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.

Abstract: The present invention relates to kits comprising 2,4-dichlorophenoxyacetate derivatives as well as antibodies that bind to these derivatives. Inter alia, the kits can be used to label biomolecules for analytical and diagnostic applications. Some of the compounds described here can be used to label biomolecules under physiological conditions and without having to apply in situ activation. Furthermore, the presence of spacers within the 2,4-dichlorophenoxyacetate derivatives improves their binding to antibodies.

Abstract: The invention relates to a seat securing system for securing air passenger seats to a securing rail (10), whereby the system permits a relative motion between a mounting part (24) and a base body (26) that, in the longitudinal direction of said securing rail (10), can be brought into a fixed position. In this securing position, a locking body (34), which can pivot from a release position and into a locking position and which is subjected to the action of an energy storage device (32), secures the respective detent parts (22, 30) and thus the base body (24) and mounting part (26) on the securing rail (10). Said energy storage device permits a compensation of tolerances so that the inventive fitting always rests securely against the rail(10).

Abstract: The aim of the invention is to investigate the bonding of substances to target molecules. This is achieved by means of a densely packed device wherein various target molecules are bonded in a large number of sample areas. Cross-contamination and evaporation need to be minimized. The active surface of the sample areas have to be maximized. The inventive solution resides in the use of carrier plates, containing densely packed capillary structures and having a very large inner surface despite small outer dimensions. 1000 times more molecules can be bonded than on a flat outer surface of a comparable size. Cross contamination is avoided by the lack of cross links between the capillaries. Evaporation is minimized by a small outer surface. After the inner surface of the capillaries has been silanized, peptides and peptidomimetics are synthesized in a locally targeted manner.

Abstract: The invention relates to a seat fixing device, in particular to an air passenger seat on a floor of an aircraft comprising at least one fastening rail (10) in the form or a hollow profile which is provided with a longitudinal channel (14) delimiting the free flanks (16) of the profile on the top part thereof (12) oriented to the scat, wherein said channel comprises through openings (18) disposed in a predetermined modular dimension which enlarge the free input section and are used for inserting at least one snap-locking part (24) of a locking body (26) which is movable to a clamping position with the profile (16) of the hollow profile (14) by the relative displacement of each snap-locking part (24) in a perpendicular direction with respect to the longitudinal axis (28) of the fastening rail (10).

Abstract: An aircraft air-conditioning system is disclosed, which includes at least one heat exchanger (14) to which coolant circulating in a cooling circuit of a cooling system and air are fed. The coolant cools the fed air in the heat exchanger (14), and the air leaving the heat exchanger (14) enters the aircraft cabin. The coolant of the cooling system is always in the liquid state in the cooling circuit. The liquid coolant can also cool an aircraft seat (2) or a sitting area of the aircraft seat (2).

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 vaporise at least partially while cooling the electronic device.

Abstract: Cooling system and cooling method for cooling components of a power electronics The invention relates to a cooling system for cooling components (10) of power electronics installed on board an aircraft, in particular a passenger aircraft, comprising a cooling device (30) which is to be coupled in a heat-transmitting and planar manner to the components of the power electronics, and which cooling device (30) comprises at least two heat sinks (32, 34, 36, 38, 39, 50) fluidly isolated from one another, the cooling system further comprising at least two cooling circuits each including a cooling fluid source, wherein the at least two heat sinks of the cooling device (30) can be separately supplied with cooling fluids from different cooling fluid sources, and wherein the cooling system is configured such that no phase transition of the cooling fluids within the cooling circuits occurs, during operation of the cooling system. The invention also relates to a method for cooling components of power electronics.