Abstract: A safety valve arrangement and method, having an upstream block valve, a downstream block valve, and a pressure monitored galley between the upstream valve and the downstream valve.

Abstract: A method of manufacturing a shell component for an aircraft or spacecraft includes positioning a skin panel, which includes a skin of the aircraft or spacecraft and first and second stringers stiffening the skin, opposite a frame having first and second mouseholes for receiving the first and second stringers, elastically bending the skin panel, inserting the first stringer into the first mousehole, and releasing the elastic bend to insert the second stringer into the second mousehole.

Abstract: An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.

Abstract: An aircraft frame includes a first partial aircraft frame configured to be attached to a first aircraft fuselage segment, and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment. The first and second partial aircraft frames include corresponding first and second stringer coupling sections. The first partial aircraft frame and the second partial aircraft frame are configured to be attached to each other via a first web and a second web. The first stringer coupling section is located between the first inner flange and the first outer flange and the second stringer coupling section is located between the second inner flange and the second outer flange. The first stringer coupling section includes a first wall which extends from the first web into the first section of the first partial aircraft frame, and the second stringer coupling section comprises a second wall, which extends from the second web into the second section of the second partial aircraft frame.

Abstract: Techniques for selecting a boot display device in the multi-GPU configured computing device include a graphic initialization routine for determining a topology of a plurality of GPUs. It is then determined if a display is coupled to any of the plurality of GPUs. The determination of whether the display is coupled to a GPU is communicated to the other of the plurality of GPUs based upon the determined topology. Thereafter, selection of a given GPU as a primary boot device, by a system initialization routine, is influenced by representing each GPU not coupled to the display as a graphics device and the GPUs coupled to a given display as the primary boot device if one or more displays are coupled to GPUs, and by representing the given GPU as the primary boot device and all other GPUs as graphics devices when the display is not coupled to any of the GPUs.

Abstract: A method for the manufacture of a fiber composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mold core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fiber composite component with a multiplicity of openings, each of which is edged by an integral collar.

Abstract: Method for connecting two intermediate products for forming a fiber composite product, wherein the two intermediate products respectively are composite fiber material with a layer of matrix material and reinforcing fibers extending therein by connecting areas that adjoin one another in an overlapping region of the interconnected intermediate products, with the method including applying an adhesive layer with an adhesive film with connecting particles onto the connecting areas of the intermediate products, arranging the second intermediate product on the first intermediate product or vice versa so the connecting areas at least partially overlap one another, and connecting the two intermediate products. A structural component is also disclosed with at least a first and a second fiber-reinforced intermediate product.

Abstract: A method for coupling a first and a second stiffening element for a skin of an aircraft or spacecraft, wherein the first stiffening element has a cross-sectional profile with first and second web portions extending from a flange portion of a predefined width toward the skin includes forming a coupling zone of the first stiffening element wherein the second web portion is at least partially removed to expose an inner surface of the first web portion, and a step of fastening a coupling element, for coupling the stiffening elements, to the coupling zone of the first stiffening element.

Abstract: A method of manufacturing a shell component for an aircraft or spacecraft includes positioning a skin panel, which includes a skin of the aircraft or spacecraft and first and second stringers stiffening the skin, opposite a frame having first and second mouseholes for receiving the first and second stringers, elastically bending the skin panel, inserting the first stringer into the first mousehole, and releasing the elastic bend to insert the second stringer into the second mousehole.

Abstract: A jitter analysis system includes an electronic circuit having a noisy electrical signal with jitter along a baseline of the signal. The jitter analysis system also includes a sampling unit coupled to the noisy electrical signal that provides waveform samples of the noisy electrical timing signal and a jitter detection unit coupled to the sampling unit that provides baseline crossings of the noisy electrical signal, wherein the baseline crossings are determined from a selection of the waveform samples proximate the baseline of the signal. A jitter determination method is also provided.

Abstract: One embodiment of the present invention sets forth a method for detecting defective solder balls that includes configuring a transmitter pad to transmit a pulse signal, transmitting the pulse signal, configuring transmitter pad to receive a pulse reflection, receiving a pulse reflection, analyzing the pulse reflection; and determining whether the pulse reflection is indicative of a defective solder ball. One advantage of the disclosed method is that solder ball defects may be detected more accurately than in the trial and error approach.

Abstract: A method for the manufacture of a fibre composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mould core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fibre composite component with a multiplicity of openings, each of which is edged by an integral collar.

Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.

Abstract: An aircraft frame comprising a first partial aircraft frame configured to be attached to a first aircraft fuselage segment and a second partial aircraft frame configured to be attached to a second aircraft fuselage segment is provided. The first partial aircraft frame and the second partial aircraft frame are configured to be connected to each other to be in a connected configuration forming the aircraft frame such that the first fuselage segment and the second fuselage segment are connectable.

Abstract: An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.

Abstract: Method for connecting two intermediate products for forming a fiber composite product, wherein the two intermediate products respectively are composite fiber material with a layer of matrix material and reinforcing fibers extending therein by connecting areas that adjoin one another in an overlapping region of the interconnected intermediate products, with the method including applying an adhesive layer with an adhesive film with connecting particles onto the connecting areas of the intermediate products, arranging the second intermediate product on the first intermediate product or vice versa so the connecting areas at least partially overlap one another, and connecting the two intermediate products. A structural component is also disclosed with at least a first and a second fiber-reinforced intermediate product.

Abstract: A dipping device for a milking system, especially for an automatic milking system designed as a milking robot with teat cups to be placed onto the teats of an animal to be milked, which is designed for contacting the teats of the animal with at least one fluid or several fluids, and the device has several dipping valve arrangements so that the dipping agent introduction to each teat of the animal can be controlled separately.

Abstract: A synchronous memory device is configured to switch into and out of a full speed mode to change speed the speed of data transactions without significantly disturbing the frequency of a clock input to a PLL or DLL that provides the internal clock for the synchronous memory device. Since the PLL or DLL receives a clock signal whether or not the synchronous memory device is in a non-full speed mode, the PLL or DLL does not need to settle or relock when the clock signal is reapplied to exit a different speed mode and return to the full speed mode. Therefore, the latency incurred to switch into and out of different speed modes is reduced by eliminating or substantially reducing the time for settling or relocking the PLL or DLL.

Abstract: A synchronous memory device is configured to switch into and out of a full speed mode to change speed the speed of data transactions without significantly disturbing the frequency of a clock input to a PLL or DLL that provides the internal clock for the synchronous memory device. Since the PLL or DLL receives a clock signal whether or not the synchronous memory device is in a non-full speed mode, the PLL or DLL does not need to settle or relock when the clock signal is reapplied to exit a different speed mode and return to the full speed mode. Therefore, the latency incurred to switch into and out of different speed modes is reduced by eliminating or substantially reducing the time for settling or relocking the PLL or DLL.

Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.