Metal mesh with a low electrical resistance conversion coating for use with aircraft structures

1. A gasket for use between aircraft parts under compression, the gasket comprising:

a moisture proof body comprising an elastomeric polymer with a tacky, outer surface configured to releasably contact at least one of the aircraft parts;

a metal skeleton encapsulated by the moisture proof body of the gasket;

wherein the metal skeleton includes an electrically conductive or semi-conductive conversion coating as an outer surface thereof; and

wherein, under compression, the moisture proof body deforms sufficiently to allow an aircraft part to contact the outer surface of the metal skeleton and provides electrical conductivity therethrough.

2. The gasket of claim 1 , wherein the moisture proof body is a tacky polyurethane gel and wherein the metal skeleton is an aluminum or aluminum alloy mesh and wherein a resistance of the coated aluminum or aluminum alloy mesh is less than about 2.5 milliohms.

3. The gasket of claim 1 , wherein the conversion coating is coated between about 100-250 mg/dm2.

4. The gasket of claim 1 , wherein the elastomeric polymer is a polyurethane gel.

5. The gasket of claim 1 , wherein the body includes conductive particles or fibers.

6. The gasket of claim 1 , including a second skeleton.

7. The gasket of claim 6 , wherein the second skeleton is a metallic mesh.

8. The gasket of claim 1 , wherein the body is comprised of a polyurea polymer.

9. The gasket of claim 1 , wherein the body is comprised of a tacky, deformable, flowable gel.

10. The gasket of claim 1 , wherein the metal skeleton has a perimeter and wherein, when under compression, the body extends beyond the perimeter of the skeleton.

11. The gasket of claim 10 , wherein the perimeter includes a cure in place injectable polymer.

12. The gasket of claim 1 , wherein a resistance of the skeleton is less than about 2.5 m·Ω.

13. The gasket of claim 1 , wherein the conversion layer comprises a chromium.

14. The gasket of claim 13 , wherein the chromium is part of a chromate.

15. The gasket of claim 14 , wherein the chromate includes trivalent chromium.

16. The gasket of claim 1 , wherein the conversion coating includes a hexafluorozirconate.

17. The gasket of claim 1 , wherein the body is a gel and includes corrosion inhibitors.

18. A method of producing a corrosion resistance assembly of aircraft parts comprising:

contacting an exterior of a skeleton with a composition comprising a reactive composition to obtain a conversion coating on a top surface coat on the skeleton surface and assembling the skeleton comprising said top surface coat into an aircraft gasket having an elastomeric body and placing the gasket under compression between two parts of an aircraft.

19. The method of claim 18 , wherein the skeleton is die cut before contacting.

20. The method of claim 18 , wherein before the placing step and after the contacting step, the skeleton is die cut into a preselected shape.

21. The method of claim 18 , wherein the reactive composition contains trivalent chromium.

22. The method of claim 18 , wherein the reactive composition contains hexavalent chromium.

23. The method of claim 18 , wherein the reactive composition contains chromium, either a trivalent or hexavalent chromium, and elastomeric body is a tacky gel body including a polyurethane or polyurea two component sealant.

24. An assembly of aircraft parts comprising:

a first aluminum or aluminum alloy part having a first surface;

a second aluminum or aluminum alloy part having a second surface;

a multiplicity of fasteners for engaging the two aluminum or aluminum alloy parts;

a gasket comprising a body comprising an elastomeric polymer; and

a metal skeleton encapsulated by the body of the gasket;

wherein the metal skeleton includes a conversion coating.

25. The assembly of claim 24 , wherein the two parts comprise an aircraft antenna and an aircraft skin.

26. The assembly of claim 24 , wherein the two parts comprise an aircraft fuel door surround and an aircraft fuel door.

27. A gasket for use between aircraft parts under compression, the gasket comprising:

a moisture proof body having an outer surface comprising an elastomeric polymer; and

a metal skeleton encapsulated by the moisture proof body of the gasket;

wherein the metal skeleton includes an electrically conductive or semi-conductive conversion coating comprising an outer surface thereof;

wherein the moisture proof body and the outer surface is comprised of a tacky, deformable, flowable gel which releasably contacts at least one of the aircraft parts;

wherein the resistance of the skeleton is less than about 2.5 m·Ω; and

wherein the skeleton contacts the aircraft parts when the body is under compression between the aircraft parts and provides electrical conductivity therethrough.

28. The gasket of claim 27 , wherein the conversion layer comprises a chromium.

29. The gasket of claim 28 , wherein the chromium is part of a chromate.

30. The gasket of claim 29 , wherein the chromate includes trivalent chromium.

31. The gasket of claim 27 , wherein the conversion coating includes a hexafluorozirconate.

32. The gasket in claim 1 , wherein the gasket leaves no significant visible corrosion after salt fog immersion test according to ASTM B117 after 500 hours.

33. The gasket in claim 1 , wherein the resistance of the skeleton is less than 2.5 m·Ω after salt fog immersion tests according to ASTM B117 after 500 hours.

34. The gasket in claim 1 , wherein the body includes corrosion inhibitors.

35. The gasket in claim 27 , wherein the gasket leaves no significant visible corrosion after salt fog immersion test according to ASTM B117 after 500 hours.

36. The gasket in claim 1 , wherein the resistance of the skeleton is less than 2.5 m·Ω after salt fog immersion tests according to ASTM B117 after 500 hours.

37. The gasket in claim 1 , wherein the body includes corrosion inhibitors.

38. The gasket in claim 1 , wherein the skeleton is an aluminum alloy.

39. The gasket in claim 38 , wherein the aluminum alloy is a 6000 series alloy.

40. The gasket in claim 38 , wherein the aluminum alloy is a 2000 series alloy.

41. The gasket in claim 38 , wherein the aluminum alloy is a 3000 series alloy.

42. The gasket in claim 38 , wherein the aluminum alloy is a 4000 series alloy.

43. The gasket in claim 38 , wherein the aluminum alloy is a 5000 series alloy.

44. The gasket in claim 1 , wherein the conversion coating is on an outer surface of an end of a wire of a skeleton having wire ends.

45. A gasket for use between aircraft parts under compression, the gasket comprising:

a moisture proof body comprising an elastomeric polymer with a tacky, outer surface configured to releasably contact at least one of the aircraft parts;

a metal skeleton substantially encapsulated by the moisture proof body of the gasket in an uncompressed state;

wherein the metal skeleton includes an electrically conductive or semi-conductive conversion coating on an outer surface thereof; and

wherein, under compression, the moisture proof body deforms sufficiently to allow the aircraft parts to contact the outer surface of the metal skeleton and provide electrical conductivity therethrough.

46. The gasket of claim 45 , wherein, under a nominal electrode pressure of about 200 psi, the conversion coated skeleton has less than 200 milliohms of resistance after 500 hours of exposure at 5% salt fog.

47. The gasket of claim 46 , wherein the conversion coating weight is 100-250 mg/dm2.

48. The gasket of claim 46 , wherein the conversion coating is a non-chromate conversion coating.

49. The gasket of claim 46 , wherein the conversion coating is a trivalent chromium conversion coating.

50. The gasket of claim 46 , wherein the skeleton is a cooper alloy skeleton.

51. The gasket of claim 46 , wherein the skeleton is a nickel alloy skeleton.

52. The gasket of claim 46 , wherein the skeleton is an aluminum alloy skeleton.

53. The gasket of claim 46 , wherein the body comprises a gel and the gel includes no corrosion inhibitors.

54. The gasket of claim 46 , wherein the body comprises a gel and the gel includes corrosion inhibitors.

55. The gasket of claim 54 , wherein the corrosion inhibitors are from a group of non-chromated corrosion inhibitors.

56. The gasket of claim 46 , wherein the gasket causes no visible corrosion to the aircraft parts after 500 hours of exposure at 5% salt fog.

57. The gasket of claim 46 , wherein the resistance of the conversion coated skeleton is less than 2.5 milliohms after 500 hours of exposure at 5% salt fog.

58. The gasket of claim 46 , wherein the body contains fillers.

59. The gasket of claim 58 , wherein the body fillers include conductive fibers.

60. A gasket for use between aircraft parts under compression, the gasket comprising:

a moisture proof body comprising an elastomeric polymer with a tacky, outer surface configured to releasably contact at least one of the aircraft parts;

a metal skeleton substantially encapsulated by the moisture proof body of the gasket in an uncompressed state;

wherein the metal skeleton includes an electrically conductive or semi-conductive conversion coating on an outer surface thereof;

wherein, under compression, the moisture proof body deforms sufficiently to allow the aircraft parts to contact the outer surface of the metal skeleton and provide electrical conductivity therethrough;

wherein, under a nominal electrode pressure of about 200 psi, the conversion coated skeleton has less than 200 milliohms of resistance after 500 hours of exposure at 5% salt fog; and

wherein the gasket causes no visible corrosion to the aircraft parts after 500 hours of exposure at 5% salt fog.

61. The gasket of claim 60 , wherein the resistance of the conversion coated skeleton is less than 2.5 milliohms after 500 hours of exposure at 5% salt fog.