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: 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 collapsible partition is provided having a collapsed configuration and an installed configuration in which it is arranged to divide a vehicle compartment into two parts. The partition includes, but is not limited to a ducted portion comprising a duct. The duct extends within the partition from a first opening at a first end of the duct to a second opening at a second end of the duct. The duct is arranged to convey a control fluid for controlling the heat transfer between the partition and at least one of the two parts of the vehicle compartment. There is also disclosed a vehicle compartment control arrangement and a method of partitioning a vehicle compartment.

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 (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: 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 door and its frame especially in an aircraft are constructed for circulating air through the structure for preventing cold air from forming near the door in an aircraft cabin. For this purpose at least one air flow channel is provided in the door construction. The air flow channel communicates with at least one inlet port with at least one outlet port so positioned that air circulation is maintained through the door structure. The outlet port passes preferably through a cabin floor for discharging cold air into a space below the cabin floor.