Abstract: The invention relates to storage-stable pigmented formulations containing isocyanate groups, comprising at least one pigment a., at least one component b. containing isocyanate groups, at least one wetting agent and/or dispersant c., at least one isocyanate group-containing grinding resin d. and optionally solvents, wherein the formulation has a viscosity increase of less than 500% after storage at 50° C. over a period of at least 3 days. The invention also relates to the preparation of such formulations and to the use thereof.

Abstract: The present invention is related to agents capable of binding to and inhibiting or antagonizing the action of IL-11 and/or or IL-11RA for the treatment and/or prevention of abnormal uterine bleeding, which comprises heavy menstrual bleeding, prolonged bleeding, altered bleeding pattern, dysmenorrhea, as well as of the underlying diseases leiomyoma and endometriosis and the use of the agent to inhibit menstruation. Furthermore, the invention provides novel IL-11 antibodies.

Abstract: A battery module for a vehicle, in particular for an aircraft, comprises two end plates and a cell stack comprising an arrangement of several interconnected battery cells, in particular pouch cells, that are arranged in a row along a stacking direction, wherein the cell stack is sandwiched between the two end plates in the stacking direction, wherein the battery module further comprises a separate tube-like enclosure comprising a heat insulating material, the tube-like enclosure having a front opening and a back opening that are closed by the end plates, so that the tube-like enclosure and the two end plates form a housing in which the cell stack is accommodated.

Abstract: The present invention relates to an aircraft, comprising a fuselage, at least one pair of wings and a battery system for providing power to electrical systems of the aircraft, wherein the battery system comprises at least one battery pack, each battery pack comprises a number of individual battery modules, which are directly or indirectly coupled to one another, and the at least one battery pack is disposed between an inner structural wall defining an interior space of the fuselage and an outer fairing wall of the fuselage. The fuselage is provided with a rack mounting mechanism comprising a number of mounting brackets, each for exchangeably mounting one of the battery modules to the aircraft, and each of the battery packs is a virtual battery pack, which is obtained by electrically connecting a predetermined number of the battery modules.

Abstract: A battery module for a vehicle, in particular for an aircraft, comprises a housing, a cell stack accommodated in the housing, an internal channel system for heat transfer fluid disposed in the housing, a fluid inlet connector and a fluid outlet connector connected to the internal channel system and adapted to being connected to an external thermal management system, wherein the fluid inlet connector and the fluid outlet connector are self-sealing connectors molded into the housing, preferably self-sealing and dripless connectors.

Abstract: A process is disclosed to recycle and/or formulate expandable plastic materials using a system (1) comprising: an extruder unit (10), a mixer-heat exchanger unit (20), said process comprising the steps of: melting in the extruder unit (10), cooling in the mixer-heat exchanger unit (20), and controlling the melt pressure by means of a melt pump unit (50), followed by granulation, extrusion, or injection molding, wherein a first expansion agent (81) is not degassed during a melt processing in the system (1) such that it is substantially contained in the granulated expandable plastic material (130) or used to form either the extruded, formed and expanded plastic material (140) or the molded expanded plastic article (150). The present invention also relates to a granulated expandable plastic material (130), an extruded, formed and expanded plastic material (140), and a molded expanded plastic article (150) obtainable by said process.

Abstract: A device for separating carbon dioxide from a gas stream, in particular from a flue gas stream, includes an absorber for separating the carbon dioxide from the gas stream by means of a washing medium, a desorber which is fludically connected to the absorber to release the absorbed carbon dioxide from the washing medium, a gas cooler which is fludically connected upstream of the absorber to cool the gas stream, and a processing unit which is connected downstream of the gas cooler and which is equipped and designed to clean water from the gas cooler. A method separates carbon dioxide from a gas stream.

Abstract: A fluid handling device includes a receiving container with a piston arranged therein in a displaceable manner, such that the volume of a fluid receiving reservoir may be changed by a displacement of the piston. In addition, the fluid handling device includes an actuation mechanism configured to displace a carrier bearing upon actuation of the former. Finally, the fluid handling device includes a spring mechanism configured to transfer a force from the carrier bearing to the piston so as to effect, in response to displacement of the carrier bearing in a first direction, a displacement of the piston within the receiving container such that a volume of the fluid reservoir is increased.

Abstract: A device for separating carbon dioxide from a gas stream, in particular from a flue gas stream, includes an absorber for separating the carbon dioxide from the gas stream by means of a washing medium, a desorber which is fludically connected to the absorber to release the absorbed carbon dioxide from the washing medium, a gas cooler which is fludically connected upstream of the absorber to cool the gas stream, and a processing unit which is connected downstream of the gas cooler and which is equipped and designed to clean water from the gas cooler. A method separates carbon dioxide from a gas stream.

Abstract: A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one longitudinal brace or a transverse brace is disposed so as to form at least one of longitudinal seam or a transverse seam between the double shell skin panel and the monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flanges disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the monolithic skin panel to the double shell skin panel.

Abstract: A process is disclosed to recycle and/or formulate expandable plastic materials using a system (1) comprising: an extruder unit (10), a mixer-heat exchanger unit (20), said process comprising the steps of: melting in the extruder unit (10), cooling in the mixer-heat exchanger unit (20), and controlling the melt pressure by means of a melt pump unit (50), followed by granulation, extrusion, or injection molding, wherein a first expansion agent (81) is not degassed during a melt processing in the system (1) such that it is substantially contained in the granulated expandable plastic material (130) or used to form either the extruded, formed and expanded plastic material (140) or the molded expanded plastic article (150). The present invention also relates to a granulated expandable plastic material (130), an extruded, formed and expanded plastic material (140), and a molded expanded plastic article (150) obtainable by said process.

Abstract: The invention concerns a reaction vessel (1) for analyzing a substance, comprising a storage chamber (2) with a circular cross section and at least one measuring chamber (3), wherein the storage chamber (2) and the measuring chamber (3) are interconnected in a transition area (UB) and are intended to receive the substance, wherein the measuring chamber (3) has several pairs of two opposing, plane-parallel measuring windows composed of a transparent material successively configured in the axial direction of the reaction vessel (1) and/or transversely to this axial direction (F1, F2; F3, F4; F5, F6; F7, F8) and wherein a distance (A1, A2, A3) between the measuring windows of a pair (F1, F2; F3, F4; F5, F6) is different from a distance (A2, A3, A1) between the measuring windows of the remaining pairs (F3, F4; F5, F6; F1, F2).

Abstract: A system (10) and method for manufacturing ophthalmic devices, in particular contact lenses or intraocular lenses, the system comprising: at least one injection molding machine for manufacturing a cup bottom part (202) and cup top part (204) to form a cast mold, a cooling station (30), an injection assembly (120) arranged for injecting an amount of monomeric material into the cup bottom part, a curing assembly (130), a first optical inspection assembly (140) for determining at least one first optical cup part parameter, a second optical inspection assembly (150) for determining at least one optical combination parameter of the combination of the cured monomeric material formed into a lens and the cup part that bears the lens, and an electronic control (14) provided with a calculation module for determining at least one optical lens parameter of the lens on the basis of the cup part parameter and the combination parameter.

Abstract: A system (10) and method for manufacturing ophthalmic devices, in particular contact lenses or intraocular lenses, the system comprising: at least one injection molding machine for manufacturing a cup bottom part (202) and cup top part (204) to form a cast mold, a cooling station (30), an injection assembly (120) arranged for injecting an amount of monomeric material into the cup bottom part, a curing assembly (130), a first optical inspection assembly (140) for determining at least one first optical cup part parameter, a second optical inspection assembly (150) for determining at least one optical combination parameter of the combination of the cured monomeric material formed into a lens and the cup part that bears the lens, and an electronic control (14) provided with a calculation module for determining at least one optical lens parameter of the lens on the basis of the cup part parameter and the combination parameter.

Abstract: A laser protection cabin separates a working space for laser processing from a working space environment and includes a first wall area, in particular a ceiling area, and a second wall area, in particular a lateral wall area. The second wall area, on its interior side facing the working area, in particular in a sub-area adjacent to the first wall area, has a laser beam reflector in order to reflect laser radiation, created during laser processing, onto the first wall area. The first wall area has a surface, on its interior side facing the working area, which absorbs and/or diffusely scatters the laser radiation.

Abstract: A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.

Abstract: A fluid handling device includes a receiving container with a piston arranged therein in a displaceable manner, such that the volume of a fluid receiving reservoir may be changed by a displacement of the piston. In addition, the fluid handling device includes an actuation mechanism configured to displace a carrier bearing upon actuation of the former. Finally, the fluid handling device includes a spring mechanism configured to transfer a force from the carrier bearing to the piston so as to effect, in response to displacement of the carrier bearing in a first direction, a displacement of the piston within the receiving container such that a volume of the fluid reservoir is increased.

Abstract: A laser protection cabin separates a working space for laser processing from a working space environment and includes a first wall area, in particular a ceiling area, and a second wall area, in particular a lateral wall area. The second wall area, on its interior side facing the working area, in particular in a sub-area adjacent to the first wall area, has a laser beam reflector in order to reflect laser radiation, created during laser processing, onto the first wall area. The first wall area has a surface, on its interior side facing the working area, which absorbs and/or diffusely scatters the laser radiation.

Abstract: A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one brace which is at least one of a longitudinal and a transverse brace is disposed so as to form at least one of a longitudinal seam and a transverse seam between the at least one double shell skin panel and the at least one monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flange that are disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the at least one monolithic skin panel to the at least one double shell skin panel.

Abstract: A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.