Patent ID: 8794571
Filing Date: 2014-08-05
Classification: B64C,B64D,Y02T

Abstract:
1. An aircraft cooling system comprising: a cooler having a matrix body in which a plurality of coolant channels are formed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body, the matrix body of the cooler forming a section of an aircraft outer skin with the first and second surfaces of the matrix body, in the state of the cooler mounted to an aircraft, forming outer and inner surfaces respectively of the aircraft outer skin, and a control unit to control the coolant flow through the coolant channels, at least in some operating phases of the aircraft cooling system, such that the coolant in the region of the first surface of the matrix body passes into the coolant channels, and in the region of the second surface of the matrix body passes out of the coolant channels, and to control the coolant flow through the coolant channels, at least in other operating phases of the aircraft cooling system, such that the coolant in the region of the second surface of the matrix body passes into the coolant channels, and in the region of the first surface of the matrix body passes out of the coolant channels.