Checkout Phase Research Articles

Physical supermarkets and digital integration: acceptance of the cashierless concept

ABSTRACT The checkout phase in the large-scale retail sector is one of the critical points of the physical shopping experience. Cashierless payment technologies are expected to play a fundamental role in the checkout phase as they help by saving time and reducing queues. This study aims at investigating the acceptance and intention to use of the most prominent innovative solutions for a cashierless grocery store. The Unified Theory of Acceptance and Use of Technology is the theoretical framework taken as a reference for this study and is tested by means of a questionnaire sent to customers of a prominent regional supermarket chain in Northern Italy.

OCO-3 early mission operations and initial (vEarly) XCO2 and SIF retrievals

NASA's Orbiting Carbon Observatory-3 (OCO-3) was installed on the International Space Station (ISS) on 10 May 2019. OCO-3 combines the flight spare spectrometer from the Orbiting Carbon Observatory-2 (OCO-2) mission, which has been in operation since 2014, with a new Pointing Mirror Assembly (PMA) that facilitates observations of non-nadir targets from the nadir-oriented ISS platform. The PMA is a new feature of OCO-3, which is being used to collect data in all science modes, including nadir (ND), sun-glint (GL), target (TG), and the new snapshot area mapping (SAM) mode.This work provides an initial assessment of the OCO-3 instrument and algorithm performance, highlighting results from the first 8 months of operations spanning August 2019 through March 2020. During the In-Orbit Checkout (IOC) phase, critical systems such as power and cooling were verified, after which the OCO-3 spectrometer and PMA were subjected to a series of rigorous tests. First light of the OCO-3 spectrometer was on 26 June 2019, with full science operations beginning on 6 August 2019. The OCO-3 spectrometer on-orbit performance is consistent with that seen during preflight testing. Signal to noise ratios are in the expected range needed for high quality retrievals of the column-averaged carbon dioxide (CO2) dry-air mole fraction (XCO2) and solar-induced chlorophyll fluorescence (SIF), which will be used to help quantify and constrain the global carbon cycle.The first public release of OCO-3 Level 2 (L2) data products, called “vEarly”, is being distributed by NASA's Goddard Earth Sciences Data and Information Services Center (GES DISC). The intent of the vEarly product is to evaluate early mission performance, facilitate comparisons with OCO-2 products, and identify key areas to improve for the next data release. The vEarly XCO2 exhibits a root-mean-squared-error (RMSE) of ≃ 1, 1, 2 ppm versus a truth proxy for nadir-land, TG&SAM, and glint-water observations, respectively. The vEarly SIF shows a correlation with OCO-2 measurements of >0.9 for highly coincident soundings. Overall, the Level 2 SIF and XCO2 products look very promising, with performance comparable to OCO-2. A follow-on version of the OCO-3 L2 product containing a number of refinements, e.g., instrument calibration, pointing accuracy, and retrieval algorithm tuning, is anticipated by early in 2021.

Installation and first operation of the International Fusion Materials Irradiation Facility injector at the Rokkasho site.

The International Fusion Materials Irradiation Facility (IFMIF) linear IFMIF prototype accelerator injector dedicated to high intensity deuteron beam production has been designed, built, and tested at CEA/Saclay between 2008 and 2012. After the completion of the acceptance tests at Saclay, the injector has been fully sent to Japan. The re-assembly of the injector has been performed between March and May 2014. Then after the check-out phase, the production of the first proton beam occurred in November 2014. Hydrogen and deuteron beam commissioning is now in progress after having proceeded with the final tests on the entire injector equipment including high power diagnostics. This article reports the different phases of the injector installation pointing out the safety and security needs, as well as the first beam production results in Japan and chopper tests. Detailed operation and commissioning results (with H(+) and D(+) 100 keV beams) are reported in a second article.

INITIAL CHECKOUT RESULTS OF THE COMPACT INFRARED CAMERA (CIRC) FOR EARTH OBSERVATION

Abstract. Compact Infrared Camera (CIRC) is a technology-demonstration instrument equipped with an uncooled infrared array detector (microbolometer) for space application. CIRC is the first microbolometer sensor without a calibration function in orbit, like a shutter system or an onboard blackbody. The main objective of the CIRC is to detect wildfires, which are major and chronic disasters affecting various countries of Southeast Asia, particularly considering the effects of global warming and climate change. The CIRC achieves a small size (approximately 200 mm), light mass (approximately 3 kg), and low electrical power consumption (<20 W) by employing athermal optics and a shutterless system. The CIRC can be consequently mounted on multiple satellites to enable highfrequency observation. Installation of CIRCs on the ALOS-2 and on the JEM/CALET is expected to increase observation frequency. We present the initial check-out results of the CIRC onboard ALOS-2. Since the initial check-out phase (July 4–14, 2014), the CIRC has acquired the images of Earth. CIRC was demonstrated to function according to its intended design. After the early calibration validation phase, which confirmed the temperature accuracy of observed data, CIRC data has been available to the public January 2015 onward. We also introduce a few observational results about wildfire, volcanoes, and heat-island.

Landsat continuity mission set for launch

While the Landsat Data Continuity Mission (LDCM), scheduled for launch on 11 February, is expected to continue Landsat's more than 40‐year continuous record of providing Earth surface data, the future of the program beyond that mission—which will be renamed as Landsat 8 after its initial space checkout phase—is unclear, according to an official with the U.S. Geological Survey (USGS).

Chang’E-1 precision orbit determination and lunar gravity field solution

In this paper we present results assessing the role of Very Long Baseline Interferometry (VLBI) tracking data through precision orbit determination (POD) during the check-out phase for Chang’E-1, and the lunar gravity field solution CEGM-01 based on the orbital tracking data acquired during the nominal phase of the mission. The POD of Chang’E-1 is performed using S-band two-way Range and Range Rate (R&RR) data, together with VLBI delay and delay rate observations. The role of the VLBI data in the POD of Chang’E-1 is analyzed, and the resulting orbital accuracies are estimated for different solution strategies. The final orbital accuracies proved that the VLBI tracking data can improve the Chang’E-1 POD significantly. Consequently, CEGM-01 based on six-month tracking data during Chang’E-1 nominal mission phase is presented, and the accuracy of the model is assessed by means of the gravity field power spectrum, admittance and coherence between gravity and topography, lunar surface gravity anomaly and POD for both Chang’E-1 and Lunar Prospector (LP). Our analysis indicates that CEGM-01 has significant improvements over a prior model (i.e. GLGM-2), and shows the potential of Chang’E-1 tracking data in high resolution lunar gravity field model solution by combining with SELENE and LP tracking data.

In-orbit calibration of the lunar magnetometer onboard SELENE (KAGUYA)

Abstract The high-sensitivity fluxgate Lunar MAGnetometer (LMAG) is mounted on SELENE (KAGUYA) to investigate the near-surface electromagnetic environment and the evolution of the Moon through magnetic field observation. To avoid possible electromagnetic interferences, a triaxial fluxgate sensor (MGF-S) is installed at the far end of a 12-m-long mast. It is critical for the accurate observation to monitor MGF-S alignment in orbit, and thus we have calibrated the sensor alignment by measuring the known magnetic fields generated by the sensor alignment monitor coil (SAM-C) wound onto the mast canister. In-orbit calibration of the MGF-S alignment was performed twice each revolution during the initial check-out phase of the satellite. It is concluded that there is no systematic difference in the sensor alignment between the day-side and night-side. Applying a new technique based on the Davis-Smith method to the observed magnetic field data when KAGUYA was exposed to the solar wind, a zero offset of each axis was quickly and stably determined every month. As a result, LMAG has been calibrated with an accuracy that is sufficient for detection of the lunar magnetic anomaly at an altitude of 100 km and for high-resolution electron reflectometry.

Forced Precessions of the IMAGE Spacecraft

IMAGE (Imager for Magnetopause-to-Aurora Global Exploration), NASA’s first Medium-class Explorer (MIDEX) mission, was led by Southwest Research Institute, successfully captured global neutral atom images of the Earth’s inner magnetosphere and far and extreme ultraviolet images of the aurora and plasmasphere, respectively, and performed radio sounding of various magnetospheric boundaries and regions, during the period May 2000 to December 2005. During the in-orbit checkout and deployment phase of IMAGE, two significant spacecraft attitude modes meriting further study became apparent. The first was an unanticipated forced precession of the core body driven by the spin-plane wire antennas of the Radio Plasma Imager (RPI), with an initial period on the order of 20 minutes. The second was a slower precession of the entire system, driven by gravity gradient acting on the extended wire spin plane and having a period of approximately 105 days. Star Trackers onboard the spacecraft enabled the periods of both motions to be very well constrained by attitude observations. Both motions are analyzed and calculated rates are compared to rates observed in star-tracker data for the actual system.

The Dawn project's transition to mission operations: On its way to rendezvous with (4) Vesta and (1) Ceres

Dawn launched on 27 September 2007 on a mission to orbit main belt asteroids (4) Vesta in 2011–2012 and (1) Ceres in 2015. The operations team conducted an extensive set of assessments of the engineering subsystems and science instruments during the first 80 days of the mission. A major objective of this period was to thrust for one week with the ion propulsion system to verify flight and ground systems readiness for typical interplanetary operations. Upon successful conclusion of the checkout phase, the interplanetary cruise phase began, most of which will be devoted to thrusting. The flexibility afforded by the use of ion propulsion enabled the project to accommodate a launch postponement of more than three months caused by a combination of launch vehicle and tracking system readiness, unfavorable weather, and then conflicts with other launches. Even with the shift in the launch date, all of the science objectives are retained with the same schedule and greater technical margins. This paper describes the conclusion of the development phase of the project, launch operations, and the progress of mission operations through the conclusion of deterministic thrusting in October 2008.

Preliminary Results of the SELENE Terrain Camera

On September 14, 2007, Moon explorer SELENE (Kaguya) was launched to the Moon carrying a 10-m spatial resolution stereo-camera, the Terrain Camera (TC). Particular mission objectives of the TC include Polar regions and Mare regions such as Oceanus Procellarum, South-Pole to Aitken basin, and Mare Orientale, that have not been observed with TC's high-resolution stereoscopy. The first TC data of the Moon were obtained on Nov. 3, 2007. We confirmed 1) that the TC had not generated any defective pixels and would achieve high signal-to-noise ratio (S/N) performance and 2) that the TC could provide high-quality data in the Polar regions and a 180 km region extending from 60N to 66N along 240E. We could acquire scientific information from ortho images and digital terrain models (DTMs) produced from these TC first data. On Nov. 24, 2007, we acquired several sequential strip data, from which a seamless mosaicked TC ortho image and DTMs were successfully produced. These seamless mosaicked data will be very useful for investigating large mare regions. After completion of the nominal checkout phase on Dec. 21, 2007, the TC began the nominal mission operation phase with other mission instruments. Thus, we could confirm that TC will provide fundamental assets for lunar science from the initial checkout phase data.

On-Orbit System Identification Experiments of the Engineering Test Satellite-VIII

This paper presents the results of on-orbit system identification of the Engineering Test Satellite-VIII (ETS-VIII), which was launched by the H-IIA Launch Vehicle No. 11 in December 2006. On-orbit system identification experiments were performed using data acquired during normal operations in the initial check-out phase, such as station acquisition and wheel unloading. The satellite's unconstrained modes were identified using attitude rates and data from accelerometers located on the main body, solar array paddles and large deployable antenna reflectors at various solar array paddle angles. In addition, the constrained modal parameters of the solar array paddles and large deployable antenna reflectors were estimated for comparison with the analytical model.

The Columbus-CC—Operating the European laboratory at ISS

The European ISS Columbus Control Center (Col-CC) joined the club of ISS mission control centers in Moscow, Houston and Huntsville. It took some time to reach that goal. In 1998 the European Space Agency (ESA) awarded the German Aerospace Center DLR to design, develop and implement the Col-CC at its premises in Oberpfaffenhofen, near Munich, Germany. In 2002 a core mission operations team was built up. An integrated team of ESA, industry and control center started to define processes and implemented first operations products and tools. This was accompanied by regular meetings with the international partners in the US and Russia. With intensive training and numerous simulations the team was able to gain experience and is now eagerly waiting for the launch of Columbus. However, thanks to the involvement in some operational activities the Col-CC staff has already been able to gain operational ISS experience. After the inauguration in October 2004 Col-CC supported the Eneide mission in April 2005 when the Italian ESA-Astronaut Roberto Vittori flew onboard a Soyuz to the ISS where he spent 10 days. Another very important milestone was the operations support for ESA's Astrolab mission. The Astrolab mission was of major importance for Europe and particularly for Germany because it implied the first long duration flight of ESA astronaut Thomas Reiter, an astronaut of German nationality. The tasks of Col-CC are described and also the experiences made with the first operational long-term mission which took place from July to December 2006. Meanwhile the Col-CC was able to reach the operational readiness status for the Columbus mission which is set for a launch date later in 2007. Despite the concentration on the challenging Columbus Assembly and Checkout phase emphasis is already laid on the following increments for the European ISS operations. Early 2006 ESA transferred the operational tasks and responsibilities to the hands of the industrial operator. This approach creates beneficial synergies between the Columbus manufacturer and the experts at the control center. The cooperation will be further intensified with ESA, as the leading agency, the scientific users and the payload providers. The integrated operations team consists of technical and management experts from all involved parties, with key functions distributed among the partners according to the expertise available.

The FirstSwiftX‐Ray Flash: The Faint Afterglow of XRF 050215B

We present the discovery of XRF 050215B and its afterglow. The burst was detected by the Swift BAT during the check-out phase and observations with the X-ray telescope began approximately 30 minutes after the burst. These observations found a faint, slowly fading X-ray afterglow near the centre of the error box as reported by the BAT. Infrared data, obtained at UKIRT after 10 hours also revealed a very faint K-band afterglow. The afterglow appear unusual since it is very faint, especially in the infrared with K>20 only 9 hours post burst. The X-ray and infrared lightcurves exhibit a slow, monotonic decay with alpha=0.8 and no evidence for steepening associated with the jet break to 10 days post burst. We discuss possible explanations for the faintness and slow decay in the context of present models for the production of X-ray Flashes.

The Parsec-Scale Jet of PKS 0637−752

Abstract Chandra observations of the quasar PKS 0637$-$752 during its checkout phase resulted in the unexpected detection of a luminous kiloparsec-scale X-ray jet. The apparent superluminal speed of this jet on the parsec-scale, based on two VSOP and four ground-based observations, has proven crucial to understanding the X-ray production in the arcsec-scale jet. We present here for the first time the full details of the ground-based observations used to determine the parsec-scale jet speed, describe the results of a third VSOP observation, and examine the reported jet speed in the light of more recent ground-based VLBI observations. We find some evidence of increased source activity coincident with extrapolated epochs of jet component ejection, although the monitoring of the source is relatively sparse and the ejection epochs are not tightly constrained. We also construct the spectral energy distribution for the nucleus of PKS 0637$-$752 and show that it can be modelled well in terms of a one-zone synchrotron self-Compton model of an electron-positron jet with a Doppler factor of $\sim 10$, consistent with the results of the VLBI observations.

3402 技術試験衛星VIII型による軌道上システム同定実験計画(S87-1 飛翔体のモデリングとシステム同定(1),S87 飛翔体のモデリングとシステム同定)

This paper studies on-orbit system idntification experiment on Engineering Test Satellite-VIII (ETS-VIII), which will be launched in 2006 by H-IIA type 204 rocket. This will become the largest three-axis stabilized geoshncronous satellite in Japan. In the experiment, flexible parameters of large deployable antenna and large solar panels will be estimated by the downlinked telemetry data of stellite attitude and solar panel mounted accelerometers during the satellite check-out phase. We developed "ACFS Tool" for estimating onboard satellite attitude states using dwell data in the telemetry. In this paper, we show the the validity of the tool by numerical simulation.

Chandra X-Ray Observatory Arcsecond Imaging of the Young, Oxygen-rich Supernova Remnant 1E 0102.2-7219.

We present observations of the young, oxygen-rich supernova remnant 1E 0102.2-7219 taken by the Chandra X-Ray Observatory during its orbital activation and checkout phase. The boundary of the blast-wave shock is clearly seen for the first time, allowing the diameter of the remnant and the mean blast-wave velocity to be determined accurately. The prominent X-ray bright ring of material may be the result of the reverse shock encountering ejecta; the radial variation of O vii versus O viii emission indicates an ionizing shock propagating inward, possibly through a strong density gradient in the ejecta. We compare the X-ray emission with Australia Telescope Compact Array 6 cm radio observations (Amy & Ball) and with archival Hubble Space Telescope [O iii] observations. The ring of radio emission is predominantly inward of the outer blast wave, which is consistent with an interpretation of synchrotron radiation originating behind the blast wave but outward of the bright X-ray ring of emission. Many (but not all) of the prominent optical filaments are seen to correspond to X-ray bright regions. We obtain an upper limit of approximately 9x1033 ergs s-1 (3 sigma) on any potential pulsar X-ray emission from the central region.

FUSE Spectra of Sk 80, an 07 Supergiant in the Small Magellanic Cloud

We present far-UV spectra (910-1190Å) of Sk 80, an 07 supergiant in the Small Magellanic Cloud, observed by the FUSE satellite during its In-Orbit Checkout phase. The spectra reveal many interstellar absorption lines, including H2, and O VI, and several key stellar wind features.

In-Orbit Performance of the Far Ultraviolet Spectroscopic Explorer

The Far Ultraviolet Spectroscopic Explorer (FUSE) satellite was launched by a Delta II rocket on 24 June 1999 into a ˜768 km, 25° orbit. Following the In-Orbit Checkout phase, FUSE is obtaining high-resoluti on spectra (λ/Δλ ≳ 20,000) in the spectral range 905 −1187 Å. The sensitivity meets or exceeds the pre-launch predictions. Many QSOs and AGNs have already been observed.

Extreme Ultraviolet Explorer observations of the RS Canum Venaticorum systems AR Lacertae and II Pegasi

view Abstract Citations (8) References (16) Co-Reads Similar Papers Volume Content Graphics Metrics Export Citation NASA/ADS Extreme Ultraviolet Explorer Observations of the RS Canum Venaticorum Systems AR Lacertae and II Pegasi Patterer, R. J. ; Vedder, P. W. ; Jelinsky, P. ; Brown, A. ; Bowyer, S. Abstract We report observations of two RS CVn systems, II Peg and AR Lac, which were calibration targets during the in-orbit checkout phase of the Extreme Ultraviolet Explorer (EUVE). We have determined count rates, and, based on these count rates, preliminary emission measure analyses have been done. The Lexan/boron band count rates were 0.0849 +/- 0.0023 counts/s for AR Lac and 0.218 +/- 0.031 counts/s for II Peg during its quiescent state. Temperatures and emission measures derived from the EUVE data are consistent with previously published values. We also report a flare seen during the II Peg observations which has characteristics similar to previously observed flares on II Peg. During the flare the Lexan/boron count rate increased by at least a factor of 2.5, and the minimum total duration was about 34,000 s (about 9.4 hr). Publication: The Astrophysical Journal Pub Date: September 1993 DOI: 10.1086/186995 Bibcode: 1993ApJ...414L..57P Keywords: Eclipsing Binary Stars; Extreme Ultraviolet Explorer Satellite; G Stars; K Stars; Astronomical Satellites; Emission Spectra; Stellar Coronas; Stellar Flares; Astrophysics; STARS: CORONAE; STARS: INDIVIDUAL CONSTELLATION NAME: AR LACERTAE; STARS: INDIVIDUAL CONSTELLATION NAME: II PEGASI; STARS: LATE-TYPE full text sources ADS | data products SIMBAD (2) MAST (1)

Development of a Requirements Classification Scheme for Automated Support of Software Development

Computer hardware technology has advanced to the point where it is feasible to develop software systems that exceed one million lines of code. Software engineering, the discipline concerned with developing these systems, typically includes the following phases in the software development cycle: requirements phase, design phase, implementation phase, test phase and the installation and checkout phase [IEEE, 1983]. This paper is concerned with a classification scheme to support knowledge-based analysis of software requirements. Because requirements in these large systems can become quite numerous and complex, it is a very difficult task to analyze them in order to identify potential problems, i.e., problems that may arise in later phases, such as incompleteness, conflict, ambiguity, and absence of testability. Current software productivity tools such as CASE (Computer-Aided Software Engineering), executable requirements languages, prototyping tools, and test harnesses provide much assistance in later phases of software development, but not much for the requirements phase. It is well-known in software engineering that the most costly and profound software errors are likely to occur at the requirements definition phase, early in the software development cycle. The productivity tools mentioned earlier either work from code which has been developed for the system. or work with user requirements statements which have been translated into a restricted, formal language. There are several problems with translating user requirements into a formal language very early in the project First, it is difficult for the user to understand requirements as they have been translated and interpreted by the systems analyst. Second, the systems analyst may have made wrong assumptions or interpretations in the process of translation. Finally, formal languages do not have any provision for ambiguity, and early in the requirements phase, ambiguities may exist, to be worked out as more is learned about the system.