Abstract: In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station.

Abstract: A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser.

Abstract: An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator.

Abstract: The invention discloses the multistage cooling of an aircraft electronic system (2) with at least one electronic component which delivers heat. The multistage feature results from the use of a plurality of circuits for transferring the waste heat. An internal coolant (14) circulating in a closed circuit which is thermally coupled to the electronic component carries heat from the at least one electronic component to a heat exchanger (6) which delivers the heat to an external coolant which flows and/or circulates from a source outside of the aircraft electronic system (2) through the heat exchanger (6) to a sink outside of the aircraft electronic system (2). The internal coolant flows from the heat exchanger (6) in the direction of the at least one electronic component and/or circulates in a closed circuit.

Abstract: A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system, the aircraft electronics cooling system providing a thermal coupling between an electronic device to be cooled and the liquid cooling system of the aircraft. A coolant delivered by the liquid cooling system may flow through a board of the electronic device, through a heat sink on which the electronic device is arranged and/or through a housing in which the electronic device is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: A system for air conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer in order to supply the central mixer with air at a desired low temperature. A first recirculation system is designed to remove exhaust air from a first aircraft cabin region and is connected to the central mixer in order to lead the exhaust air into the central mixer. A second recirculation system is designed to remove exhaust air from a second aircraft cabin region and is connected to first and second local mixers in order to lead the exhaust air into the local mixers, the local mixers also receiving mixed air flow from the central mixer. The second recirculation system includes a cooling unit which is designed to cool the recirculation air removed from the second aircraft cabin region before delivery to the first and second local mixers.

Abstract: The invention discloses the multistage cooling of an aircraft electronic system (2) with at least one electronic component which delivers heat. The multistage feature results from the use of a plurality of circuits for transferring the waste heat. An internal coolant (14) circulating in a closed circuit which is thermally coupled to the electronic component carries heat from the at least one electronic component to a heat exchanger (6) which delivers the heat to an external coolant which flows and/or circulates from a source outside of the aircraft electronic system (2) through the heat exchanger (6) to a sink outside of the aircraft electronic system (2). The internal coolant flows from the heat exchanger (6) in the direction of the at least one electronic component and/or circulates in a closed circuit.

Abstract: An aircraft includes a cooling system having a cooling circuit to circulate a two-phase refrigerant therethrough, an evaporator disposed in a first section of the cooling circuit and having a refrigerant inlet and outlet, a condenser disposed in a second section of the cooling circuit and having a refrigerant inlet and outlet, a first cooling circuit control valve disposed in the cooling circuit between the refrigerant outlet of the evaporator and the refrigerant inlet of the condenser, and a second cooling circuit control valve disposed in the cooling circuit between the refrigerant outlet of the condenser and the refrigerant inlet of the evaporator. The first and the second cooling circuit control valves in their closed state seal the first section of the cooling circuit from the second section of the cooling circuit. The second section of the cooling circuit is installed in an unpressurized region of the aircraft.

Abstract: In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station.

Abstract: A cooling system, in particular for use on board an aircraft, includes a first cooling circuit allowing circulation of a two-phase refrigerant therethrough, a first evaporator disposed in the first cooling circuit, a first condenser disposed in the first cooling circuit, and a first heat sink adapted to provide cooling energy to the first condenser. The cooling system further includes a second cooling circuit allowing circulation of a two-phase refrigerant therethrough, a second evaporator disposed in the second cooling circuit, a second condenser disposed in the second cooling circuit, a second heat sink adapted to provide cooling energy to the second condenser, and a cooling energy transfer arrangement which is adapted to transfer cooling energy provided by the first heat sink and/or the first condenser to the second cooling circuit or to transfer cooling energy provided by the second heat sink and/or the second condenser to the first cooling circuit.

Abstract: A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser.

Abstract: An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator.

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system, the aircraft electronics cooling system providing a thermal coupling between an electronic device to be cooled and the liquid cooling system of the aircraft. A coolant delivered by the liquid cooling system may flow through a board of the electronic device, through a heat sink on which the electronic device is arranged and/or through a housing in which the electronic device is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: A cooling system (10) for cooling an aircraft device (12) comprises an evaporator (14, 16, 18) for receiving a fluid (F) which is to be evaporated, a first adsorber (24) which contains a medium (28) for the adsorption of the fluid (F) which is evaporated in the evaporator (14, 16, 18), as well as a second adsorber (26) which contains a medium for the adsorption of the fluid (F) which is evaporated in the evaporator (14, 16, 18). A control system (22) is adapted to establish or to interrupt a fluid connection between the evaporator (14, 16, 18) and the first and/or the second adsorber(s) (24, 26).

Abstract: A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (2), the aircraft electronics cooling system providing a thermal coupling between an electronic device (40a, 40b, 40c, 40d, 42, 44) to be cooled and the liquid cooling system (2) of the aircraft. A coolant delivered by the liquid cooling system (2) may flow through a board of the electronic device (40a, 40b, 40c, 40d), through a heat sink on which the electronic device (42) is arranged and/or through a housing in which the electronic device (44) is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (2), the aircraft electronics cooling system providing a thermal coupling between an electronic device (40a, 40b, 40c, 40d, 42, 44) to be cooled and the liquid cooling system (2) of the aircraft. A coolant delivered by the liquid cooling system (2) may flow through a board of the electronic device (40a, 40b, 40c, 40d), through a heat sink on which the electronic device (42) is arranged and/or through a housing in which the electronic device (44) is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: A system (10) for air conditioning an aircraft cabin (12) comprises an air conditioning unit (14) connected to a central mixer (16) in order to supply the central mixer (16) with air at a desired low temperature. A first recirculation system (18) is designed to remove exhaust air from a first aircraft cabin region (12a) and is connected to the central mixer (16) in order to lead the exhaust air from the first aircraft cabin region (12a) into the central mixer (16). A second recirculation system (24) is designed to remove exhaust air from a second aircraft cabin region (12b) and is connected to a local mixer (20, 22) in order to lead the exhaust air from the second aircraft cabin (12b) into the local mixer (20, 22). The local mixer (20, 22) is connected to the central mixer (16) in order to supply mixed air from the central mixer (16) into the local mixer (20, 22).

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (2), the aircraft electronics cooling system providing a thermal coupling between an electronic device (40a, 40b, 40c, 40d, 42, 44) to be cooled and the liquid cooling system (2) of the aircraft. A coolant delivered by the liquid cooling system (2) may flow through a board of the electronic device (40a, 40b, 40c, 40d), through a heat sink on which the electronic device (42) is arranged and/or through a housing in which the electronic device (44) is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.