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FPI Instrument Manager Art Jacques Finance _ Resources

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FPI Instrument Manager Art Jacques Finance _ Resources Powered By Docstoc
					                             FPI Performance Update
                  IDPU                                                                     FPI Lead Co-Investigator:
                                 FPI DIS
                                                                                           Craig Pollock (673)
                                      FPI DES
FPI DES                  Z
                             Y                                                             FPI Instrument Manager:
FPI DIS                                                                                    Art Jacques
                              X
                                                FPI DIS                                    Finance & Resources:
                                                FPI DES                                    Dwight Norwood (501)
                                                                                           Carmine St. Paul (501)

                                                                                           Systems Engineer:
     FPI DES
        FPI DIS                                                                            Jim Lobell (556)
                                                                                           Al Mariano (556)
                                                                                           Chad Salo (556)

                                                                                           Partners:
                                                                                           Southwest Research Institute
                                                                                           JAXA / ISAS
                                                                                           CESR
                                                                                           MSFC
                                                                                           Meisei Electric, Co.
                                                                                           SPEI
                  DIS                                 DES

                                  NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”                   1
                                 Requirements

 STP-MMS-I60: The Fast Plasma Instrument (FPI) shall have the capability to measure
 3-dimensional electron flux distributions from cold plasma (~10 eV) to 30 keV with an
 energy resolution of 20% and a time resolution better than 30 ms and 3-dimensional ion flux
 distributions from cold plasma (~10 eV) to 30 keV with an energy resolution of 20% and a
 time resolution better than 150 ms.


- PROGRAM LEVEL REQUIREMENTS FOR THE MMS) PROJECT;

- VERSION JUNE 8, 2009 BASELINE FOR KEY DECISION POINT-C (KDP-C)




                      NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   2
         Pre-Launch Calibration

  Calibration Facilities at GSFC and MSFC.
  Backups at MSSL, ISAS, other sites
 • Ground Calibration Testing                                        On-orbit Calibration, Maintenance
Test              Full (1 box)       Std. (3 box)                    Test                       Frequency
Aperture,      32 pixels           4 pixels                          Aperture cal.     Monthly
MCP saturation 8 energies          2 energies                         against s/c
                                                                      potential, waves
                                                                     MCP saturation
Pixel           32 pixels          4 pixels
                                                                     Inter-calibration Each orbit
Geometry        8 energies         2 energies

Energy          8 pixels           4 pixels
                16 energies        2 energies                        UV contamination Each orbit

UV rejection    All pixels         Quick scan
                                                                     HPCA, EPD cross Monthly
HPCA, EPD       32 pixels          --                                cal.
cross cal       8 energies

NB: Ground Cal plan under review; revision likely.
 Parallel path calibration assures sensors meet specifications and are inter-calibrated
                              NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”         3
       DIS ETU Testing




      2 keV N2 + beam  Ch23(Head#1)
NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   4
                       DIS Test Summary - 2
       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               5.0          8.5           8.8    10.3      8.7

CH0    <E>/V (eV/V) @11.25deg.                               4.95        4.91           4.90   4.90     4.90
       <Alpha> (deg.) @11.25deg.                            -19.6        -6.8           -0.8   5.17     17.7
       dE/<E> (%) @11.25deg.                                 9.3         10.3           11.7   12.4     11.9
       dAlpha (deg.) @11.25deg.                              5.7          5.1           4.8     4.1      2.4

       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               5.9          9.0           10.0    9.4      8.0

CH8    <E>/V (eV/V) @11.25deg.                               4.93        4.88           4.90   4.88     4.86
       <Alpha> (deg.) @11.25deg.                            -20.1        -7.4           -1.0    4.7     17.4
       dE/<E> (%) @11.25deg.                                 11.4        10.7           12.0   11.9     11.3
       dAlpha (deg.) @11.25deg.                              6.1          5.4           5.1     4.2      2.1

       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               6.1          9.4           9.8    11.2      9.7

CH15   <E>/V (eV/V) @11.25deg.                               4.90        4.90           4.89   4.88     4.87
       <Alpha> (deg.) @11.25deg.                            -20.0        -6.6           -0.2    5.8     18.7
       dE/<E> (%) @11.25deg.                                 11.7        12.2           11.2   11.8     11.5
       dAlpha (deg.) @11.25deg.                              6.0          5.7           5.5     4.9      2.7

                NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”                            5
                       DIS Test Summary - 3
       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               7.0         10.1           9.8    13.7      9.3
CH16   <E>/V (eV/V) @11.25deg.                               4.93        4.90           4.90   4.89     4.89
       <Alpha> (deg.) @11.25deg.                            -20.0        -6.9           -0.9    5.2     17.8
       dE/<E> (%) @11.25deg.                                 11.2        12.0           11.7   12.7     11.2
       dAlpha (deg.) @11.25deg.                              5.6          5.8           5.2     4.5      2.4

       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               7.4          7.4           8.2     8.8      8.9
CH23   <E>/V (eV/V) @11.25deg.                               4.9         4.89           4.88   4.88     4.87
       <Alpha> (deg.) @11.25deg.                            -19.4        -6.5           -0.4    5.4     18.0
       dE/<E> (%) @11.25deg.                                 11.1        12.3           10.9   11.9     11.6
       dAlpha (deg.) @11.25deg.                              5.8          5.4           4.9     4.1      2.6

       Vup/|Vin| / Vlw/|Vin|                                0.85/0      0.27/0          0/0    0/0.27   0/0.85
       g-factor (e-4 cm^2 sr eV/eV) @11.25deg.               6.2          9.2           8.8    10.6      8.7
CH31   <E>/V (eV/V) @11.25deg.                               4.93        4.88           4.88   4.89     4.86
       <Alpha> (deg.) @11.25deg.                            -19.8        -7.1           -0.8    5.1     17.8
       dE/<E> (%) @11.25deg.                                 10.8        11.8           12.2   11.8     12.1
       dAlpha (deg.) @11.25deg.                              5.8          5.3           4.9     4.1      2.5

                NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”                            6
                     DIS Test Summary - 3


Vup/|Vin| / Vlw/|Vin|                             0.85/0      0.27/0         0/0      0/0.27     0/0.85

g-factor (e-4 cm^2 sr eV/eV) @11.25deg.             6.3         8.9          9.2       10.7        8.9
                                                  +/- 0.8     +/- 0.9      +/- 0.7    +/- 1.7    +/- 0.6
<E>/V (eV/V) @11.25deg.                            4.92        4.89         4.89        4.89       4.89
                                                 +/- 0.02    +/- 0.01     +/- 0.01    +/- 0.01   +/- 0.01
<Alpha> (deg.) @11.25deg.                          -19.8       -6.9         -0.7        5.2       17.9
                                                  +/- 0.3     +/- 0.3      +/- 0.3    +/- 0.4    +/- 0.4
dE/<E> (%) @11.25deg.                              10.9        11.6         11.6       12.1       11.6
                                                  +/- 0.8     +/- 0.8      +/- 0.5    +/- 0.4    +/- 0.3
dAlpha (deg.) @11.25deg.                            5.8         5.5          5.2        4.3        2.5
                                                  +/- 0.2     +/- 0.3      +/- 0.4    +/- 0.3    +/- 0.2




              NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”                         7
DES: Higher Flux, un-Deflected




  NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   8
DES: Lower Flux, un-Deflected




  NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   9
DES: Higher Flux, Deflected




  NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   10
                                DES ETU – Before & After Vibe

Note: 20% dE/E
Anomalous – need

                         dE/E
to work at lower
rates
                      E/qV
                      Vpeak
                      Gap
                       Angle




Note:Variability in
geometry factor
                  G0




owing to variable
noise. Working it.
                                NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   11
   Uncertainties in FPI Measurements


• Statistical fluctuations in Count Rate

• Location of Energy and Angle band passes (geometry and HVPS performance)

• Inherent Energy & Angle Band Passes widths (geometry dominated)

• Inherent Sensitivity (geometry and detection efficiency)




                  NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   12
     Plan to Achieve Required Accuracy
• Statistical uncertainties will be unusually prominent owing to small interval (~200
us for DES; ~1ms for DIS); these will be irreducible;

• Geometric dependencies will not change with time and will be fully calibrated in
laboratories before flight

• Detection efficiencies will change slowly with time and be calibrated in flight
     o absolute cal using occasional inter-instrument calibration
     o relative pixel calibration:
           - like elevations comparing count rates at same spin phases; requires spin-
          period stability in fluxes
           - disparate elevations comparing count rates during isotropic fluxes
           - condition of gyrotropy can provide some inter-elevation cal

• Energy & angle selection will change slowly with time and be calibrated in flight
     o Common energy & angle features provide relative cal
     o Multiple data points reduce absolute uncertainty, asumming independent and
     random evolution of command and HVPS circuits

                     NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   13
NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   14
                                      Summary


• All aspects of DES and DIS performance are in specification

• There exists some concern about the uniformity of DIS sensor performance

• Width of band passes are easy to over-estimate in lab, owing to saturation effects

• In-flight calibration will be crucial to knowing both geometric factor and energy
and angle selection performance as the mission evolves

• FPI team not quite finished chasing system noise & cross-talk issues in ETU.




                     NASA Goddard Space Flight Center • Enabling the “Reality of Tomorrow”   15

				
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