370 research outputs found

    When and why physicians deceive : interactions with third-party payers

    Get PDF

    Deformation induced phase transformation in Zr3Al studied by transmission electron microscopy

    Get PDF
    Die Herstellung nanokristalliner Materialien durch extreme plastische Verformung grobkristalliner Strukturen wird seit rund zwei Jahrzehnten intensiv erforscht. Trotz des Potentials, Materialeigenschaften durch Nanostrukturierung zu verĂ€ndern, wurden nanokristalline intermetallische Legierungen noch nicht umfassend untersucht. In dieser Arbeit wird die intermetallische Verbindung Zr3Al, die die geordnete L12 Struktur aufweist, zum ersten Mal extrem plastisch verformt und die dabei auftretenden StrukturĂ€nderungen untersucht. Die dabei zum Einsatz kommenden Verformungsmethoden sind Hochdrucktorsion sowie wiederholtes Kaltwalzen und Falten. Hochdrucktorsion bei Raumtemperatur fĂŒhrt zu nanokristallinen Proben und ermöglicht einen systematischen Vergleich zwischen Zr3Al und anderen hochverformten Verbindungen, die ursprĂŒnglich die L12 Struktur aufweisen. Dieser Vergleich liefert ein tieferes VerstĂ€ndnis des Einflusses der verschiedenen Versetzungsaufspaltungsmechanismen auf die Kornverfeinerung und die verformungsinduzierten Phasenumwandlungen. Eine raster- und durchstrahlungselektronenmikroskopische Betrachtung der verformten Proben ermöglicht die Untersuchung von strukturellen InhomogenitĂ€ten ab der atomaren Skala bis hin zu einer LĂ€ngenskala, die der ProbengrĂ¶ĂŸe entspricht. Dabei werden Abweichungen von einem idealen Torsionsexperiment sowie der Wechsel der Verformungsmechanismen mit zunehmender Kornverfeinerung erklĂ€rt. Die Verformung von Zr3Al durch wiederholtes Kaltwalzen und Falten fĂŒhrt zu amorphen Proben. Damit wird der Einfluss der verschiedenen Verformungsmethoden auf die SĂ€ttigungsstruktur gezeigt. Weiters werden kalorimetrische Messungen angewandt, um Auskunft ĂŒber die thermische StabilitĂ€t und das Kristallisationsverhalten des durch Walzen amorphisierten Materials zu erhalten. Die unvollstĂ€ndige Amorphisierung, die Restnanokristallite im Material verursacht, begĂŒnstigt wĂ€hrend des Aufheizens der Probe die Bildung einer nanokristallinen Phase. HĂ€rtemessungen und Röntgendiffraktometrie ergĂ€nzen all diese Studien durch Informationen ĂŒber die mechanischen und integralen strukturellen Eigenschaften. Durch die Untersuchung verschiedener Verformungsmethoden sowie der InhomogenitĂ€ten der Verformung durch Hochdrucktorsion kann diese Arbeit einen wesentlichen Beitrag zum physikalischen VerstĂ€ndnis der StrukturĂ€nderungen von intermetallischen Verbindungen durch extreme plastische Verformung liefern.The production of nanocrystalline materials by severe plastic deformation of coarse grained structures has been attracting a lot of research interest for the last two decades. Despite the potential to change and tailor material properties by nanostructuring, there are rather limited data available for nanocrystalline intermetallic alloys. In this work, severe plastic deformation of the ordered L12 structured intermetallic compound Zr3Al and the study of deformation induced structural changes are conducted for the first time. Zr3Al is heavily deformed by the methods of high pressure torsion and repeated cold rolling with intermediate foldings. The deformation by high pressure torsion at room temperature leads to nanocrystalline samples and allows a systematic comparison to other L12 compounds subjected to high pressure torsion. This comparison facilitates the understanding of the influence of different dislocation dissociation mechanisms on the grain refinement characteristics and on the deformation induced phase transitions of these materials. A multi-scale analysis of the deformed Zr3Al samples by transmission and scanning electron microscopy using both plan view and cross section samples allows to assess inhomogeneities from the atomic scale to the scale of the sample, revealing important deviations from the ideal torsion experiment and the change of deformation mechanisms with decreasing grain size. The deformation by repeated cold rolling with intermediate foldings leads to amorphous samples, thus unambiguously showing the different effects of the deformation methods on the saturation structure. In addition, calorimetric measurements yield information about the thermal stability and the crystallization behaviour of the material amorphized by rolling. It is shown that imperfect amorphization involving residual nanocrystallites facilitates the crystallization of a fine nanocrystalline structure. Hardness measurements by microindentation and X-ray diffractometry supplement these studies by yielding information on the mechanical properties and integral structural properties of deformed samples, respectively. By studying different deformation methods and the inhomogeneity of the deformation by high pressure torsion, this work is an important contribution to the physical understanding of structural changes of intermetallic compounds by severe plastic deformation

    SpaceCube Version 1.5

    Get PDF
    SpaceCube 1.5 is a high-performance and low-power system in a compact form factor. It is a hybrid processing system consisting of CPU (central processing unit), FPGA (field-programmable gate array), and DSP (digital signal processor) processing elements. The primary processing engine is the Virtex- 5 FX100T FPGA, which has two embedded processors. The SpaceCube 1.5 System was a bridge to the SpaceCube 2.0 and SpaceCube 2.0 Mini processing systems. The SpaceCube 1.5 system was the primary avionics in the successful SMART (Small Rocket/Spacecraft Technology) Sounding Rocket mission that was launched in the summer of 2011. For SMART and similar missions, an avionics processor is required that is reconfigurable, has high processing capability, has multi-gigabit interfaces, is low power, and comes in a rugged/compact form factor. The original SpaceCube 1.0 met a number of the criteria, but did not possess the multi-gigabit interfaces that were required and is a higher-cost system. The SpaceCube 1.5 was designed with those mission requirements in mind. The SpaceCube 1.5 features one Xilinx Virtex-5 FX100T FPGA and has excellent size, weight, and power characteristics [443 in. (approx. = 10108 cm), 3 lb (approx. = 1.4 kg), and 5 to 15 W depending on the application]. The estimated computing power of the two PowerPC 440s in the Virtex-5 FPGA is 1100 DMIPS each. The SpaceCube 1.5 includes two Gigabit Ethernet (1 Gbps) interfaces as well as two SATA-I/II interfaces (1.5 to 3.0 Gbps) for recording to data drives. The SpaceCube 1.5 also features DDR2 SDRAM (double data rate synchronous dynamic random access memory); 4- Gbit Flash for storing application code for the CPU, FPGA, and DSP processing elements; and a Xilinx Platform Flash XL to store FPGA configuration files or application code. The system also incorporates a 12 bit analog to digital converter with the ability to read 32 discrete analog sensor inputs. The SpaceCube 1.5 design also has a built-in accelerometer. In addition, the system has 12 receive and transmit RS- 422 interfaces for legacy support. The SpaceCube 1.5 processor card represents the first NASA Goddard design in a compact form factor featuring the Xilinx Virtex- 5. The SpaceCube 1.5 incorporates backward compatibility with the Space- Cube 1.0 form factor and stackable architecture. It also makes use of low-cost commercial parts, but is designed for operation in harsh environments

    SpaceCube Mini

    Get PDF
    This version of the SpaceCube will be a full-fledged, onboard space processing system capable of 2500+ MIPS, and featuring a number of plug-andplay gigabit and standard interfaces, all in a condensed 3x3x3 form factor [less than 10 watts and less than 3 lb (approximately equal to 1.4 kg)]. The main processing engine is the Xilinx SIRF radiation- hardened-by-design Virtex-5 FX-130T field-programmable gate array (FPGA). Even as the SpaceCube 2.0 version (currently under test) is being targeted as the platform of choice for a number of the upcoming Earth Science Decadal Survey missions, GSFC has been contacted by customers who wish to see a system that incorporates key features of the version 2.0 architecture in an even smaller form factor. In order to fulfill that need, the SpaceCube Mini is being designed, and will be a very compact and low-power system. A similar flight system with this combination of small size, low power, low cost, adaptability, and extremely high processing power does not otherwise exist, and the SpaceCube Mini will be of tremendous benefit to GSFC and its partners. The SpaceCube Mini will utilize space-grade components. The primary processing engine of the Mini is the Xilinx Virtex-5 SIRF FX-130T radiation-hardened-by-design FPGA for critical flight applications in high-radiation environments. The Mini can also be equipped with a commercial Xilinx Virtex-5 FPGA with integrated PowerPCs for a low-cost, high-power computing platform for use in the relatively radiation- benign LEOs (low-Earth orbits). In either case, this version of the Space-Cube will weigh less than 3 pounds (.1.4 kg), conform to the CubeSat form-factor (10x10x10 cm), and will be low power (less than 10 watts for typical applications). The SpaceCube Mini will have a radiation-hardened Aeroflex FPGA for configuring and scrubbing the Xilinx FPGA by utilizing the onboard FLASH memory to store the configuration files. The FLASH memory will also be used for storing algorithm and application code for the PowerPCs and the Xilinx FPGA. In addition, it will feature highspeed DDR SDRAM (double data rate synchronous dynamic random-access memory) to store the instructions and data of active applications. This version will also feature SATA-II and Gigabit Ethernet interfaces. Furthermore, there will also be general-purpose, multi-gigabit interfaces. In addition, the system will have dozens of transceivers that can support LVDS (low-voltage differential signaling), RS-422, or SpaceWire. The SpaceCube Mini includes an I/O card that can be customized to meet the needs of each mission. This version of the SpaceCube will be designed so that multiple Minis can be networked together using SpaceWire, Ethernet, or even a custom protocol. Scalability can be provided by networking multiple SpaceCube Minis together. Rigid-Flex technology is being targeted for the construction of the SpaceCube Mini, which will make the extremely compact and low-weight design feasible. The SpaceCube Mini is designed to fit in the compact CubeSat form factor, thus allowing deployment in a new class of missions that the previous SpaceCube versions were not suited for. At the time of this reporting, engineering units should be available in the summer 2012

    Modelling of Innovative SANEX Process Maloperations

    Get PDF
    The innovative (i-) SANEX process for the separation of minor actinides from PUREX highly active raffinate is expected to employ a solvent phase comprising 0.2M TODGA with 5 v/v% 1-octanol in an inert diluent. An initial extract / scrub section would be used to extract trivalent actinides and lanthanides from the feed whilst leaving other fission products in the aqueous phase, before the loaded solvent is contacted with a low acidity aqueous phase containing a sulphonated bis-triazinyl pyridine ligand (BTP) to effect a selective strip of the actinides, so yielding separate actinide (An) and lanthanide (Ln) product streams. This process has been demonstrated in lab scale trials at JĂŒlich (FZJ). The SACSESS (Safety of ACtinide SEparation proceSSes) project is focused on the evaluation and improvement of the safety of such future systems. A key element of this is the development of an understanding of the response of a process to maloperations. It is only practical to study a small subset of possible maloperations experimentally and consideration of the majority of maloperations entails the use of a validated dynamic model of the process. Distribution algorithms for HNO3, Am, Cm and the lanthanides have been developed and incorporated into a dynamic flowsheet model that has, so far, been configured to correspond to the extract-scrub section of the i-SANEX flowsheet trial undertaken at FZJ in 20131. Comparison is made between the steady state model results and experimental results. Results from modelling of low acidity and high temperature maloperations are presented

    Boom‐bust dynamics in biological invasions: towards an improved application of the concept

    Get PDF
    Boom‐bust dynamics – the rise of a population to outbreak levels, followed by a dramatic decline – have been associated with biological invasions and offered as a reason not to manage troublesome invaders. However, boom‐bust dynamics rarely have been critically defined, analyzed, or interpreted. Here, we define boom‐bust dynamics and provide specific suggestions for improving the application of the boom‐bust concept. Boom‐bust dynamics can arise from many causes, some closely associated with invasions, but others occurring across a wide range of ecological settings, especially when environmental conditions are changing rapidly. As a result, it is difficult to infer cause or predict future trajectories merely by observing the dynamic. We use tests with simulated data to show that a common metric for detecting and describing boom‐bust dynamics, decline from an observed peak to a subsequent trough, tends to severely overestimate the frequency and severity of busts, and should be used cautiously if at all. We review and test other metrics that are better suited to describe boom‐bust dynamics. Understanding the frequency and importance of boom‐bust dynamics requires empirical studies of large, representative, long‐term data sets that use clear definitions of boom‐bust, appropriate analytical methods, and careful interpretations

    Spacecube V2.0 Micro Single Board Computer

    Get PDF
    A single board computer system radiation hardened for space flight includes a printed circuit board having a top side and bottom side; a reconfigurable field programmable gate array (FPGA) processor device disposed on the top side; a connector disposed on the top side; a plurality of peripheral components mounted on the bottom side; and wherein a size of the single board computer system is not greater than approximately 7 cm.times.7 cm
    • 

    corecore