Abstract: A multi-line camera such as a two-line camera acquires image data of an object moving relative to the camera. An output of a first sensor line is connected through a first time-delay memory to a first comparator, and is connected directly to a second comparator. An output of a second sensor line is connected directly to the first comparator, and is connected through a second time-delay memory to the second comparator. Thus, the current image data of each sensor line is respectively compared crosswise to the time-delayed previous image data of the respective other sensor line. An evaluation unit compares the outputs of the two comparators, to determine which comparison had a better degree of correspondence, and dependent thereon determines the direction of relative motion of the object relative to the camera.

Abstract: A fiber reinforced strip is adhesively bonded to an outwardly facing surface of a reinforcing frame and to an inwardly facing outer skin surface. Such a strip position reduces crack propagation in a lightweight structure particularly in the outer skin adhesively bonded to the reinforcing frame through the strip. For this purpose the fiber reinforced strip is interposed between the outer skin and the frame and adhesively bonded to the outer skin and to the frame. The strip has reinforcing fibers extending in parallel to each other or the reinforcing fibers are woven into a fabric embedded in a synthetic adhesive bonding material. The embedding of the parallel fibers or of the fiber fabric in the bonding material is performed either prior to the bonding or during the bonding of the strip to the outer skin and to the reinforcing frame.

Abstract: A method and an apparatus facilitate the processing of a core structure for a composite sandwich structure. The core has an open three-dimensional structure and is not self-supporting due to an insufficient strength or stiffness. The method involves temporarily providing a support arrangement on the core structure to mechanically support and stabilize it, then subjecting the supported core structure to the desired processing, and then separating and removing the core structure and the support arrangement from one another. The processing can involve immersion into a processing liquid such as a curable resin, or mechanical machining operations. The support arrangement preferably includes a core impression that is surfacially form-fitting on a structured surface of the core structure. The apparatus includes a support arrangement including a core impression to be disposed on a surface of the core structure. The core impression may be formed of a polymer, a metal, or a casting material.

Abstract: The invention relates to a method for the digital transmission of an analogue measuring signal (M), comprising the following steps: comparing momentary values of a triangular signal (D) with a value of the measuring signal (M) for generating a binary measurement pulse (PM); comparing momentary values of the triangular signal (D) with a predeterminable first reference variable (R1) for generating a binary reference pulse (PR) that corresponds to the measurement pulse (PM) and transmitting the measurement pulse (PM) and reference pulse (PR) at a constant phase.

Abstract: A holding device produces a retaining pressure on a contoured airplane component (40) for holding the component in place when work is performed on the component. For this purpose the holding device (10) comprises a support (11) and at least one holding element (16) connected to the support (11) and projecting from the support (11) for contacting the contoured airplane component (40) in a holding zone. A spacing between a contact area of the holding element (16) and the support (11) is adjustable in accordance with the contour of the airplane component (40) in the holding zone. The adjustment of the position of the holding element relative to the support (11) moves the holding element (16) more or less against the surface contour so that the holding force is applied exactly where needed on the holding zone. A plurality of holding elements can be advanced toward the surface contour to variable extents so that all contact areas together conform to the surface contour.

Abstract: A gas turbine, such as an aircraft engine, has at least one compressor, at least one turbine, a combustion chamber, and a fuel pump to supply fuel to the combustion chamber. Upon identification of a break of a shaft that couples a compressor with a turbine, the gas turbine is shut off. For this purpose, at least one electrical current conductor is arranged on the shaft, whereby this current conductor is a component of a current supply for the fuel pump or for a fuel pump regulation. When the integrity of the current conductor is disrupted, thereby the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.

Abstract: A method and an apparatus are for applying a rotationally driven pressure roller (4) onto a rotationally driven goods guiding roller (3) in stretching equipment for thermoplastic films. The pressure roller (4) is advanced in the direction of the goods guiding roller (3) by at least one first pressurizable piston-cylinder unit (7) in such a manner so that after the advancement an axis-parallel remaining stroke exists between the pressure roller (4) and the goods guiding roller (3). Then at least one second pressurizable piston-cylinder unit (8) operatively connected with the first piston-cylinder unit (7) carries out the remaining stroke, while maintaining the axis-parallelism, until a touching contact exists between the pressure roller (4) and the goods guiding roller (3). Then the pressure roller (4) becomes effective with a nominal pressing force onto the goods guiding roller (3).

Abstract: The procedure is used for the operation of an internal combustion engine (1) with several cylinders (2, 3, 4, 5) into each of which fuel is injected. For a current operating point (15), the current correction factor (KM) for the injection into one of the cylinders (2, 3, 4, 5) is determined. Using the current correction factor (KM) at least some of the grid correction factors (KGA) which are stored in a correction factor characteristic map (13) for discrete operating points (16) of the internal combustion engine (1) are adapted. Here, a distance between the current operating point (15) and the discrete operating point of the grid correction factor (KGA) currently to be adapted is taken into account during the adaptation of the grid correction factors (KGA). Using updated grid correction factors (KGN) which are stored following adaptation in the correction factor characteristic map (13), an updated correction factor (KMN) is determined for the current operating point (15) and used for the injection.

Abstract: An optical strain gage (1) for multi-axis strain measurement includes at least two linear light waveguide sections (2, 3, 4) with Bragg gratings (5). These are arranged next to one another in a prescribed angle (19) of 90° or 45° on a support layer (6) and are supplied with lightwaves by a common infeeding waveguide section (7). All of the light waveguide sections(2, 3, 4, 7) are provided preferably linearly on the support layer (6), and a beam dispersion element (8) is arranged between the infeeding waveguide section (7) and the measuring waveguide sections (2, 3, 4) containing the Bragg grating (5).

Abstract: An antenna arrangement for coupling high frequency electromagnetic waves into or out of a pipe-shaped hollow body includes two patch antenna elements that are located opposite one another and integrated in the pipe inner wall (5) of the hollow body (1), and have curved surfaces fitted to the curved longitudinal pipe inner wall of the hollow body (1). An apparatus for mass flow measurement includes at least two of such antenna arrangements axially spaced apart from one another in a conveyor pipe section.

Abstract: A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: An apparatus for producing a molded product from a sheet-form raw material blank has first and second mold tools that each respectively include a respective inner core mold and a respective outer edge mold laterally adjacent thereto. Drive elements drive the outer edge molds relative to a machine frame, and drive the inner core molds relative to the outer edge molds. A molding process involves closing the outer edge molds to hold an edge rim of the material blank while allowing slippage thereof, and then closing the inner core molds to three-dimensionally deform and mold a central portion of the material blank while pulling required additional material by slippage through the outer edge molds. A separate slip frame is not used. The edge rim held by the outer edge molds remains as a permanent mounting rim or flange of the finished molded product. Edge waste is minimized.

Abstract: A wing has a changeable profile, and extends in a wing chord direction and perpendicularly thereto in a wingspan direction. The wing has a first cover skin and a second cover skin spaced apart from one another with spars therebetween. The wing includes a leading edge region and a trailing edge region opposite one another in the wing chord direction, and a wing tip region at the end of the wing in the wingspan direction. The wing further includes a flexible region that connects the wing tip region to the rest of the wing, and that is adapted to vary the profile of the wing in a direction that includes a component in the wing chord direction and a component in the wingspan direction.

Abstract: The invention relates to a method and an apparatus for forming an insertion-side fabric selvedge (35) on a gripper weaving machine, whereby: a) selectively one of several weft threads (3, 4, 43, 44) that are provided on bobbins (1, 2, 41, 42) is positioned in the running path (5) of a gripper (6), while the other weft threads (3, 4, 43, 44) are held outside of the running path, whereby: b) the weft thread positioned in the running path is grasped and inserted into a loom shed by the gripper (6), whereby: c) thereafter the inserted weft thread (3) is beat-up against a binding line (33) by means of a weaving reed (31), whereby: d) the inserted weft thread (3) is cut-off on the insertion side directly after the beat-up, and e) the bobbin-side weft thread end of a respective cut-off weft thread (3) is respectively grasped and held by a different suction chamber of a suction chamber block (10, 20).

Abstract: At least one liquid tank has an outlet opening and a drain stub extending therefrom. A circular flange has plural connection openings with connection stubs respectively extending therefrom. A drain line is connected to the circular flange and communicates with all of the connection stubs. The drain stub of each tank is flange-connected to a respective connection stub extending from the circular flange. Unneeded connection stubs can be closed with blind flanges. This provides a modular reconfigurable system allowing a selected plurality of liquid tanks to be connected to a single drain line through the flange arrangement.

Abstract: In a method for the calibration of a yaw rate measurement in a motor vehicle, the motor vehicle features at least one device for determining the yaw rate, a camera system which is oriented in the forward direction, and, if applicable, a steering angle sensor or a lateral acceleration sensor. At least one initial calibration is carried out at a standstill and at least one second calibration is carried out when the motor vehicle is moving. The second calibration uses image data of the camera system, which detects the environment in front of the motor vehicle, to predict the course of the roadway lane on which the vehicle is driving, from which the yaw rate is estimated.

Abstract: Producing a composite structure involves providing a core structure having a folded configuration with fold valleys forming open channels extending along the valleys, and then forming a local reinforcement zone in the core structure itself, before applying any cover layer onto the core structure. The method may further involve applying two cover layers on two opposite sides of the core structure to form a composite sandwich structure, after the local reinforcement zone has been formed in the core structure. A core structure preferably has a local reinforcement zone formed by two molded bodies, e.g. of cured synthetic resin or foam, arranged form-fittingly on the opposite sides of the core.

Abstract: A hollow structural component suitable for an aircraft structure includes an inner framework of intersecting longitudinal and transverse ribs, cover sheets covering the top and bottom of the framework, and end closure sheets covering ends of the framework. The transverse ribs have slots to receive the intersecting longitudinal ribs and vice versa, so the ribs intermesh in a grid pattern. Top and bottom edges of the ribs have protruding connector tabs that are fitted into slots provided in the cover sheets. Additional connector tabs at the ends of the transverse ribs are fitted into slots in the end closure sheets. After the parts are assembled by intermeshing the longitudinal and transverse ribs and fitting the connector tabs of the ribs into the slots of the cover sheets and end closure sheets, the resulting plugged-in joints are permanently mechanically secured, e.g. by welding, brazing, soldering or adhesive bonding.

Abstract: A component such as a gas turbine engine component has an oxidation protective layer formed as a substrate surface region in a substrate of the component. The substrate has a nickel-based composition including nickel and an aluminum proportion of greater than 4.5 weight %. The surface region is formed by diffusion of at least platinum into the substrate surface region to provide an integrated platinum proportion of 5 to 40 weight percent over the integration depth range in the surface region.