Precipitation static charge drain system for an aircraft window

1. A static charge drain system for an aircraft window, comprising:

a resistive probe penetrating an outer ply of the aircraft window, a first end of the probe being exposed at an outer surface of the outer ply of the aircraft window, a second end of the probe penetrating an inner surface of the outer ply of the aircraft window;

a conductive drain element disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and being electrically connected between the second end of the probe and a ground point of the aircraft window; and

a heating element disposed between the outer ply of the aircraft window and the inner ply of the aircraft window,

wherein the heating element is electrically connected to the conductive drain element.

2. The static charge drain system of claim 1 , wherein the first end of the probe is substantially flush with the outer surface of the outer ply of the aircraft window.

3. The static charge drain system of claim 1 , wherein the conductive drain element comprises a conductive wire between the second end of the probe and the ground point of the aircraft window.

4. The static charge drain system of claim 1 , wherein the conductive drain element comprises a conductive film between the second end of the probe and the ground point of the aircraft window.

5. The static charge drain system of claim 4 , wherein the conductive film is a coating formed over the inner surface of the outer ply of the aircraft window.

6. The static charge drain system of claim 1 , wherein the heating element comprises a resistive film formed over the inner surface of the outer ply of the aircraft window.

7. The static charge drain system of claim 6 , wherein the second end of the probe penetrates the heating element into a region between the outer ply of the aircraft window and the inner ply of the aircraft window.

8. The static charge drain system of claim 1 , wherein the probe comprises at least one of plastic, epoxy, carbon, a metal, and a combination of any of plastic, epoxy, carbon, and a metal.

9. An aircraft window, comprising:

an outer ply;

an inner ply;

a resistive probe penetrating the outer ply, a first end of the probe being exposed at an outer surface of the outer ply, a second end of the probe penetrating an inner surface of the outer ply;

a conductive drain film electrically disposed between the outer ply and the inner ply and being electrically connected between the second end of the probe and a ground point of the aircraft window; and

a resistive heating film disposed between the outer ply of the aircraft window and the inner ply of the aircraft window wherein,

the resistive heating film is electrically connected to the conductive drain film.

10. The static charge drain system of claim 9 , wherein the first end of the probe is substantially flush with the outer surface of the outer ply.

11. The static charge drain system of claim 9 , wherein the conductive film is a coating formed over the inner surface of the outer ply.

12. The static charge drain system of claim 9 , wherein the second end of the probe penetrates the resistive heating film into a region between the outer ply and the inner ply.

13. The static charge drain system of claim 9 , wherein the probe comprises at least one of plastic, epoxy, carbon, a metal, and a combination of any of plastic, epoxy, carbon, and a metal.

14. The static charge drain system of claim 1 , wherein the probe comprises a resistance in the range of 1 Megohm to 10 Megohms.

15. The static charge drain system of claim 9 , wherein the probe comprises a resistance in the range of 1 Megohm to 10 Megohms.