HEAT DISSIPATION SYSTEM

• US 20110139430A1
• Filed: 06/10/2009
• Published: 06/16/2011
• Est. Priority Date: 06/10/2008
• Status: Abandoned Application

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: Rebeyrotte, Vincent, Colongo, Emile
• Application Number:
  US12/996,983
• Publication Number:
  US 20110139430A1
• Time in Patent Office: Days
• US Class Current: 165/185
• CPC Class Codes: H01L 23/36 Selection of materials, or shaping, to facilitate cooling or heating, e.g. heatsinks H01L23/28, H01L23/40, H01L23/42, H01L23/44, H01L23/46 take precedence; heating H01L23/345
• CPC Class Codes: H01L 23/3675 characterised by the shape of the housing
• CPC Class Codes: H01L 23/473 by flowing liquids H01L23/4332, H01L23/4338 take precedence
• CPC Class Codes: H01L 2924/00 Indexing scheme for arrangements or methods for connecting or disconnecting semiconductor or solid-state bodies as covered by H01L24/00
• CPC Class Codes: H01L 2924/0002 Not covered by any one of groups H01L24/00, H01L24/00 and H01L2224/00
• CPC Class Codes: H05K 7/20254 Cold plates transferring heat from heat source to coolant

Abstract

A system for dissipating heat generated by an electronic system, for example an electronic device in an aircraft. The system includes a housing including an external lid covering the electronic system and configured to be in contact with a first cold source, and a second cold source located inside the external lid. The housing includes an internal lid located inside the external lid and covering the electronic system, the second cold source being located between the internal and external lids.

Claims

1-6. -6. (canceled)

7. A system for dissipation of heat produced by an electronic system, or by an electronic equipment item in an aircraft, comprising:

a housing that includes an external lid covering the electronic system and configured to be in contact with a first cold source, and a second cold source located inside the external lid,

wherein the housing further includes an internal lid located inside the external lid and covering the electronic system, the second cold source being located between the internal and external lids.

8. A dissipation system according to claim 7, wherein the internal lid and the external lid form a cavity containing the second cold source.

9. A dissipation system according to claim 7, wherein the second cold source has a heat capacity value greater than a heat capacity value of the first cold source.

10. A dissipation system according to claim 7, wherein the housing comprises six faces, a first face being fastened to a support and the other five faces being configured to be in contact with the first cold source.

11. A dissipation system according to claim 7, wherein the second cold source comprises water.

12. An aircraft, comprising:

a dissipation system according to claim 7.