wherein the array of solar cells further comprises carbon nanotubes embedded within conducting polymers.
18. A method of preventing ice formation on a surface of an aircraft, the method comprising:
supplying electrical power from an array of solar cells to an array of carbon nanotubes coupled to a first exposed aircraft surface, wherein an insulation layer having opposing first and second sides is coupled to the first exposed aircraft surface and the first exposed aircraft surface is located on an engine inlet, a booster, a splitter nose, an outer fan case, or a nacelle; and
transferring heat from the array of carbon nanotubes to the first exposed aircraft surface.
19. The method of claim 18 wherein the supplying electrical power further comprises supplying electrical power from an array of solar cells coupled with carbon nanotubes.
20. The method of claim 18 wherein the supplying electrical power further comprises supplying electrical power via carbon nanotubes electrically coupled to one of the array of solar cells or the array of carbon nanotubes coupled to the first exposed aircraft surface.
21. The method of claim 18 further comprising generating heat within a heat-generating layer having the array of carbon nanotubes.
22. The method of claim 21 wherein the supplying electrical power further comprises supplying electrical power to the heat-generating layer from the array of solar cells coupled to a second exposed aircraft surface remote from the first exposed aircraft surface.