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: In a radio communication system, a common channel is provided which is allocated to a plurality of subscribers at the same time for data transmission between a base station and a subscriber station. Measurements regarding the transmission quality are carried out on the common channel and their results are available in the base station. If the transmission quality does not meet a defined criterion, the base station transmits a first message to a controlling radio network controller associated therewith, the first message containing information about the transmission quality and about subscriber stations for which a bad transmission quality was measured. The controlling radio network controller sends a second message which informs serving radio network controllers, associated with the subscriber stations having bad transmission quality and responsible for the configuration of the subscriber stations, about the bad transmission quality.

Abstract: A composition is disclosed comprising virus in a formulation comprising a polyhydroxy hydrocarbon buffered to maintain a pH in a range from about 7 to about 8.5 at a temperature in the range from about 2° C. to 27° C. Methods for concentrating and purifying virus preparations are also disclosed.

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: 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: The present invention concerns novel synthetic blocking reagents for the reduction of non-specific bindings in solid phase assays that rely on biological and specific recognition, e.g., in enzyme-linked immunosorbent assays (ELISAs). The invention provides the use of compounds as blocking reagents as well as kits comprising these compounds. The compounds comprise one or more poly(ethylene glycol) moieties, one or more alkyl- or aminoalkyl groups and another unit bridging the aforementioned groups, wherein the compound comprises at least one amino group.

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 passenger seat, an aircraft passenger seat in particular, has seat components such as a seat frame (20), a backrest (12), and a seat cushion carrier (30) with seat cushion (16). The seat depth between backrest (12) and a seat front edge (26) can be varied by an adjustment mechanism (32) with an energy accumulator, such that the seat depth is adjustable and fastenable in desired adjustment positions. The adjustment mechanism has at least one variable-volume energy accumulator. An adjustment position of the seat depth may be associated with each volume level. The seat depth adjustment may be effected essentially free of mechanical components such as sets of levers.

Abstract: An aircraft cooling system (1) according to the invention comprises a first coolant stream (4a) which cools at least one first heat load (2a), and a second coolant stream (4b) which cools at least one second heat load (2b), wherein the aircraft cooling system (1) is formed such that the first heat load (2a) and the second heat load (2b) are thermally coupled together. The first heat load (2a) and the second heat load (2b) can be formed by two mutually redundant aircraft components. A third coolant stream (12) can thermally couple the first heat load (2a) and the second heat load (2b) together. The third coolant stream (12) can be cooled by a heat sink (16).

Abstract: A system (10) for cooling freight goods on board an aircraft comprises a refrigerating apparatus and a cooling station (14) to which cooling energy generated by said refrigerating apparatus is fed by means of a refrigerating medium and which is connected to an air infeed line (29) of an air-conditioning installation of the aircraft, wherein an air outlet aperture (16) of the cooling station (14) is connectable to a freight compartment (24) of the aircraft in order to discharge into said freight compartment (24) air which has been cooled down to a desired temperature.

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 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 circuit arrangement, having a circuit and a computer unit is provided, in which the circuit and the computer unit are connected to one another via multiple lines for transmitting a number of signals which are embodied as information signals. The circuit has a multiplexer for combining signals, the multiplexer being connected to the computer unit via an additional line.

Abstract: A cooling system for cooling heat loads on board an aircraft comprises a cold producing device, a first cold carrier fluid circuit, which is thermally coupled to the cold producing device and is connected to a first heat load in order to carry off heat from the first heat load, and a second cold carrier fluid circuit, which is connected to a second heat load in order to carry off heat from the second heat load. A coupling system of the cooling system is adapted to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit. In a method for operating such a cooling system for cooling heat loads on board an aircraft, the first cold carrier fluid circuit is selectively thermally coupled to the second cold carrier fluid circuit or thermally uncoupled from the second cold carrier fluid circuit by means of the coupling system.

Abstract: The reception of a first base station of a first mobile radio system in a first frequency range can be influenced by transmissions, associated with a connection, of at least one subscriber station of a second mobile radio system in a second frequency range adjacent to the first frequency range. A signaling unit of the first mobile radio station transmits a signal which is used to reduce the influence of the transmissions of the subscriber station of the second radio mobile system on the reception of the first base station in the first frequency range.

Abstract: The invention relates to methods for examining the enzymatic cleavability of substrates. In the methods, compounds, which have a cleavability of the section to be examined, are firstly synthesized on a first solid phase, separated therefrom, the cleavage reaction is carried out in solution and the cleaved and uncleaved compounds are immobilized on a second solid phase and the cleavability is determined.