Precipitation Static Charge Drain System For An Aircraft Window

• US 20130087655A1
• Filed: 10/05/2012
• Published: 04/11/2013
• Est. Priority Date: 10/05/2011
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Cessna Aircraft Company (Textron Inc)
• Inventors: Eddy, Stephen
• Granted Patent: US 9,266,622 B2
• Time in Patent Office: Days
• US Class Current: 244/1.A
• CPC Class Codes: B64C 1/1492 Structure and mounting of the transparent elements in the window or windscreen
• CPC Class Codes: B64D 45/02 Lightning protectors; Static dischargers in general H01T

Abstract

A static charge drain system for an aircraft window includes 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 penetrates an inner surface of the outer ply of the aircraft window. A conductive drain element is disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and is electrically connected between the second end of the probe and a ground point of the aircraft window.

Claims

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; and

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.

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, further comprising a heating element disposed over the inner surface of the outer ply of the aircraft window.

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

8. The static charge drain system of claim 7, wherein the heating element is the conductive drain element.

9. The static charge drain system of claim 7, 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.

10. 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.

11. 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; and

a conductive drain element 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.

12. The static charge drain system of claim 11, wherein the first end of the probe is substantially flush with the outer surface of the outer ply.

13. The static charge drain system of claim 11, wherein the conductive drain element comprises a conductive wire between the second end of the probe and the ground point of the aircraft window.

14. The static charge drain system of claim 11, wherein the conductive drain element comprises a conductive film between the second end of the probe and the ground point of the aircraft window.

15. The static charge drain system of claim 14, wherein the conductive film is a coating formed over the inner surface of the outer ply.

16. The static charge drain system of claim 11, further comprising a heating element disposed over the inner surface of the outer ply.

17. The static charge drain system of claim 16, wherein the heating element comprises a resistive film formed over the inner surface of the outer ply of the aircraft window.

18. The static charge drain system of claim 17, wherein the heating element is the conductive drain element.

19. The static charge drain system of claim 17, wherein the second end of the probe penetrates the heating element into a region between the outer ply and the inner ply.

20. The static charge drain system of claim 11, 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.