Heater design for carbon allotrope ice protection systems
An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.
1. An ice protection system for an aircraft component comprising:
a first section of the aircraft component having a first span and a first chord;
a second section of the aircraft component, adjacent to the first section of the aircraft component, having a second span and a second chord, wherein the first section of the aircraft component and the second section of the aircraft component meet at a joint;
a junction section comprising:
an end portion of the first section of the aircraft component;
an end portion of the second section of the aircraft component adjacent to the end portion of the first section of the aircraft component, and
the joint;
a first plurality of heaters expanding spanwise across the first section of the aircraft component configured to heat the first section of the aircraft component;
a second plurality of heaters expanding spanwise across the second section of the aircraft component configured to heat the second section of the aircraft component;
a first H-shaped heater on the first section of the aircraft component expanding into the junction section, wherein the first H-shaped heater has at least one chordwise section connected to at least one spanwise section and the at least one chordwise section is positioned in the junction section close to the joint such that the at least one chordwise section is configured to heat the end portion of the first section of the aircraft component; and
a second H-shaped heater on the second section of the aircraft component, expanding into the junction section, wherein the second H-shaped heater has at least one chordwise section connected to at least one spanwise section and the at least one chordwise section is positioned in the junction section close to the joint such that the at least one chordwise section is configured to heat the end portion of the second section of the aircraft component.
2. The system of claim 1 , wherein the ice protection system is applied to a component selected from the group consisting of wing leading edges, vertical stabilizer leading edges, horizontal stabilizer leading edges, pylons, vanes, propellers, blades, engine inlets and surfaces requiring adjacent heaters.
3. The system of claim 1 , wherein the first and second H-shaped heaters each comprise two chordwise sections connected by a spanwise section.
4. The system of claim 3 , wherein each of the first and second H-shaped heaters further comprises a resistor on the spanwise section and two resistors on each of the chordwise sections.
5. The system of claim 1 , wherein each of the first and second H-shaped heaters comprises an electrical resistivity between 0.005 ohms per square (Ω/sq) and 3.0 Ω/sq.
6. The system of claim 1 , wherein the first and second H-shaped heaters each comprise a material selected from the group consisting of carbon nanotubes, graphene, graphene nanoribbons, and combinations thereof.
7. The system of claim 1 , wherein electrical power is constant throughout each of the first and second H-shaped heaters.
8. The system of claim 7 , wherein each of the first and second H-shaped heaters further comprises:
two positive electrical connections each at the end of a first chordwise section; and
two negative electrical connections each at the end of a second chordwise section.
9. The system of claim 1 , wherein electrical power is variable throughout each of the first and second H-shaped heaters.
10. The system of claim 9 , wherein each of the first and second H-shaped heaters further comprises:
a positive electrical connection at one end of a chordwise section; and
a negative electrical connection at the one end of the chordwise section.