Abstract: A probe head with a cylindrical portion and an oblique truncated portion angled downward toward a high-powered electronic device under testing. The probe head has a proximal end comprising an oblique truncated cone portion angled relative to the longitudinal axis at an input angle and has an analog signal input. The probe head has a digital signal output provided on the distal end of the housing.

Abstract: A metrology system may include an optical metrology sub-system to generate optical metrology measurements of optical metrology based on features of the optical metrology targets associated with at least one optical pitch and an additional metrology sub-system to generate additional metrology measurements of the optical metrology targets, where the additional metrology measurements have a higher resolution than the optical metrology measurements, and where the additional metrology sub-system further measures deviations of the optical metrology targets from a reference design. The system may further include a controller to generate accuracy measurements for the optical metrology targets based on the measurements, identify variations of a lithography process based on the deviations, correlate the accuracy measurements to the variations, and adjust at least one of the optical metrology sub-system, a lithography tool, or the reference design based on the correlations.

Abstract: In a method for producing an implant from a biocompatible silicone, a 3D mathematical model of an implant to be produced is used to create a 3D model of a casting mold for the implant as a negative. The casting mold is produced from a polymeric material through an additive manufacturing process and coated through vapor deposition of a coating material from the parylene family at least in a region that comes into contact with the biocompatible silicone to be cast. A platinum-catalyzed 2-component thermosetting silicone as the biocompatible silicone for the implant is introduced into a mold cavity of the coated casting mold, with a residence time of the implant in a patient's body of more than 29 days. The casting mold is heated to vulcanize the biocompatible silicone, and after cooling down the vulcanized implant is demolded from the casting mold.

Abstract: In a method for producing an implant from a biocompatible silicone, a 3D mathematical model of an implant to be produced is used to create a 3D model of a casting mold for the implant as a negative. The casting mold is produced from a polymeric material through an additive manufacturing process and coated through vapor deposition of a coating material from the parylene family at least in a region that comes into contact with the biocompatible silicone to be cast. A platinum-catalyzed 2-component thermosetting silicone as the biocompatible silicone for the implant is introduced into a mold cavity of the coated casting mold, with a residence time of the implant in a patient's body of more than 29 days. The casting mold is heated to vulcanize the biocompatible silicone, and after cooling down the vulcanized implant is demolded from the casting mold.

Abstract: A radiation protection material (10) is arranged between at least two layers (21, 22) of at least one plastic-containing element in order to produce a radiation protection element. At least part of the gas present between the at least two layers (21, 22) is removed. The at least two layers (21, 22) are connected with each other.

Abstract: A multilumen body for a medical device, comprising a first tubular element and a second tubular element, which is arranged in the first tubular element and which is in contact with the first tubular element at least in sections and movable relative to the first tubular element, an inner surface of the first tubular element having a first profile and/or an outer surface of the second tubular element having a second profile so that the contact surface between the first tubular element and the second tubular element is smaller than without the first profile and/or without the second profile. The multilumen body is characterized in that the first profile and/or the second profile include a plurality of alternating elevations and depressions, wherein a maximum distance between two neighboring elevations is 100 ?m.

Abstract: A method for the manufacture of a gear component includes, in a soft machining process, introducing a preliminary toothing 3 with a machining allowance 7 that is fixed relative to a final toothing 4 into a blank such that a semi-finished part 2 is produced. The method also includes, in a fine machining process, removing the machining allowance 7 and producing the final toothing 4 of the toothed component. The machining allowance 7 is removed in a single-stage hobbing method by a grinding tool 1, wherein the grinding tool 1 removes the machining allowance completely in a single stroke movement H.

Abstract: The invention described herein shows a high surface area anode. The high surface area anode contains a flat surface on one side and a ribbed surface on the opposite side. On the ribbed surface there is a first edge-lip on its first-end and a second edge-lip on its second-end. Both the first edge-lip and the second edge-lip run parallel to each other. The high surface area anode further contains a plurality of ribs and groves between the first edge-lip and the second edge-lip also running parallel to each other. The high surface area anode is manufactured using a continuous casting method that includes the following steps; dissolving the anode metal into the holding furnace shaping the anode metal using a high surface area graphite mold; solidifying the anode metal using a liquid while extruding the anode metal through the high surface area mold; solidifying the anode metal by using a secondary cooling source; and extracting the now solidified and shaped high surface anode metal.

Abstract: An aircraft beacon light for being mounted to an aircraft fuselage includes: a support structure, having a carrier, and a stem for supporting the carrier and for spacing the carrier from the aircraft fuselage; and a lighting system, supported by the support structure, the lighting system having a plurality of light sources, light optics for redirecting at least a portion of the light emitted by the plurality of light sources, and a lens cover, with the plurality of light sources and the light optics being arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red-flashing beacon light output in operation.

Abstract: A method for the manufacture of a gear component includes, in a soft machining process, introducing a preliminary toothing 3 with a machining allowance 7 that is fixed relative to a final toothing 4 into a blank such that a semi-finished part 2 is produced. The method also includes, in a fine machining process, removing the machining allowance 7 and producing the final toothing 4 of the toothed component. The machining allowance 7 is removed in a single-stage hobbing method by a grinding tool 1, wherein the grinding tool 1 removes the machining allowance completely in a single stroke movement H.

Abstract: A radiation protection material (10) is arranged between at least two layers (21, 22) of at least one plastic-containing element in order to produce a radiation protection element. At least part of the gas present between the at least two layers (21, 22) is removed. The at least two layers (21, 22) are connected with each other.

Abstract: An aircraft beacon light for being mounted to an aircraft fuselage includes: a support structure, having a carrier, and a stem for supporting the carrier and for spacing the carrier from the aircraft fuselage; and a lighting system, supported by the support structure, the lighting system having a plurality of light sources, light optics for redirecting at least a portion of the light emitted by the plurality of light sources, and a lens cover, with the plurality of light sources and the light optics being arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red-flashing beacon light output in operation.

Abstract: An exterior aircraft light unit includes a power input coupleable to an aircraft on-board power supply; at least one LED coupled to the power input for receiving power from the aircraft on-board power supply and configured to emit a light output; an optical sensor arranged for sensing an intensity detection portion of the light output and configured to output a detection signal indicative of an intensity level of the light output; an end of life detector, coupled to the optical sensor for receiving the detection signal and configured to determine an end of life condition; and a fuse circuit coupled to the end of life detector; wherein the fuse circuit is configured to irreversibly disable an LED circuit board upon the end of life detector communicating the end of life condition to the fuse circuit.

Abstract: An exterior aircraft light unit includes a power input coupleable to an aircraft on-board power supply; at least one LED coupled to the power input for receiving power from the aircraft on-board power supply and configured to emit a light output; an optical sensor arranged for sensing an intensity detection portion of the light output and configured to output a detection signal indicative of an intensity level of the light output; an end of life detector, coupled to the optical sensor for receiving the detection signal and configured to determine an end of life condition; and a fuse circuit coupled to the end of life detector; wherein the fuse circuit is configured to irreversibly disable an LED circuit board upon the end of life detector communicating the end of life condition to the fuse circuit.

Abstract: The present invention relates to a method for testing different selected materials and/or surface structures for the culture of cells and/or microorganisms.

Abstract: An emergency lighting system for an aircraft includes an emergency light control unit, having an external power input and at least one external control input for receiving external control commands from at least one of a cockpit crew, a cabin crew, a board computer and an autopilot, and a plurality of autonomous emergency light units, each of the plurality of autonomous emergency light units comprising at least one LED and a rechargeable capacitor. The emergency light control unit is configured to process the external control commands and to communicate emergency light control commands to the plurality of autonomous emergency light units as a response to the external control commands.

Abstract: A dimmable LED reading light unit includes a dimming module and an LED module, connected in series. The dimming module has an input being connectable to a power supply supplying direct voltage and includes a potentiometer allowing section of a dimming rate and a current controller providing an operating current for the LED module. The LED module includes at least one LED and a current consumer connected in parallel and the current controller is configured to supply direct current to the LED module that substantially corresponds to the sum of the driving current necessary for driving the at least one LED to emit light with an intensity of illumination corresponding to the dimming rate of the potentiometer, and the current consumption of the current consumer.

Abstract: An emergency lighting system for an aircraft includes an emergency light control unit, having an external power input and at least one external control input for receiving external control commands from at least one of a cockpit crew, a cabin crew, a board computer and an autopilot, and a plurality of autonomous emergency light units, each of the plurality of autonomous emergency light units comprising at least one LED and a rechargeable capacitor. The emergency light control unit is configured to process the external control commands and to communicate emergency light control commands to the plurality of autonomous emergency light units as a response to the external control commands.

Abstract: A combined wing scan and winglet illumination light unit is disclosed. The light unit has at least one LED and at least one optical structure for shaping a light emission distribution of the combined wing scan and winglet illumination light unit. The wherein the light emission distribution has a first illumination region for illuminating a wing and a wing engine of an aircraft and a second illumination region for illuminating a wing tip winglet of the aircraft.

Abstract: Floor element for use in the gymnastics and/or fitness sector, wherein, in particular for forming a floor with a large surface area, at least one connecting means is provided on least one outer edge to connect the floor element to a further floor element, in particular of the same kind. The floor element is characterised in that the floor element is formed from an elastic, in particular permanently elastic, polyurethane integral foam. In addition the invention relates to a floor formed from a plurality of floor elements according to the invention.