Find research datasets worth reusing
Search datasets from major research repositories and use ShareScore to quickly assess how well each record supports discovery, access, and reuse.
326
datasets available to search
ShareScore release 0.9.0
Dataset results
326 results for “electricity data”
Apollo 17 Surface Electrical Properties Experiment Calibrated ASCII Data Bundle
This bundle contains two comma-delimited ASCII files of calibrated lunar surface electromagnetic field and navigation (range) data from the Surface Electrical Properties (SEP) Experiment at the Apollo 17 landing site for the time span of 11-13 December 1972. One file contains straightened science and navigation (range) data; the other file contains only unstraightened science data. These data were extracted from binary files held on magnetic tape at the NASA Space Science Data Coordinated Archive as data set PSPG-00559, then reformatted to ASCII. This bundle also contains a high-resolution digital reproduction of the SEP final technical report that contains plots of the complete set of processed lunar field data, as decibal values versus range, and explanations the data processing and calibration techniques implemented by the SEP instrument team.
MMS 2 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Ions, Level 2 (L2), Burst Mode, 0.3025 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Burst Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 4 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Electrons, Level 2 (L2), Survey Mode, 2.42 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Survey Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 4 Electron Drift Instrument (EDI) Electric Field, Level 2 (L2), Burst Mode, 0.9765625 ms Data
Electron Drift Instrument (EDI) Electric Field Burst Survey, Level 2, 0.0009765625 s Data (1024 samples/s). EDI has two scientific data acquisition modes, called electric field mode and ambient mode. In electric field mode, two coded electron beams are emitted such that they return to the detectors after one or more gyrations in the ambient magnetic and electric field. The firing directions and times-of-flight allow the derivation of the drift velocity and electric field. In ambient mode, the electron beams are not used. The detectors with their large geometric factors and their ability to adjust the field of view quickly allow continuous sampling of ambient electrons at a selected pitch angle and fixed but selectable energy. To find the beam directions that will hit the detector, EDI sweeps each beam in the plane perpendicular to B at a fixed angular rate of 0.22 °/ms until a signal has been acquired by the detector. Once signal has been acquired, the beams are swept back and forth to stay on target. Beam detection is not determined from the changes in the count-rates directly, but from the square of the beam counts divided by the background counts from ambient electrons, i.e., from the square of the instantaneous signal-to-noise ratio (SNR). This quantity is computed from data provided by the correlator in the Gun-Detector Electronics that also generates the coding pattern imposed on the outgoing beams. If the squared SNR ratio exceeds a threshold, this is taken as evidence that the beam is returning to the detector. The thresholds for SNR are chosen dependent on background fluxes. They represent a compromise between getting false hits (induced by strong variations in background electron fluxes) and missing true beam hits. The basic software loop that controls EDI operations is executed every 2 ms. As the times when the beams hit their detectors are neither synchronized with the telemetry nor equidistant, EDI data have no fixed time-resolution. Data are reported in telemetry slots. In Survey, using the standard packing mode 0, there are eight telemetry slots per second and Gyn Detector Unit (GDU). The last beam detected during the previous slot will be reported in the current slot. If no beam has been detected, the data quality will be set to zero. In Burst telemetry there are 128 slots per second and GDU. The data in each slot consists of information regarding the beam firing directions (stored in the form of analytic gun deflection voltages), times-of-flight (if successfully measured), quality indicators, time stamps of the beam hits, and some auxiliary correlator-related information. Whenever EDI is not in electron drift mode, it uses its ambient electron mode. The mode has the capability to sample at either 90 degrees pitch angle or at 0/180 degrees (field aligned), or to alternate between 90 degrees and field aligned with selectable dwell times. While all options have been demonstrated during the commissioning phase, only the field aligned mode has been used in the routine operations phase. The choices for energy are 250 eV, 500 eV, and 1 keV. The two detectors, which are facing opposite hemispheres, are looking strictly into opposite directions, so while one detector is looking along B the other is looking antiparallel to B (corresponding to pitch angles of 180 and 0 degrees, respectively). The two detectors switch roles every half spin of the spacecraft as the tip of the magnetic field vector spins outside the field of view of one detector and into the field of view of the other detector. This is the primary data product generated from data collected in electric field mode. The science data generated are drift velocity and electric field data in various coordinate systems. They are derived from triangulation and/or time-of-flight analysis. Where both methods are applicable, their results will be combined using a weighting approach based on their relative errors. The EDI instrument paper can be found at: http://link.springer.com/article/10.1007%2Fs11214-015-0182-7. The EDI instrument data products guide can be found at https://lasp.colorado.edu/mms/sdc/public/datasets/fields/.
MMS 1 Electron Drift Instrument (EDI) Electric Field, Level 2 (L2), Burst Mode, 0.9765625 ms Data
Electron Drift Instrument (EDI) Electric Field Burst Survey, Level 2, 0.0009765625 s Data (1024 samples/s). EDI has two scientific data acquisition modes, called electric field mode and ambient mode. In electric field mode, two coded electron beams are emitted such that they return to the detectors after one or more gyrations in the ambient magnetic and electric field. The firing directions and times-of-flight allow the derivation of the drift velocity and electric field. In ambient mode, the electron beams are not used. The detectors with their large geometric factors and their ability to adjust the field of view quickly allow continuous sampling of ambient electrons at a selected pitch angle and fixed but selectable energy. To find the beam directions that will hit the detector, EDI sweeps each beam in the plane perpendicular to B at a fixed angular rate of 0.22 °/ms until a signal has been acquired by the detector. Once signal has been acquired, the beams are swept back and forth to stay on target. Beam detection is not determined from the changes in the count-rates directly, but from the square of the beam counts divided by the background counts from ambient electrons, i.e., from the square of the instantaneous signal-to-noise ratio (SNR). This quantity is computed from data provided by the correlator in the Gun-Detector Electronics that also generates the coding pattern imposed on the outgoing beams. If the squared SNR ratio exceeds a threshold, this is taken as evidence that the beam is returning to the detector. The thresholds for SNR are chosen dependent on background fluxes. They represent a compromise between getting false hits (induced by strong variations in background electron fluxes) and missing true beam hits. The basic software loop that controls EDI operations is executed every 2 ms. As the times when the beams hit their detectors are neither synchronized with the telemetry nor equidistant, EDI data have no fixed time-resolution. Data are reported in telemetry slots. In Survey, using the standard packing mode 0, there are eight telemetry slots per second and Gyn Detector Unit (GDU). The last beam detected during the previous slot will be reported in the current slot. If no beam has been detected, the data quality will be set to zero. In Burst telemetry there are 128 slots per second and GDU. The data in each slot consists of information regarding the beam firing directions (stored in the form of analytic gun deflection voltages), times-of-flight (if successfully measured), quality indicators, time stamps of the beam hits, and some auxiliary correlator-related information. Whenever EDI is not in electron drift mode, it uses its ambient electron mode. The mode has the capability to sample at either 90 degrees pitch angle or at 0/180 degrees (field aligned), or to alternate between 90 degrees and field aligned with selectable dwell times. While all options have been demonstrated during the commissioning phase, only the field aligned mode has been used in the routine operations phase. The choices for energy are 250 eV, 500 eV, and 1 keV. The two detectors, which are facing opposite hemispheres, are looking strictly into opposite directions, so while one detector is looking along B the other is looking antiparallel to B (corresponding to pitch angles of 180 and 0 degrees, respectively). The two detectors switch roles every half spin of the spacecraft as the tip of the magnetic field vector spins outside the field of view of one detector and into the field of view of the other detector. This is the primary data product generated from data collected in electric field mode. The science data generated are drift velocity and electric field data in various coordinate systems. They are derived from triangulation and/or time-of-flight analysis. Where both methods are applicable, their results will be combined using a weighting approach based on their relative errors. The EDI instrument paper can be found at: http://link.springer.com/article/10.1007%2Fs11214-015-0182-7. The EDI instrument data products guide can be found at https://lasp.colorado.edu/mms/sdc/public/datasets/fields/.
MMS 4 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Ions, Level 2 (L2), Survey Mode, 2.42 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Survey Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 1 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Electrons, Level 2 (L2), Burst Mode, 0.3025 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Burst Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 1 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Ions, Level 2 (L2), Burst Mode, 0.3025 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Burst Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 3 Electric Particle Detector, Fly's Eye Energetic Particle Sensor (EPD, FEEPS) Ions, Level 2 (L2), Survey Mode, 2.42 s Data
Fly's Eye Electron Proton Spectrometer (FEEPS) Survey Data. The Energetic Particle Detector (EPD) investigation aboard the four MMS spacecraft consists of two instrument designs, the FEEPS and the EIS (Energetic Ion Spectrometer). A FEEPS consists of six Heads, each composed of two Eyes. Each eye is a particle telescope with a single silicon detector. There are nine electron eyes and three ion eyes per FEEPS. The energy coverage is from 25 keV to 650 keV for electrons and 45 keV to 650 keV for ions. Each eye has sixteen energy channels, the spacing of which can be modified by command. The fields of view and pointing of each eye are designed to provide a broad, instantaneous field of view for the twelve eyes per FEEPS.
MMS 3 Electron Drift Instrument (EDI) Electric Field, Level 2 (L2), Burst Mode, 0.9765625 ms Data
Electron Drift Instrument (EDI) Electric Field Burst Survey, Level 2, 0.0009765625 s Data (1024 samples/s). EDI has two scientific data acquisition modes, called electric field mode and ambient mode. In electric field mode, two coded electron beams are emitted such that they return to the detectors after one or more gyrations in the ambient magnetic and electric field. The firing directions and times-of-flight allow the derivation of the drift velocity and electric field. In ambient mode, the electron beams are not used. The detectors with their large geometric factors and their ability to adjust the field of view quickly allow continuous sampling of ambient electrons at a selected pitch angle and fixed but selectable energy. To find the beam directions that will hit the detector, EDI sweeps each beam in the plane perpendicular to B at a fixed angular rate of 0.22 °/ms until a signal has been acquired by the detector. Once signal has been acquired, the beams are swept back and forth to stay on target. Beam detection is not determined from the changes in the count-rates directly, but from the square of the beam counts divided by the background counts from ambient electrons, i.e., from the square of the instantaneous signal-to-noise ratio (SNR). This quantity is computed from data provided by the correlator in the Gun-Detector Electronics that also generates the coding pattern imposed on the outgoing beams. If the squared SNR ratio exceeds a threshold, this is taken as evidence that the beam is returning to the detector. The thresholds for SNR are chosen dependent on background fluxes. They represent a compromise between getting false hits (induced by strong variations in background electron fluxes) and missing true beam hits. The basic software loop that controls EDI operations is executed every 2 ms. As the times when the beams hit their detectors are neither synchronized with the telemetry nor equidistant, EDI data have no fixed time-resolution. Data are reported in telemetry slots. In Survey, using the standard packing mode 0, there are eight telemetry slots per second and Gyn Detector Unit (GDU). The last beam detected during the previous slot will be reported in the current slot. If no beam has been detected, the data quality will be set to zero. In Burst telemetry there are 128 slots per second and GDU. The data in each slot consists of information regarding the beam firing directions (stored in the form of analytic gun deflection voltages), times-of-flight (if successfully measured), quality indicators, time stamps of the beam hits, and some auxiliary correlator-related information. Whenever EDI is not in electron drift mode, it uses its ambient electron mode. The mode has the capability to sample at either 90 degrees pitch angle or at 0/180 degrees (field aligned), or to alternate between 90 degrees and field aligned with selectable dwell times. While all options have been demonstrated during the commissioning phase, only the field aligned mode has been used in the routine operations phase. The choices for energy are 250 eV, 500 eV, and 1 keV. The two detectors, which are facing opposite hemispheres, are looking strictly into opposite directions, so while one detector is looking along B the other is looking antiparallel to B (corresponding to pitch angles of 180 and 0 degrees, respectively). The two detectors switch roles every half spin of the spacecraft as the tip of the magnetic field vector spins outside the field of view of one detector and into the field of view of the other detector. This is the primary data product generated from data collected in electric field mode. The science data generated are drift velocity and electric field data in various coordinate systems. They are derived from triangulation and/or time-of-flight analysis. Where both methods are applicable, their results will be combined using a weighting approach based on their relative errors. The EDI instrument paper can be found at: http://link.springer.com/article/10.1007%2Fs11214-015-0182-7. The EDI instrument data products guide can be found at https://lasp.colorado.edu/mms/sdc/public/datasets/fields/.
Cluster-Rumba Wideband Data (WBD) Plasma Wave Receiver/High Time Resolution Electric and Magnetic Waveform Data Returned via BM2
The following description applies to the Wideband Data (WBD) Plasma Wave Receivers on all four Cluster satellites, each satellite being uniquely identified by its number (1 through 4) or its given name (Rumba, Salsa, Samba, Tango, respectively). High time resolution calibrated waveform data sampled in one of 3 frequency bands in the range 0-577 kHz along one axis using either an electric field antenna or a magnetic search coil sensor. The dataset also includes instrument mode, data quality and the angles required to orient the measurement with respect to the magnetic field and to the GSE coordinate system. The AC electric field data are obtained by using one of the two 88m spin plane electric field antennas of the EFW (Electric Fields and Waves) instrument as a sensor. The AC magnetic field data are obtained by using one of the two search coil magnetometers (one in the spin plane, the other along the spin axis) of the STAFF (Spatio-Temporal Analysis of Field Fluctuations) instrument as a sensor. The WBD data are obtained in one of three filter bandwidth modes: (1) 9.5 kHz, (2) 19 kHz, or (3) 77 kHz. The minimum frequency of each of these three frequency bands can be shifted up (converted) from the default 0 kHz base frequency by 125.454, 250.908 or 501.816 kHz. The time resolution of the data shown in the plots is determined from the WBD instrument mode. The highest time resolution data (generally the 77 kHz bandwidth mode) are sampled at 4.6 microseconds in the time domain (~4.7 milliseconds in the frequency domain using a standard 1024 point FFT). The lowest time resolution data (generally the 9.5 kHz bandwidth mode) are sampled at 36.5 microseconds in the time domain (~37.3 milliseconds in the frequency domain using a standard 1024 point FFT). The availability of these files depends on times of Panska Ves ground station telemetry downlinks. A list of the status of the WBD instrument on each spacecraft, the telemetry time spans, operating modes and other details are available under Science Data Availability on the University of Iowa Cluster WBD web site at http://www- pw.physics.uiowa.edu/cluster/ and through the documentation section of the Cluster Science Archive (CSA) (https://www.cosmos.esa.int/web/csa/documentation). Details on Cluster WBD Interpretation Issues and Caveats can be found at http://www- pw.physics.uiowa.edu/cluster/ by clicking on the links next to the Caution symbol in the listing on the left side of the web site. These documents are also available from the Documentation section of the CSA website. For further details on the Cluster WBD data products see Pickett, J.S., et al., "Cluster Wideband Data Products in the Cluster Active Archive" in The Cluster Active Archive, 2010, Springer-Verlag, pp 169-183, and the Cluster WBD User Guide archived at the CSA website in the Documentation section. ... CALIBRATION: ... The procedure used in computing the calibrated Electric Field and Magnetic Field values found in this file can be obtained from the Cluster WBD Calibration Report archived at the CSA website in the Documentation section. Because the calibration was applied in the time domain using simple equations the raw counts actually measured by the WBD instrument can be obtained by using these equations and solving for 'Raw Counts', keeping in mind that this number is an Integer ranging from 0 to 255. Since DC offset is a real number, the resultant when solving for raw counts will need to be converted to the nearest whole number. A sample IDL routine for reverse calibrating to obtain 'Raw Counts' is provided in the WBD Calibration Report archived at the CSA. ... CONVERSION TO FREQUENCY DOMAIN: ... In order to convert the WBD data to the frequency domain via an FFT, the following steps need to be carried out: 1) If Electric Field, first divide calibrated data values by 1000 to get V/m; 2) Apply window of preference, if any (such as Hann, etc.); 3) Divide data values by sqrt(2) to get back to the rms domain; 4) perform FFT (see Bandwidth variable notes for non-continuous modes and/or the WBD User Guide archived at the CSA); 5) divide by the noise bandwidth, which is equal to the sampling frequency divided by the FFT size (see table below for appropriate sampling frequency); 6) multiply by the appropriate constant for the window used, if any. These steps are more fully explained in the WBD Calibration Report archived at the CSA.... BURST MODE: ... WBD data can also be obtained in a mode called Burst Mode 2 (BM2), stored onboard, and transmitted to the ground with the data from all the other instruments. This mode has been rarely used throughout the mission only once prior to July 2010 (on March 7, 2001), but more often thereafter to obtain data at low altitude or in the high priority auroral acceleration region, because it results in decreased bandwidth or a higher degree of duty cycling for WBD. NASA's Deep Space Network terminated WBD data acquisition in February 2015 and after that date WBD
Supporting data for "Health benefits of US light-duty vehicle electrification: roles of fleet dynamics, clean electricity, and policy timing"
<p>Supporting data for the manuscript "Health benefits of US light-duty vehicle electrification: roles of fleet dynamics, clean electricity, and policy timing". Contains the files generated by FLAME-AQ for the scenarios included in the publication.</p> <p>The FLAME-AQ model is available here: https://github.com/jean-schmitt/FLAME-AQ</p>
Expression data from HDFA cells exposed to nanosecond duration electrical pulses
GEO Series GSE77906. Homo sapiens. 9 samples. Type: Expression profiling by array.
Expression data from electrically-altered larval Drosophila LNvs
GEO Series GSE27565. Drosophila melanogaster. 27 samples. Type: Expression profiling by array.
Electric consumption data
Open the record for dataset details and reuse information.
DE 1 Retarding Ion Mass Spectrometer (RIMS) Low Channel, H+ and He++, and High Channel, He+, O+, and O++, Density, Temperature, and Electric Potential, 1 min Data
The Data were provided by Dennis Gallagher, MSFC. The Retarding Ion Mass Spectrometer, RIMS, consisted of a Retarding Potential Analyzer for Energy Analysis in Series with a Magnetic Ion-Mass Spectrometer for Mass Analysis. Multiple Sensor Heads permitted the Determination of the Thermal Plasma Flow Characteristics. This Instrument was designed to operate in two basic Commandable Modes: a High-Altitude mode in which the Density, Temperature, and Bulk Flow Characteristics of principally H+, He+, and O+ Ions were measured, and a Low-Altitude Mode that concentrated on the Composition in the 1-u to 32-u Range. This Investigation provided Information on: (1) The Densities of H+, He+, and O+ Ions in the Ionosphere, Plasmasphere, Plasma Trough, and Polar Cap including the Density Distribution along the Magnetic Vector in the Vicinity of the Satellite Apogee (2) The Temperature of H+, He+, and O+ Ions in the Ionosphere, Plasmasphere, Plasma Trough, and Polar Cap in the Energy Range from 0 eV to 45 eV (3) The Bulk Flow Velocities of H+, He+, and O+ in the Plasmapause, Plasma Trough and Polar Cap (4) The changing Character of the Cold Plasma Density, Temperature, and Bulk Flow in Regions of Interaction with Hot Plasma such as at the Boundary between the Plasmasphere and the Ring Current (5) The detailed Composition of Ionospheric Plasma in the Range from 1-u to 32-u He++ and O++ were also measured. The Instrument consisted of three Detector Heads. One looked out in the Radial Direction, and the other two looked out along the Plus and Minus Spin Axis Directions. Each Detector had a 55° half-cone Acceptance Angle. The Detector Heads had a gridded, weakly collimating Aperture where the Retarding Analysis was performed, followed by a Parallel Plate Ceramic Magnetic Mass Analyzer with two separate Exit Slits corresponding to Ion Masses in the Ratio 1:4. Ions exiting from these Slits were detected with Electron Multipliers. In the Apogee Mode, the Thermal Particle Fluxes were measured while the Potential on a Set of Retarding Grids was stepped through a Sequence of Settings. In the Perigee Mode, the Retarding Grids were grounded and the Detector utilized a Continuous Acceleration Potential Sweep that focused the Mass Ranges from 1 to 8, and 4-u to 32-u. The Time Resolution was 16 ms. Additional Details can be found in C.R. Chappell et al., Space Sci. Instrum., 5(4), 477, 1981. The Criterion for selecting Data Points to be appropriate for fitting include that the Aperature Bias equal to zero must have at least ten or more Non-Zero Points in the RPA Curve. If the Spacecraft Altitude was less that 1.3 Re, the High Voltage Monitor must be turned on, the Maximum Counter Rate Value must at least 5.0, and there must be at least four Points starting from the End of RPA Curve. Find three consecutive Points of increasing Value, reset the End of the RPA Curve to here and make certain that the last Point is one Sigma above the Noise Level (the Points excluded in previous Step). if not, then drop a Point and check the new last Point, continue until the Criteria is met. One must have at least three Points left starting at new End of the selected RPA Curve Stop first Point greater that 80% of the Maximum of Spin Curve. If not found, stop at the last Point that is less than the Maximum. There must be at least three Points left. Change the Curve from the Count Rate Curve to the l**2 Curve. If Number of Points are five or less, then do a Linear Least Squares Fit (LINFIT) to the Data. If the Linear Correlation Coefficient (LCC) greater than 0.8 then the Points will be used, if not, the data set is discarded. If the Number of Points are greater then five, then do a LINFIT to the bottom five and a LINFIT to the top five Points. If there are six or more Points, then apply LINFIT to the middle Set of five Points, saving the LCC and Slope for each Case. If all three LCCs are less than 0.800, then discard the Data Set. Through a Series of Tests, find the Set of five Points with the best LCC Slope Combination. Once the Set of five Points has been selected, add the Rest of the Points one at a time and recompute the LLC with LINFIT, if the LCC gets worse discard the added Point otherwise keep it, do this until all Points are checked. Once this Procedure is completed, the final Set of Points have been determined.
MMS 4 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Fast Mode, 31.25 ms Data
Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Fast Survey Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.
MMS 1 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Slow Mode, 0.125 s Data
Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Slow Survey Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.
MMS 4 Digital Signal Processor (DSP) Double Probe (ADP, SDP), Electric Field Power Spectral Density, Level 2 (L2), Slow Mode, 16 s Data
The MMS electric field power spectral density (EPSD) is computed onboard by the Digital Signal Processor (DSP). The fast Fourier transform (FFT) calculation is performed on a digitized version of analog signals from the Axial Double Probe (ADP) and Spin-Plane Double Probe (SDP). This data product is computed in space from individual components that are not synchronized to the 1 second pulse. Therefore, the timing between channels can be inaccurate by a fraction of a second. The samples times are interval start times taken from the x component. The spectra are calculated via a 1024-point FFT algorithm on piecewise continuous sets of waveform data. Nine signals can be processed simultaneously. Six of the twelve DC-coupled E, DC-coupled V, or SCM signals (16384 samples/s) are selected for spectral processing at 100% duty cycle. In addition, the three AC-coupled signals (262,144 kS/s) each can be processed at 6.25% duty cycle. Each of the nine signals has 16, 1024-point FFT operations every second; the field-programmable gate array (FPGA) performs 144 FFTs per second. The FFT is performed by an arithmetic logic unit (ALU), which is controlled by a state machine. Both are hard-coded into the FPGA. The operation starts by applying a 1024-point Hanning window onto a waveform. Next, an FFT is implemented. The FFT is broken into a series of "butterfly" operations performed by the ALU. The result has real and imaginary data. Power spectra are calculated by taking the sum of squares of real and imaginary values (the ALU includes a multiplier), which produces a power spectrum with 512 frequency bins. The frequency bins are then combined to give pseudo-logarithmic frequency spacing (del f)/f. The spectra are reduced to 56 frequency bins with (del f)/f between 6% and 12% when possible. Narrow-band emissions can be fit to an accuracy of (del f)/f ~3%, allowing for an accurate determination of plasma density. The spectra can be averaged in time. The fastest reporting rate of any signal is 16 spectra per second. Reporting rates can be as slow a one spectra every 16 s (averaging 256 spectra). The averaging process has 48-bit accuracy to maximize the dynamic range. The amplitudes undergo a pseudo-logarithmic compression to an 8-bit number representing over 120 dB of dynamic range at ~5% precision.
MMS 3 Electric Double Probe (EDP) Spacecraft Potential, Level 2 (L2), Burst Mode, 0.1220703125 ms Data
Electric Double Probe, Dual Probe Spacecraft Potential, Level 2, Burst Mode Data. Spacecraft potential is etstimatrd by averaging measurements of the probe-to-spacecraft potential from several probes.
ScienceDex guides
Understand access before you commit
These curated guides explain access requirements, typical timelines, costs, and reuse considerations for widely used research datasets.
Allen Brain Atlas
Allen Brain Atlas is an Allen Institute collection of brain map atlases, datasets, APIs, and analysis tools covering mouse, human, and non-human primate brain resources.
Annotated Behaviour and Observability Dataset (ABODe)
ABODe is a University of Edinburgh DataShare dataset for behavior classification in group-housed mice using home-cage video, identities, bounding boxes, ground-plate positions, and annotator labels.
DANDI Archive for NWB datasets
DANDI is a BRAIN Initiative archive for publishing and sharing neurophysiology data, including electrophysiology, optophysiology, and behavioral data packaged as NWB and related standards.
International Brain Laboratory public data
The International Brain Laboratory public data releases expose standardized mouse decision-making experiments, including Neuropixels recordings, widefield calcium imaging, behavior, and session metadata accessed through the ONE API.
OpenNeuro
OpenNeuro is a free, open platform for sharing neuroimaging datasets, with public search, dataset pages, and download paths for web, S3, DataLad, and the OpenNeuro CLI.