| 摘要 |
A system for managing the heat fluxes of an aircraft including at least one propulsion system that integrates a turbomachine and a cell including at least one fuel tank to supply the turbomachine via a fuel supply circuit, and at least one source of thermal effluents connected to a cell cooling circuit that integrates first elements for ensuring heat transfer between a coolant circulating in the cell cooling circuit and an air flow channeled into at least one cooling air channel extending from at least one air intake up to at least one air exhaust, whereby the system includes second elements for ensuring heat transfer between a coolant circulating in the cell cooling circuit and the fuel, a fuel circuit connecting the at least one tank to the second heat transfer elements, whereby the air intake includes blocking elements that can occupy a first open state for air to pass inside the channel and a second closed state to block the air intake. The fuel circuit includes at least one control valve that orients the fuel either in the direction of the tank or of the circuit designed for the propulsion system. |
