US2011139430A1PendingUtilityA1

Heat dissipation system

Assignee: AIRBUS OPERATIONS SASPriority: Jun 10, 2008Filed: Jun 10, 2009Published: Jun 16, 2011
Est. expiryJun 10, 2028(~1.9 yrs left)· nominal 20-yr term from priority
H10W 40/47H10W 40/22H10W 40/10H05K 7/20254
43
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Claims

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

exact text as granted — not AI-modified
1 - 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 .

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