ULYSSES In Space

 

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ULYSSES

Ulysses HISCALE Data Analysis Handbook

 

List of Figures

 

  • Figure 2.1 ISPM EDR record format
  • Figure 4.1 HISCALE viewing cones with respect to Ulysses spin axis
  • Figure 4.2 LAN2A and LAN2B simplified cross-sections
  • Figure 4.3a LAN2A cross section detail (M'F')
  • Figure 4.3b LAN2B telescope assembly WART cross section detail
  • Figure 4.3c LAN2B assembly MF cross section detail
  • Figure 4.3d LAN2B telescope assembly, exterior view MF-WART
  • Figure 4.4 HISCALE instrument assembly photograph
  • Figure 4.4a LAN assembly field of view drawing
  • Figure 4.4b HISCALE assembly FOV drawing, detail a
  • Figure 4.4c HISCALE assembly FOV drawing, detail b
  • Figure 4.4d Outline flight model LAN experiment, detail 1
  • Figure 4.4e Outline flight model LAN experiment, detail 2
  • Figure 4.4f Outline of flight model LAN experiment
  • Figure 4.5 LAN attached to Ulysses, view 1
  • Figure 4.6 LAN attached to Ulysses, view 2
  • Figure 4.7 External view of LAN2A (M'F'), view 1
  • Figure 4.8 External view of LAN2A (M'F'), view 2
  • Figure 4.9 Assembly cross section of LAN2A
  • Figure 4.10 Magnetic yoke section, type 1
  • Figure 4.11 Magnetic yoke front view, type 1
  • Figure 4.12 Magnetic yoke section back view, type 1
  • Figure 4.13 Section of magnet yoke, type 1
  • Figure 4.14 External view of LAN2B (MF-WART)
  • Figure 4.15 Section of LAN2B (aperture sketch)
  • Figure 4.16 Magnet yoke type 2, front view
  • Figure 4.17 Magnet yoke type 2: cross section
  • Figure 4.18 Magnetic yoke section, type 2, back view
  • Figure 4.19 LEMS detector mount
  • Figure 4.20 Notch in deflection system
  • Figure 4.21 Section of detector housing
  • Figure 4.22 Parts list, LAN2B assembly
  • Figure 4.23 Foil assembly
  • Figure 4.24 Foil mount
  • Figure 4.25 HISCALE digital signal block diagram
  • Figure 4.26 Energy losses in LEMS30
  • Figure 4.27 Energy losses in LEMS120
  • Figure 4.28 Energy losses in LEFS60
  • Figure 4.29 Energy losses for LEFS150
  • Figure 4.30 Composition aperture energy losses
  • Figure 4.31 Delta E versus E for composition aperture (WART)
  • Figure 4.32 WART channel definitions
  • Figure 4.33 Data system block diagram
  • Figure 4.34 Data system software block diagram
  • Figure 4.35 Science data format
  • Figure 4.36 EDR summary diagram
  • Figure 4.37 EDR summary list
  • Figure 4.38 Data input-output timing diagram
  • Figure 4.39 Status preamble definitions, bytes 1-3
  • Figure 4.40 Status preamble definitions, bytes 4-6
  • Figure 4.41 CA priority byte 4-81
  • Figure 4.42a Status trailer format
  • Figure 4.42b Status trailer format, continued
  • Figure 4.43 Digital housekeeping format, channels 2-4
  • Figure 4.44 Obtaining rate data values by adding modulus
  • Figure 4.45 Telemetry mode changes
  • Figure 4.46 Sector definitions for 0£ LAG<TSPIN/8
  • Figure 4.47 Sector definitions for TSpin/8£ Lag<TSpin/4
  • Figure 4.48 Sun sensor configuration
  • Figure 4.49 XBS geometry
  • Figure 4.50 Sun sensor electronics
  • Figure 4.51 AME sun sensor electronics
  • Figure 4.52 SRP filter flow chart
  • Figure 4.53 Implementation of the SSC
  • Figure 4.54 Flow chart for the reconstitution of the SRP
  • Figure 4.55 Error of SRP, double crossing
  • Figure 4.56 Error of SRP, single crossing
  • Figure 4.57 Orientation of LAN2B magnet in electron beam
  • Figure 4.58 Schematic ISPM LAN2B telescope
  • Figure 4.59 Determination of electronic counting thresholds using a calibrated pulser
  • Figure 4.60 LAN2B B detector electron detection efficiency, energy=40 keV
  • Figure 4.61 LAN2B B detector electron detection efficiency, energy=100 keV
  • Figure 4.62 LAN2B angular location of B peak efficiency
  • Figure 4.63 LAN2B B detector peak electron efficiency as f (energy)
  • Figure 4.64 Electron energy deposited in detector F
  • Figure 4.65 Electron detection efficiency of detector F LAN2B as f (energy)
  • Figure 4.66 Electron detection efficiency 30° CCW
  • Figure 4.67 Electron detection efficiency 20° CCW
  • Figure 4.68 Electron detection efficiency 10° CCW
  • Figure 4.69 Electron detection efficiency 0°
  • Figure 4.70 Electron detection efficiency 10° CW
  • Figure 4.71 Electron detection efficiency 20° CW
  • Figure 4.72 Electron detection efficiency 30° W
  • Figure 4.73 PHA matrix for Rutgers Composition Aperture calibration
  • Figure 4.74 LAN flight model Rutgers beam calibration 4-141
  • Figure 4.75 Plots of G vs. E for all eight trials 4-143
  • Figure 4.76a Spectra plots for the DE and two LEFS channels using IDF.DAT G-factors
  • Figure 4.76b Spectra plots for the same time period using Trial 10 G-factors
  • Figure 4.76c Spectra plots for the same time period using Table 4.18 G-factors
  • Figure 4.77a Ratio plots for all four energy channels for a 32-day period
  • Figure 4.77b Ratio plots for a later time period in 1991
  • Figure 4.77c Ratio plots including the electron event around day 301
  • Figure 4.77d Ratio plots for a 32-day period in 1992
  • Figure 4.78 A plot comparing Kohl's electron efficiency study with the simulation
  • Figure 4.79 Comparison of simulation results to S/C data – LEMS120
  • Figure 4.80 Comparison of simulation results to S/C data – LEMS30
  • Figure 4.81 Comparison of simulation results to S/C data – LEFS60
  • Figure 4.82 Comparison of simulation results to S/C data – LEFS150
  • Figure 4.83 Flow chart for RTG simulation
  • Figure 4.84 Cosmic ray case 2 and case 3
  • Figure 4.85 Cosmic ray case 1 and total
  • Figure 4.86 Calculations of penetration geometry, part I
  • Figure 4.87 Calculations of penetration geometry, part II
  • Figure 4.88 LAN "Rosetta Stone" for sectors
  • Figure 4.89 LAN detectors angular response
  • Figure 4.90 RTG response in MFSA (M¢ detector)
  • Figure 4.91 LAN RTG tests
  • Figure 4.92 Solar polar temperature conversion
  • Figure 5.1 Variation of the background excess over the values in Table 5.8 with latitude for all the main rate channels
  • Figure 5.2 Preliminary attempts to fit a latitude-dependent background level to the P7, P2, and DE2 channels
  • Figure 5.3 Daily average P¢ 3 and DE3 rates vs. heliolatitude
  • Figure 5.4 Rates versus heliolatitude for all HISCALE channels
  • Figure 5.5 The HISCALE instrument (photo)
  • Figure 5.6 Configuration of LAN detector telescopes
  • Figure 5.7 LEMS120 cover (outside)
  • Figure 5.8 SEEPHA plot during 92049 calibration
  • Figure 5.9 Enlargement of PHA matrix
  • Figure 5.10 LANSPECT output for 92049 calibration
  • Figure 5.11 COMP spectrum and composition ratios
  • Figure 5.12 Calibration plots of WART and DE channels vs. time
  • Figure 5.13 Calibration plots of P¢ and P channels vs. time 5-25
  • Figure 5.14 Calibration in B, C, and D channels vs. time
  • Figure 5.15 Calibration count rates vs. time since launch
  • Figure 5.16 Best fits to He decay
  • Figure 5.17 Best fits to RTG background
  • Figure 5.18 PHA matrix for 92049 calibration
  • Figure 5.19 PHA matrix for 92049 calibration
  • Figure 5.20 Thirty-two channel spectra for 5 calibrations
  • Figure 5.21 PHA matrix for 92049 calibration
  • Figure 5.22 SPECTIME output for 94091
  • Figure 5.23 Z2 time plots during calibrations
  • Figure 5.24 Beginning of 93008 calibration
  • Figure 5.25 Open/close cover times vs. AU
  • Figure 5.26 PHA matrix plot during polar pass
  • Figure A2-1 Look angles for the five detector telescopes for the LAN experiment
  • Figure A2-2 LAN360 plot for channel P6 for hours 22-24 UT on day 82, 1991
  • Figure A2-3 Diagram showing the 16 sectors that are used to determine the anisotropies for the spacecraft X-Z plane, the detectors from which the measurements are made, and their final location on the LAN360 plot
  • Figure A2-4 LAN plot for WART channels in the XY plane for hours 0-24 UT on day 33, 1992 when Ulysses entered the Jovian magnetosphere
  • Figure A2-5a LAN plot for channel P5 for hours 14-24 UT on day 33, 1992
  • Figure A2-5b Plot with smooth = 1
  • Figure A2-5c Setting foilfact to 0.0 allows the ion anisotropies in this energy range after 2130 UT to be seen
  • Figure A3-1 Ulysses CDR – solar wind plasma and magnetic field – 98 244 Sep 1
  • Figure A3-2 Ulysses CDR – solar wind plasma and magnetic field – 98 260 Sep 17
  • Figure A3-3 Ulysses CDR – energetic particles, low energy ions and cosmic ray – 98 244 Sep 1
  • Figure A3-4 Ulysses CDR – energetic particles, low energy ions and cosmic ray – 98 260 Sep 17
  • Figure A3-5 Ulysses CDR – plasma wave – 98 244 Sep 1
  • Figure A3-6 Ulysses CDR – plasma wave – 98 260 Sep 17
  • Figure A3-7 Ulysses CDR – solar wind ion composition – 98 244 Sep 1
  • Figure A3-8 Ulysses CDR – solar wind ion composition – 98 260 Sep 17
  • Figure A4-1 ULS SFDU primary and secondary header format
  • Figure A4-2 ULS SFDU tertiary header format
  • Figure A4-3 Ulysses CDF File 1 format
  • Figure A4-4 Ulysses CDF File 2 format
  • Figure A6-1 HISCALE hourly average of spin average rates, type 1, without QCA (E1' – FP6')
  • Figure A6-2 HISCALE hourly average of spin average rates, type 2, without QCA (FP7' – P5')
  • Figure A6-3 HISCALE hourly average of spin average rates, type 3, without QCA (P6' – W3)
  • Figure A6-4 HISCALE hourly average of spin average rates, type 4, without QCA (W4 – Z2)
  • Figure A6-5 HISCALE hourly average of spin average rates, type 5, without QCA (Z2A – E3)
  • Figure A6-6 HISCALE hourly average of spin average rates, type 6, without QCA (E4 – P2)
  • Figure A6-7 HISCALE hourly average of spin average rates, type 7, without QCA (P3 – P8)
  • Figure A6-8 HISCALE hourly average of spin average rates, type 8, without QCA (DE1 – C WARTC)
  • Figure A6-9 HISCALE hourly average of spin average rates, type 9, without QCA (D WARTD – F')
  • Figure A6-10 HISCALE hourly average of spin average rates, type 10, without QCA (X-Ray P1 – X-ray P2)
  • Figure A6-11 HISCALE hourly average of spin average rates, type 1, with QCA (E1' – FP6')
  • Figure A6-12 HISCALE hourly average of spin average rates, type 2, with QCA (FP7' – P5')
  • Figure A6-13 HISCALE hourly average of spin average rates, type 3, with QCA (P6' – W3)
  • Figure A6-14 HISCALE hourly average of spin average rates, type 4, with QCA (W4 – Z2)
  • Figure A6-15 HISCALE hourly average of spin average rates, type 5, with QCA (Z2A – E3)
  • Figure A6-16 HISCALE hourly average of spin average rates, type 6, with QCA (E4 – P2)
  • Figure A6-17 HISCALE hourly average of spin average rates, type 7, with QCA (P3 – P8)
  • Figure A6-18 HISCALE hourly average of spin average rates, type 8, with QCA (DE1 – C WARTC)
  • Figure A6-19 HISCALE hourly average of spin average rates, type 9, with QCA (D WARTD – F')
  • Figure A6-20 HISCALE hourly average of spin average rates, type 10, with QCA (X-Ray P1 – X-ray P2)
  • Figure A7-1 ULS SFDU primary header format
  • Figure A7-2 ULS SFDU secondary header format
  • Figure A7-3 ULS SFDU tertiary header format (EDR)
  • Figure A7-4 ULS EDR record format
  • Figure A7-5 EDR/MDR format layout
  • Figure A7-6 EDR file structure
  • Figure A8-1 SEDR tape layout
  • Figure A8-2 Data block
  • Figure A8-3 Scale Factor Block
  • Figure A8-4 ULS SEDR primary and secondary SFDU headers
  • Figure A8-5 ULS SEDR tertiary SFDU header
  • Figure A9-1 The HISCALE instrument aboard the Ulysses spacecraft
  • Figure A9-2 Electrons entering the LEMS30 aperture are deflected into the back of the Composition Aperture
  • Figure A9-3 Calculating G for simple geometries
  • Figure A9-4 The detector is broken into finite area elements, and the solid angle for each element is determined
  • Figure A9-5 Part of a mechanical drawing used to model the geometry
  • Figure A9-6 The coordinate system adopted for this study
  • Figure A9-7a The modeled geometry as viewed in the xy plane
  • Figure A9-7b The modeled geometry as viewed in the xz plane
  • Figure A9-7c A three-dimensional view of the geometry
  • Figure A9-8 The detector is broken up into finite area elements, and a starting coordinate assigned to each
  • Figure A9-9 The coordinate systems adopted by Kohl and Shodhan
  • Figure A9-10 To determine the solid angle for a particular area element, the electron is placed at the starting coordinate with given starting angles, and its trajectory traced out one line segment at a time.
  • Figure A9-11 For each area element, the number of electrons that escape the system is shown.
  • Figure A9-12 Trajectories of escaping particles for selected energies. The starting coordinate is located at the center of the detector.
  • Figure A9-13 A plot of G vs. E for the Trial 10 B field
  • Figure A9-14 Plots of G vs. E for all eight trials
  • Figure A9-15a Spectra plots for the DE and two LEFS channels using IDF.DAT G-factors
  • Figure A9-15b Spectra plots for the same time period using Trial 10 G-factors
  • Figure A9-15c Spectral plots for the same time period using Table A9-3 G factors
  • Figure A9-16a Ratio plots for all four energy channels for a 32-day period
  • Figure A9-16b Ratio plots for a later time in period in 1991
  • Figure A9-16c Ratio plots including the electron event around day 301
  • Figure A9-16d Ratio plots for a 32-day period in 1992
  • Figure A9-17 A plot comparing Kohl's electron efficiency study with the simulation
  • Figure A9-18 Coordinate labels
  • Figure A9-19 Plane labels
  • Figure A9-20 Geometry of detector segmentation
  • Figure A9-21 Definition of the translation parameters
  • Figure A9-22 Magnetic intensity map
  • Figure A9-23 Results of the observed and calculated values, Z = 0.0 (trials 6 and 10)
  • Figure A9-24 Results of the observed and calculated values, Z = 0.1 (trials 6 and 10)
  • Figure A9-25 Results of the observed and calculated values, Z = -0.1 (trials 6 and 10)
  • Figure A9-26 Results of the observed and calculated values, Z = 0.0 (trials 4 and 11)
  • Figure A9-27 Results of the observed and calculated values, Z = 0.1 (trials 4 and 11)
  • Figure A9-28 Results of the observed and calculated values, Z = -0.1 (trials 4 and 11)
  • Figure A9-29 Results of the observed and calculated values, Z = 0.0 (trials 5 and 12)
  • Figure A9-30 Results of the observed and calculated values, Z = 0.1 (trials 5 and 12)
  • Figure A9-31 Results of the observed and calculated values, Z = -0.1 (trials 5 and 12)
  • Figure A9-32 Results of the observed and calculated values, Z = 0.0 (trials 3 and 13)
  • Figure A9-33 Results of the observed and calculated values, Z = 0.1 (trials 3 and 13)
  • Figure A9-34 Results of the observed and calculated values, Z = -0.1 (trials 3 and 13)
  • Figure A9-35 X vs. Y for 20, 30, 40, and 50 keV electrons, maximum curvature A9-83
  • Figure A9-36 X vs. Y for 75, 100, 150, and 200 keV electrons, maximum curvature
  • Figure A9-37 X vs. Y for 250, 300, 350, and 400 keV electrons, maximum curvature
  • Figure A9-38 X vs. Y for 20, 30, 40, and 50 keV electrons, mid curvature
  • Figure A9-39 X vs. Y for 75, 100, 150, and 200 keV electrons, mid curvature
  • Figure A9-40 X vs. Y for 250, 300, 350, and 400 keV electrons, mid curvature
  • Figure A9-41 X vs. Y for 20, 30, 40, and 50 keV electrons, minimum curvature
  • Figure A9-42 X vs. Y for 75, 100, 150, and 200 keV electrons, minimum curvature
  • Figure A9-43 X vs. Y for 250, 300, 350, and 400 keV electrons, minimum curvature
  • Figure A9-44 Illustration of spectrum fitting
  • Figure A9-45 Efficiency vs. angle for Z = -0.5 cm
  • Figure A9-46 Efficiency vs. angle for Z = 0.0 cm
  • Figure A9-47 Efficiency vs. angle for Z = 0.3 cm
  • Figure A9-48 Efficiency vs. angle for Z = 0.6 cm
  • Figure A9-49 Efficiency vs. angle for Z = 1.0 cm
  • Figure A10-1 The Ulysses spacecraft
  • Figure A10-2 The outline of HISCALE telescopes
  • Figure A10-3 Trajectories of escaped electrons including specular backscattering of the energy for the center detector. Radzimski's backscattering coefficients are used.
  • Figure A10-4 View angle q = 0 deg., f = 90 deg.
  • Figure A10-5 View angle q = -20 deg., f = 80 deg.
  • Figure A10-6 The detector is divided into 21 small DAi
  • Figure A10-7 The number of escapes at each DAi for energy of 50 keV; Radzimski's h is used.
  • Figure A10-8 The geometric factor including specular backscattering; Radzimski's h is used.
  • Figure A10-9 The geometric factor including specular backscattering (both Radzimski's and Neubert's backscattering coefficients) and non-scattering.
  • Figure A10-10 Backscattering coefficient vs. energy, Radzimski model
  • Figure A10-11 Backscattering coefficient vs. energy, Neubert model
  • Figure A10-12 Detector mosaic
  • Figure A10-13 Coordinates used
  • Figure A10-14 Geometry of surface crossing I
  • Figure A10-15 Geometry of surface crossing II
  • Figure A10-16 Geometry of surface crossing III
  • Figure A10-17a View angle of q = 0 deg., f = 90 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-17b View angle of q = 0 deg., f = 90 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-17c View angle of q = 0 deg., f = 90 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-18a View angle of q = -20 deg., f = 80 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-18b View angle of q = -20 deg., f = 80 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-18c View angle of q = -20 deg., f = 80 deg. Radzimski's backscattering coefficients are used.
  • Figure A10-19a View angle of q = 0 deg., f = 90 deg. Neubert's backscattering coefficients are used.
  • Figure A10-19b View angle of q = 0 deg., f = 90 deg. Neubert's backscattering coefficients are used.
  • Figure A10-19c View angle of q = 0 deg., f = 90 deg. Neubert's backscattering coefficients are used.
  • Figure A10-20a View angle of q = -20 deg., f = 80 deg. Neubert's backscattering coefficients are used.
  • Figure A10-20b View angle of q = -20 deg., f = 80 deg. Neubert's backscattering coefficients are used.
  • Figure A10-20c View angle of q = -20 deg., f = 80 deg. Neubert's backscattering coefficients are used.
  • Figure A16-1 LAN PHA system design
  • Figure A16-2 PHAGEN process flow
  • Figure A16-3 LAN PHA generator PHAGEN, top level process flow
  • Figure A16-4 Process_events flow diagram
  • Figure A16-5 Process_mfsa flow diagram
  • Figure A16-6 LAN plots and color displays
  • Figure A16-7 Sample plots of Track Sums and Lanspect
  • Figure A16-8 Sample PHA matrix plot
  • Figure A16-9 Sample SEEMFSA plot
  • Figure A16-10 Sample SPECTIME plot
  • Figure A16-11 Sample SPECPLOT output
  • Figure A16-12 Rate channel energy spectogram display
  • (Figure A16-13 - not available)
  • Figure A16-14 Histograms for each track of the number of counts as a function of displacement in D from the centreline
  • Figure A16-15 Schematic illustration of the determination of the effective minimum energy of a track
  • Figure A17-1 Log channel
  • Figure A17-2 Thermal vac test results for log E channel
  • Figure A17-3 Log amp/sensistor configuration
  • Figure A17-4 Thermal configuration modifications
  • Figure A17-5a PHA width at 25 deg. C (heaters on)
  • Figure A17-5b PHA width, heaters off
  • Figure A17-6 DC offset vs. temperature
  • Figure A17-7 Relocation of S/C Therm 1 on LEMS/LEFS LINEAR board
  • Figure A17-8 Analog wave forms
  • Figure A17-9 SAMA output waveform for 2 of the crosstalk cases
  • Figure A17-10 SAMA output waveform when channel F is excited
  • Figure A17-11a MUX configuration with M' selected
  • Figure A17-11b Equivalent circuit assuming feedthrough capacitance
  • Figure A17-12 Crosstalk-LOG C into LOG D
  • Figure A17-13 LAN pulser test set-up
  • Figure A17-14 Random pulser test results
  • Figure A17-15 Pile-up in D, no effect in C
  • Figure A17-16 Random pulser test results for pile-down
  • Figure A17-17 Pile-down in D, little effect in C
  • Figure A17-18 Pile-down in D (similar to Figure A17-17) associated with a low value of C from the falling edge of the main lobe
  • Figure A18-1 Magnet field survey mechanical setup
  • Figure A18-2 Sketch to indicate axis orientation with respect to magnets
  • Figure A18-3 Sketch to indicate yoke/electron beam orientation on electrostatic accelerator at NASA/GSFC
  • Figure A18-4 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=+0.1"
  • Figure A18-5 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=0
  • Figure A18-6 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=-0.1"
  • Figure A18-7 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=+0.1"
  • Figure A18-8 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=0
  • Figure A18-9 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=-0.1"
  • Figure A18-10 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=+0.1", graphical form
  • Figure A18-11 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-12 Yoke SST 416/APL, Configuration I, Magnets 1 and 2, Y=-0.1", graphical form
  • Figure A18-13 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=+0.1", graphical form
  • Figure A18-14 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-15 Yoke SST 416/APL, Configuration II, Magnets 1 and 2, Y=-0.1", graphical form
  • Figure A18-16 Yoke SST 416/UCB, Configuration I, Magnets 1 and 2, Y=0
  • Figure A18-17 Yoke SST 416/UCB, Configuration I, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-18 Carpenter 49/APL, Configuration I, Magnets 1 and 2, Y=0
  • Figure A18-19 Carpenter 49/APL, Configuration I, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-20 Carpenter 49, Mod 1, Configuration I, Magnets 1 and 2, Y=0
  • Figure A18-21 Carpenter 49, Mod 1, Configuration II, Magnets 1 and 2, Y=0
  • Figure A18-22 Carpenter 49, Mod 1, Configuration I, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-23 Carpenter 49, Mod 1, Configuration II, Magnets 1 and 2, Y=0, graphical form
  • Figure A18-24 Carpenter 49, Mod 1, Configuration I, z = -3/16
  • Figure A18-25 Carpenter 49, Mod 1, Configuration I, z = 0
  • Figure A18-26 Carpenter 49, Mod 1, Configuration I, z = +3/16
  • Figure A18-27 Carpenter 49, Mod 1, Configuration II, y = 0, z = -3/16
  • Figure A18-28 Carpenter 49, Mod 1, Configuration II, y = 5/32, z = 0
  • Figure A18-29 Carpenter 49, Mod 1, Configuration II, y = 0, z = 0
  • Figure A18-30 Carpenter 49, Mod 1, Configuration II, y = -5/32, z = 0
  • Figure A18-31 Carpenter 49, Mod 1, Configuration II, y = 5/32, z = 3/16
  • Figure A18-32 Carpenter 49, Mod 1, Configuration II, y = 0, z = 3/16
  • Figure A18-33 Carpenter 49, Mod 1, Configuration II, y = -5/32, z = -3/16
  • Figure A18-34 Carpenter 49, Mod 1, Configuration II, y = 0, z = 0; screen ~3.8" out
  • Figure A18-35 Carpenter 49, Mod II, Flight Configuration, y = +.1"
  • Figure A18-36 Carpenter 49, Mod II, Flight Configuration, y = 0
  • Figure A18-37 Carpenter 49, Mod II, Flight Configuration, y = -.1"
  • Figure A18-38 Carpenter 49, Mod II, Flight Configuration, y = +.1", graphical form
  • Figure A18-39 Carpenter 49, Mod II, Flight Configuration, y = 0, graphical form
  • Figure A18-40 Carpenter 49, Mod II, Flight Configuration, y = -.1", graphical form
  • Figure A18-41 Deflected Electron Beam Image, Carpenter 49, Mod II, Configuration I, z = 0
  • Figure A18-42 Deflected Electron Beam Image, Carpenter 49, Mod II, Configuration I, z = 5/16
  • Figure A18-43 Magnetic Field Intensity Along Central Axis as a Function of Magnet Pairs
  • Figure A18-44 Magnetic Field Intensity Along Central Axis as a Function of Magnet/Pole-Piece Configuration
  • Figure A18-45 Magnetic Field Intensity Along Central Axis as a Function of Yoke Material and Design
  • Figure A18-46 Location of deflected electron beam image. Comparison of Yoke C49/Mod I, Configuration I & II, target: x=0, y=0, z=-3/16
  • Figure A18-47 Location of deflected electron beam image. Comparison of Yoke C49/Mod I, Configuration I & II, target: x=0, y=0, z=0
  • Figure A18-48 Location of deflected electron beam image. Comparison of Yoke C49/Mod I, Configuration I & II, target: x=0, y=0, z=+3/16
  • Figure A18-49 Location of deflected electron beam image. Comparison of Mod I and II for Yoke C49, Configuration I, target: x=0, y=0, z=0.
  • Figure A18-50 Location of deflected electron beam image. Yoke C49/Mod I, Configuration II. Target screen moved back 0.375 inches.
  • Figure A18-51 Electron trajectories - 80 keV, Yoke C49/Mod I, Configuration II
  • Figure A18-52 Electron trajectories - 145 keV, Yoke C49, ModI, Configuration II
  • Figure A18-53 Solar Polar yoke

 

 

Next: Chapter 1: Purpose of This Document

 

Return to Ulysses HISCALE Data Analysis Handbook Table of Contents


Updated 1/2/19, Cameron Crane

QUICK FACTS

Manufacturer: ESA provided the Ulysses spacecraft, NASA provided the power supply, and various others provided its instruments.

Mission End Date: June 30, 2009

Destination: The inner heliosphere of the sun away from the ecliptic plane

Orbit:  Elliptical orbit transversing the polar regions of the sun outside of the ecliptic plane