Patent ID: 8516792

Claim:
A system for managing the heat fluxes of an aircraft that includes at least one propulsion system that integrates a turbomachine, and a cell, the system comprising: at least one fuel tank configured to supply the turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to at least one source of thermal effluents, the cell cooling circuit integrating first means for ensuring a heat transfer between a coolant that circulates in the cell cooling circuit and an air flow that is channeled into at least one cooling air channel that extends from at least one air intake up to at least one air exhaust; second means for ensuring a heat transfer between the coolant that circulates in the cell cooling circuit and the fuel; and a fuel transfer circuit that connects the at least one fuel tank to the second heat transfer means and that is configured to provide the fuel from the at least one fuel tank to the second heat transfer means, the fuel transfer circuit including at least one control valve configured in the fuel transfer circuit to selectively change a supply direction of the fuel from the second heat transfer means between the direction toward the tank and the direction toward the fuel supply circuit that is designed for the propulsion system, wherein the air intake includes means for blocking air configured to occupy a first open state in which the blocking means allows the air flow to pass inside the cooling air channel and a second closed state in which the blocking means blocks the air intake to prohibit the air flow to pass inside the cooling air channel.