Carbon nanotube anti-icing and de-icing means for aircraft
View Patent ↗A system and method for anti-icing and de-icing an aircraft are provided. The system includes an electrically conductive coating, an electrical circuit having one or more electrical leads, a control unit, a plurality of temperature sensors connected to the control unit, and a plurality of ice detector sensors connected to the plurality of temperature sensors and the control unit. A process for anti-icing and de-icing an aircraft is also provided that includes applying electrically conductive coating under the skin of an airplane surface and attaching electrical wiring or metal strips to the skin of the airplane surface, and directing electricity to the electrical wiring or metal strips.
1. A system for anti-icing and de-icing an aircraft, the system comprising:
an electrically conductive coating or film;
an electrical circuit comprising one or more electrical leads, wherein the one or more electrical leads comprises either electrical wires or metal strips;
a carriage assembly having an upper carriage and a lower carriage, wherein the carriage assembly houses the one or more electrical leads, wherein the carriage assembly is bonded to a wing of the aircraft, wherein the one or more electrical leads is configured to be heated;
a control unit comprising a power supply and an electrical connector, wherein the electrical connector comprises a negative end and a positive end, wherein the negative end is connected to a corresponding negative end of an electrical lead of the one or more electrical leads, and wherein the positive end is connected to a corresponding positive end of said electrical lead;
a plurality of temperature sensors connected to the control unit; and
a plurality of ice detector sensors connected to said plurality of temperature sensors and said electrical connector.
2. The system of claim 1 , wherein the electrically conductive coating or film further comprise carbon nanotubes.
3. The system of claim 1 , further comprising a plurality of failsafe rib brackets, wherein the plurality of failsafe rib brackets add support to the upper carriage and the lower carriage of the carriage assembly.
4. The system of claim 1 , wherein the metal strips further comprise metal selected from any one of aluminum, copper, or stainless steel.
5. The system of claim 1 , wherein said electrically conductive coating or film is applied underneath a skin of a leading edge of an aircraft wing.
6. The system of claim 1 , wherein said electrically conductive coating or film is bonded underneath an outer skin of an aircraft wing, and further wherein the electrically conductive coating or film is bonded between the outer skin and an inner skin of a leading edge of the aircraft wing.
7. The system of claim 1 , wherein the control unit is affixed to a forward face of an aircraft wing's front spar.
8. The system of claim 1 , wherein the control unit is affixed to an aft face of a forward bulkhead of a forward ring of an engine inlet.
9. The system of claim 1 , wherein the electrically conductive coating or film comprises a mixture of silicon resin and carbon nanotubes.
10. The system of claim 1 wherein the electrically conductive coating or film comprises a mixture of graphene and polyurethane or carbon nanotubes and polyurethane.
11. The system of claim 1 , wherein said electrical circuit comprises a parallel circuit layout.
12. The system of claim 1 , wherein said electrical circuit comprises a simple circuit layout.