Avionics chassis

• US 8,222,541 B2
• Filed: 06/19/2009
• Issued: 07/17/2012
• Est. Priority Date: 06/19/2009
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Vander Ploeg, Benjamin Jon, Steenwyk, Meredith Marie, Coxon, Danny Weldon, Horton, Paul James, Streyle, John Jay
• Primary Examiner(s): NGO, HUNG V
• Application Number:
  US12/487,784
• Publication Number:
  US 20100319948A1
• Time in Patent Office: 1,124 Days
• Field of Search: 174/382, 174/384, 174/386, 361/218, 361/816
• US Class Current: 174/382
• CPC Class Codes: H02G 13/00 Installations of lightning conductors; Fastening thereof to supporting structure
• CPC Class Codes: H05K 2201/10371 Shields or metal cases
• CPC Class Codes: H05K 7/20545 Natural convection of gaseous coolant; Heat transfer by conduction from electronic boards
• CPC Class Codes: H05K 9/0045 being rigid plastic containers having a coating of shielding material
• CPC Class Codes: H05K 9/0062 Structures of standardised dimensions, e.g. 19" rack, chassis for servers or telecommunications
• CPC Class Codes: H05K 9/0084 comprising a single continuous metallic layer on an electrically insulating supporting structure, e.g. metal foil, film, plating coating, electro-deposition, vapour-deposition

Abstract

An avionics chassis comprises a composite housing, a radio wave shield, and a lightning strike conductive path, wherein the radio wave shield attenuates electromagnetic interference entering and leaving the housing, and the lightning strike conductive path directs the current from a lightning strike away from an interior of the housing.

Claims

1. An avionics chassis comprising:

a housing made from a carbon composite material and having an outer surface, defining an exterior of the housing, an inner surface, defining an interior of the housing, and having a plurality of heat-dissipating fins projecting from at least a portion of the outer surface;

a metallic layer provided on the housing and having a thickness sufficient to attenuate radio wave energy by at least 60 dB; and

a metallic strip provided on at least a portion of the heat-dissipating fins and having a thickness and density sufficient to carry a lightning-induced current without damage.

2. The avionics chassis according to claim 1, wherein the metallic layer overlies the housing exterior.

3. The avionics chassis according to claim 2, wherein the metallic strip overlies a portion of the metallic layer.

4. The avionics chassis according to claim 2, wherein the metallic layer further overlies the housing interior.

5. The avionics chassis according to claim 1, wherein the metallic layer comprises a metal deposition layer.

6. The avionics chassis according to claim 5, wherein the metallic strip comprises a layer of thermal sprayed aluminum applied to the metal deposition layer.

7. The avionics chassis according to claim 1, further comprising at least one site forming an electrical ground that may be operably coupled to an aircraft such that electricity may be conducted from the chassis to the aircraft through the electrical ground, and the metallic strip is electrically coupled to the site.

8. The avionics chassis according to claim 1, wherein the avionics chassis further comprises bonded joints and the metallic strip creates electrical paths across bonded joints.

9. An avionics chassis comprising:

a housing made from a carbon composite material and having an outer surface, defining an exterior of the housing, an inner surface, defining an interior of the housing, and having a plurality of heat-dissipating fins projecting from at least a portion of the outer surface;

a radio wave shield comprising a metallic layer provided on the housing; and

a lightning strike conductive path comprising a metallic strip provided on at least a portion of the heat-dissipating fins;

wherein the radio wave shield attenuates electromagnetic interference entering and leaving the interior, and the lightning strike conductive path directs current from a lightning strike away from the interior of the housing.

10. The avionics chassis according to claim 9, wherein the lightning strike conductive path comprises thermal sprayed aluminum.

11. The avionics chassis according to claim 10, wherein the radio wave shield comprises a metal deposition layer on the housing.

12. The avionics chassis according to claim 9 wherein the metallic layer overlies the housing exterior.

13. The avionics chassis according to claim 12 wherein the metallic layer further overlies the housing interior.

14. The avionics chassis according to claim 12, wherein the metallic strip overlies a portion of the metallic layer.

15. The avionics chassis according to claim 9, further comprising at least one avionics element mounted within the housing wherein the avionics element is heat producing and radio wave sensitive.

16. The avionics chassis according to claim 9 wherein the radio wave shield has a thickness sufficient to attenuate radio wave energy by at least 60 dB.

17. The avionics chassis according to claim 9 wherein the lightning strike conductive path has a thickness and density sufficient to carry a lightning-induced current without damage.

18. The avionics chassis according to claim 9, further comprising at least one electrical ground that may be operably coupled to an aircraft such that electricity may be conducted from the chassis to the aircraft through the at least one electrical ground.

19. The avionics chassis according to claim 18, wherein the lightning strike conductive path is electrically coupled to the at least one electrical ground.

20. The avionics chassis according to claim 19, wherein the at least one electrical ground comprises a mounting foot.

21. The avionics chassis according to claim 19, wherein the metallic layer overlies the housing exterior and the lightning strike conductive path overlies a portion of the metallic layer.