Abstract: A thermal management control valve a housing assembly having a first housing section and a second housing section, a rotary actuator coupled to a drive shaft, and a louver plate assembly. The louver plate assembly includes a louver plate having a louver cutout, a first seal assembly arranged between the louver plate and the first housing section, and a second seal assembly arranged between the louver plate and the second housing section. The first seal assembly includes a plurality of inner walls that define a plurality of first fluid passageways. The second seal assembly defines a second fluid passageway between. Selective rotation of the louver plate rotationally aligns the louver cutout with one or more of the plurality of first fluid passageways and the second fluid passageway to provide fluid communication between the one or more of the plurality of first fluid passageways and the second fluid passageway.

Abstract: A thermal management control valve includes a housing assembly having a first housing section and a second housing section, a rotary actuator coupled to a drive shaft, and a louver plate assembly. The louver plate assembly includes a louver plate, a first seal plate, and a second seal plate. The louver plate is coupled to the drive shaft so that rotation of the drive shaft is configured to selectively move the louver plate along a louver direction between a first position and a second position. The first seal plate includes one or more first seal plate slots that are elongated in a direction that is generally parallel to the louver direction, and the second seal plate includes one or more first seal plate slots that are elongated in a direction that is generally perpendicular to the louver direction.

Abstract: A measuring apparatus for measuring chemical or physical characteristics of a fluid in real time, wherein a measuring window of a fluid channel can be cleaned by an internal cleaning device having an extendable, movable, and rotatable wiper element. Also a sensor carrier for the measuring apparatus and a cleaning method.

Abstract: A thermal management control valve includes a first housing section, a second housing section, and a louver plate assembly defining a flow path. The louver plate assembly includes a louver plate, a first seal plate in engagement with a first louver surface of the louver plate, a first biasing element in engagement with the first seal plate, a second seal plate in engagement with a second louver surface of the louver plate arranged opposite to the first louver surface, and a second biasing element in engagement with the second seal plate. The louver plate is selectively movable relative to the first seal plate and the second seal plate to inhibit or provide fluid flow along the flow path.

Abstract: A method which may serve to producing a fiber preform for a fiber reinforced composite component and/or to manufacturing the fiber reinforced composite component. The method includes pressing an evacuable envelope enclosing a fiber preform material against a forming tool, the pressing being accomplished by evacuating an evacuable bag containing the evacuable envelope with the fiber preform material. The method further includes heating the forming tool and/or the preform, evacuating the envelope, and unsealing the bag while maintaining the envelope evacuated. Due to the maintained evacuated state, a clamping force acts on the fiber preform material which force serves to compensate different shrinkage of the forming tool and the fiber preform material when both cool down. It allows removing the evacuable envelope with the fiber preform material at any temperature after forming. Also, an assembly is disclosed to carry out the method.

Abstract: A thermal management control valve includes a first housing defining a first fluid chamber, a second housing coupled to the first housing and defining a second fluid chamber, a rotary actuator having a drive shaft that defines a drive axis, a cam coupled to the drive shaft and having a cam slot, and a louver plate sealed between the first housing and the second housing and having a plurality of louver slots extending through the louver plate along a louver flow direction. The louver plate is coupled to the cam slot so that rotation of the cam selectively moves the louver plate along a radial direction relative to the drive axis. The radial direction is perpendicular to the louver flow direction.

Abstract: An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough.

Abstract: The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element.

Abstract: An arrangement for monitoring the functionality of a structural adhesive layer to be fabricated between a first surface of a stiffening element and another component. A sensor block is bonded to a second surface of the stiffening component opposite to the first surface. The area of the structural adhesive layer incorporates a plurality of air openings and vacuum openings that vertically extend through the stiffening component and structural adhesive layer and the sensor block. The air openings are interconnected among each other by at least one air channel, and the vacuum openings by at least one vacuum channel. At least one of the channels is connected to an evaluator unit to detect a failure of the structural adhesive layer.

Abstract: An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough.

Abstract: The invention relates to a stiffening component (2) for monitoring the functionality of a structural adhesive layer (6) to be fabricated between the latter and another component (4). According to the invention, the area of the structural adhesive layer (6) incorporates a plurality of air openings and vacuum openings that intersperse the stiffening component (2) and structural adhesive layer (6), as well as a sensor block (28), and the air openings are interconnected by at least one air channel (32), and the vacuum openings by at least one vacuum channel (34), wherein the channels (32, 34) run in the sensor block (28), and at least one of the channels (32, 34) can be connected to an evaluator unit (38) to detect a failure of the structural adhesive layer (6).