Abstract: A connector system for an aircraft, for connecting a hose line, includes a skin panel which has a clearance which extends between an external face and an internal face, a primary part which on the clearance is disposed on an internal side of the skin panel that is defined by the internal face, a cover mounted on the primary part and movable between a closing position in which the cover covers the clearance of the skin panel, and an opening position in which the cover releases the clearance of the skin panel, and a tubular connector port mounted on the primary part and movable between a storage position in which the connector port is disposed on the internal side of the skin panel, and a use position in which the connector port projects beyond the external face of the skin panel.

Abstract: Stirring device for stirring a sample in a container which is closable by a lid, for a flash point determination test and/or combustion point determination test, wherein the stirring device comprises a stirring unit which may extend at least partially through the lid for stirring the sample which is arranged in the container, a drive unit which is to be arranged at least partially outside of the lid, for driving, in particular rotationally driving, the stirring unit, a coupling unit for coupling the stirring unit with the drive unit, and an actuation unit which, in particular for adjusting the coupling unit, is actuatable such that selectively in a first actuation position, when pulling up the drive unit, the lid is detachable from the container commonly with the stirring device, or in a second actuation position, when pulling up the drive unit, the drive unit is detachable from the container, and the stirring unit and the lid remain at the container.

Abstract: A device for tempering a sample located in a container for a flash point determination test and/or fire point determination test is provided, the device comprising: a temperature control block having a, in particular cylindrical, container receptacle for receiving the container; a cooling air guide body for delimiting a cooling air path in which the temperature control block is arranged; wherein the temperature control block has an outer surface with fins.

Abstract: A connector system for an aircraft, for connecting a hose line, includes a skin panel which has a clearance which extends between an external face and an internal face, a primary part which on the clearance is disposed on an internal side of the skin panel that is defined by the internal face, a cover mounted on the primary part and movable between a closing position in which the cover covers the clearance of the skin panel, and an opening position in which the cover releases the clearance of the skin panel, and a tubular connector port mounted on the primary part and movable between a storage position in which the connector port is disposed on the internal side of the skin panel, and a use position in which the connector port projects beyond the external face of the skin panel.

Abstract: The invention relates to a method for controlling a chemical reaction which creates a product, wherein at least one reactant that is present in a liquid phase is subjected to a pressure change.

Abstract: The present invention relates to crystal forms of blood coagulation factor XIIIa, crystal structure information obtained from them, methods of preparing such crystal forms, their use for the identification and/or design of inhibitors of blood coagulation factor XIIIa activity and methods for identifying, optimizing and designing compounds which should have the ability to interact with or inhibit blood coagulation factor XIIIa.

Abstract: An explosive charge is disclosed which has a spatial shape comprising explosive material and, in the course of the explosion, unfolds a spatially anisotropic pressure action in at least one main action direction, in which the pressure action is greater than in the other action directions. The spatial shape comprising the explosive material has a surface area facing toward the at least one main action direction and extends in the at least one main action direction, particles are applied and/or a material layer disintegrating into particles during the explosion is applied to the surface area, the particles comprise a nonexplosive material, and a total mass of the particles is less than a mass of the explosive material.

Abstract: An explosive charge is disclosed which has a spatial shape comprising explosive material and, in the course of the explosion, unfolds a spatially anisotropic pressure action in at least one main action direction, in which the pressure action is greater than in the other action directions. The spatial shape comprising the explosive material has a surface area facing toward the at least one main action direction and extends in the at least one main action direction, particles are applied and/or a material layer disintegrating into particles during the explosion is applied to the surface area, the particles comprise a nonexplosive material, and a total mass of the particles is less than a mass of the explosive material.