Abstract: A honeycomb structure including a first external side, a second external side, and an anti-friction agent buffer for receiving an anti-friction agent. An opening to an anti-friction agent inlet and an opening to an air outlet are present on the first external side. This honeycomb structure may be useful in an aircraft as part of a belly-landing system for the aircraft.

Abstract: An insulation pack for thermally and acoustically insulating an aircraft has a mat formed from an insulation material, and a casing film which completely encases the mat. The casing film has drying openings, each closable a cover that is connected to the casing film. Each cover has a coating substance, the planar extent of which varying as a function of the relative air humidity of the air in the interior of the insulation pack such that each cover moves relative to the casing film, as a function of air humidity. The associated covers are adapted for assuming an orientation which, below a predetermined relative air humidity, closes the associated drying opening and which, at higher relative air humidity values, at least partially opens the associated drying opening.

Abstract: An insulation pack for thermally and acoustically insulating an aircraft has a mat formed from an insulation material, and a casing film which completely encases the mat. The casing film has drying openings, each closable a cover that is connected to the casing film. Each cover has a coating substance, the planar extent of which varying as a function of the relative air humidity of the air in the interior of the insulation pack such that each cover moves relative to the casing film, as a function of air humidity. The associated covers are adapted for assuming an orientation which, below a predetermined relative air humidity, closes the associated drying opening and which, at higher relative air humidity values, at least partially opens the associated drying opening.

Abstract: An air conduction part for conducting a compressible medium, which part has a cross section through which the medium passes in a flow direction of the medium when the air conduction part is used, which flow direction approximately corresponds to a longitudinal axis of the air conduction part, the air conduction part including at least one wall arrangement that laterally defines the cross section of the air conduction part and conducts the medium. The wall arrangement are provided with at least one shell and with at least one damping device that removes sound energy from the medium, and the shell and the damping device are integrally interconnected so that, with a justifiable amount of outlay, the resulting air conduction parts effectively damp sound and the transport direction of the medium and/or the cross section of the air conduction part may change.

Abstract: An air-distribution system has a first hollow body and a membrane. The first hollow body has a first air-conducting space. The membrane is fitted on the first hollow body in such a way that a second air-conducting space is formed. The second air-conducting space is enclosed by the membrane and an outer surface of the first hollow body. The method comprises the following steps: providing a membrane; fastening the membrane to a hollow body, with the result that there is obtained a second air-conducting space which is enclosed by the membrane and an outer surface of the hollow body.

Abstract: An aircraft passenger service device for receiving goods for cold storage to be supplied to aircraft passengers includes a receiving device having a viewing apparatus, a coolant inlet for feeding a coolant into the receiving device, and a coolant outlet for discharging the coolant from the receiving device. The viewing apparatus is designed to enable a user to inspect goods stored in the receiving device before removal. The aircraft passenger service device further includes a cooling arrangement having a coolant circuit line connected to the coolant inlet and the coolant outlet of the receiving device, and a device that directs into the coolant circuit line a refrigerant fluid flowing through a refrigerant fluid circuit line of a central cooling system of the aircraft.

Abstract: An air conduction part for conducting a compressible medium, which part has a cross section through which the medium passes in a flow direction of the medium when the air conduction part is used, which flow direction approximately corresponds to a longitudinal axis of the air conduction part, the air conduction part including at least one wall arrangement that laterally defines the cross section of the air conduction part and conducts the medium. The wall arrangement are provided with at least one shell and with at least one damping device that removes sound energy from the medium, and the shell and the damping device are integrally interconnected so that, with a justifiable amount of outlay, the resulting air conduction parts effectively damp sound and the transport direction of the medium and/or the cross section of the air conduction part may change.

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 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: An aircraft passenger service device (10) for receiving goods for cold storage to be supplied to aircraft passengers comprises a receiving device (12) which comprises a viewing apparatus, a coolant inlet (14) for feeding a coolant into the receiving device (12) and a coolant outlet (18) for discharging the coolant from said receiving device (12), wherein the viewing apparatus is designed to enable a user to inspect goods stored in the receiving device (12) before they are removed from the receiving device (12). The aircraft passenger service device (10) further comprises a cooling arrangement (20) which comprises a coolant circuit line (22) connected to the coolant inlet (14) and the coolant outlet (18) of the receiving device (12), and a device (27) for thermally coupling a coolant flowing through the coolant circuit line (22) to a refrigerant fluid flowing through a refrigerant fluid circuit line (28) of a central cooling system (30) of the aircraft.

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.