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L.10.4.1 WFC3 Verification
L.10.4.1.1 WFC3 Engineering Verification
L.10.4.1.1.1 WFC3 entry into each of four instrument states WFC3-01
(Boot, Hold, Operate, Observe) shall be
demonstrated. Operations shall be
commanded via stored commands transmitted
over the Supervisory Bus.
L.10.4.1.1.2 WFC3 entry into each of the defined detector WFC3-01
states shall be demonstrated. Operations shall
be commanded via stored commands
transmitted over the Supervisory Bus.
L.10.4.1.1.3 WFC3 command and engineering data WFC3-01
interface via the RIU and science data
transmission via the Science Data Formatter
(SDF) shall be verified by monitoring of normal
configuration and science activities.
L.10.4.1.1.4 Onboard memory shall be checked by WFC3-02
performing a full dump of the CS (control
section) EEPROM, PROM, and EXEC RAM,
and verify a match with the ground image.
L.10.4.1.1.5 The ability to read and write data from and to WFC3-03
the science data buffer shall be demonstrated.
L.10.4.1.1.6 The performance of the Channel Select WFC3-08,
Mechanism, M1 and IM2 Alignment and Focus WFC3-09,
Corrector Mechanisms, UVIS Selectable WFC3-10,
Optical Filter Assembly, IR Filter Wheel, and WFC3-14,
UVIS CCD shutter shall be verified. WFC3-19,
WFC3-20
L.10.4.1.1.7 The functionality of the WFC3 Tungsten and WFC3-09,
Deuterium calibration lamps shall be verified. WFC3-10,
Operation of the deuterium lamp shall be WFC3-15,
deferred for an initial outgassing period WFC3-19,
following release of the observatory, as defined WFC3-20
in the CARD 3.4.13.11.
L.10.4.1.1.8 Functionality of the WFC3 UVIS CCD detector WFC3-06
shall be demonstrated. This shall include the
proper accumulation of signal over a specified
time interval and data readout, readout of
subarrays, and on-chip binning.
L.10.4.1.1.9 Functionality of the WFC3 IR detector shall be WFC3-07
demonstrated. This shall include the proper
accumulation of signal over a specified time
interval and multiaccum data readout, readout
of subarrays, and characterization of the
reference pixels.
L.10.4.1.1.10 The ability of the TECs to cool and stably WFC3-04,
control the detectors shall be tested at a small WFC3-05,
number of temperature set points, in order to WFC3-16,
determine a cold stable operating point. The WFC3-17
goal is to demonstrate that this point be at least
as cold as –83C for the UVIS CCDs and 145K
for the IR detector. WFC3 detectors cannot be
cooled before 21 days in vacuum (CARD
3.4.13.15).
L.10.4.1.1.11 The ability to perform a CCD anneal shall be WFC3-18
demonstrated.
L.10.4.1.1.12 WFC3 operations shall be managed to WFC3-13
minimize risk of contamination of its optical
surfaces by materials outgassed either
internally or from other units installed during the
SM as well as from the payload bay
environment during servicing (CARD 3.4.13.15,
3.4.13.16, 3.4.13.17) . A contamination
monitoring program shall be initiated as early
as possible after the SM.
L.10.4.1.2 WFC3 Optical Alignment Requirements
L.10.4.1.2.1 The encircled energy and image diameter shall WFC3-11,
be measured over a grid of focus and tilt WFC3-12,
positions for both M1 and IM2 correctors. WFC3-21,
These measurements shall be used to set the WFC3-22
nominal corrector positions.
L.10.4.1.2.2 The image quality at the detectors over the full WFC3-11,
field shall be measured via broad and narrow WFC3-12,
band imaging of stars. The requirement for WFC3-21,
encircled energy in the UVIS channel field WFC3-22,
center is 75% within a diameter of 0.25 WFC3-23,
arcseconds, through the F631N filter. The WFC3-24
requirement for encircled energy in the IR
channel field center is 75% within a diameter of
0.60 arcseconds, for a star observed through
the F164N.
L.10.4.1.2.3 The pointing stability of the OTA-WFC3 WFC3-27,
combination shall be measured over at least WFC3-28
three orbits including hot and cold spacecraft
attitudes. The purpose of these measurements
is to confirm that the typical thermal
environment after SM4 does not cause
unacceptable image drifts.
L.10.4.1.2.4 The WFC3 Point Spread Function (PSF) shall WFC3-25,
be measured over a large dynamic range in WFC3-26
order to study PSF wings and image ghosts.
L.10.4.1.3 WFC3 Calibration Requirements
L.10.4.1.3.1 The plate scale, orientation and geometric WFC3-31,
distortion shall be measured for each of the WFC3-32
WFC3 channels by imaging an astrometric
field.
L.10.4.1.3.2 The absolute FGS/WFC3 alignment shall be WFC3-29,
determined. WFC3-30
L.10.4.1.3.3 Dark rate, read noise and CTE shall be WFC3-33
measured for the CCD detector. The hot pixel
creation rate shall be assessed and the efficacy
of the hot annealing cycle shall be
demonstrated. The stability of these
parameters over a 30 day baseline shall be
determined.
L.10.4.1.3.4 Dark rate, background level, and read noise WFC3-34
shall be measured for the IR detector. IR bad
pixels shall be characterized. The stability of
these parameters over a 30-day baseline shall
be determined.
L.10.4.1.3.5 The behavior of both channels during SAA WFC3-35,
passages shall be characterized. The SAA WFC3-36
afterimage shall be measured for the IR
detector.
L.10.4.1.3.6 Instrument sensitivity vs. wavelength shall be WFC3-13,
measured for a subset of WFC3 spectral WFC3-37,
elements. Sensitivity measurements shall be WFC3-38
performed using astronomical standard stars.
The photometric stability shall be determined
over several orbits. As part of this process, UV
sensitivity measurements shall be obtained as
early as possible, to enable early trending of
UV sensitivity.
L.10.4.1.3.7 The flat field uniformity per pixel and cosmetic WFC3-19,
defect fraction shall be measured for both WFC3-20,
WFC3 detectors. The ability to determine the WFC3-39,
residual response variation using the WFC3 WFC3-40
internal calibration sources shall be
demonstrated. The difference between sky
flats and internal flats and temporal stability of
the flat field correction shall be assessed.
L.10.4.2 COS Verification
L.10.4.2.1 COS Engineering Requirements
L.10.4.2.1.1 COS entry into each of four instrument states COS-01
(Boot, Hold, Operate, Observe) shall be
demonstrated. Operations shall be
commanded via RIU (Remote Interface Unit)
commands transmitted over the Supervisory
L.10.4.2.1.2 COS entry into each of the defined detector COS-01
states shall be demonstrated. Operations shall COS-04
be commanded via RIU commands transmitted COS-23
over the Supervisory Bus. COS-29
COS-30
COS-34
L.10.4.2.1.3 Science data transmission via the Science COS-03
Data Formatter (SDF), shall be verified by
monitoring of normal configuration and science
L.10.4.2.1.4 The ability to load and dump on-board memory COS-02
shall be demonstrated.
L.10.4.2.1.5 The ability to read and write data from and to COS-03
the science data buffer shall be demonstrated.
The science data buffer shall also be checked
for bit flips during SAA passage.
L.10.4.2.1.6 The procedure used for initial turn-on and COS-04
recovery after anomalous shutdown of NUV
MAMA detector shall be tested.
L.10.4.2.1.7 The procedure used for initial turn-on and COS-23
recovery after anomalous shutdown of FUV
XDL detector shall be tested.
L.10.4.2.1.8 Functionality and operations of the two COS COS-05
detectors shall be demonstrated. This shall COS-06
include; a) the proper accumulation of signal COS-09
over a specified time interval in ACCUM and COS-11
TTAG readout mode, b) readout of subarrays, COS-14
c) standard auto-wavelength calibration for COS-16
ACCUM mode with the PSA and for TTAG and COS-24
ACCUM mode with the Bright Object Aperature COS-25
(BOA), d) TAG-FLAG operational mode COS-26
(standard wavelength calibration for TTAG COS-28
mode with the PSA), e) on-board Doppler COS-29
correction in ACCUM mode.
L.10.4.2.1.9 The functionality of the FUV detector shall be deleted
tested with and without the QE enhancement
grid turned on.
L.10.4.2.1.10 The performance of the external shutter, routine
Aperture Mechanism (ApM), Optics Select
Mechanisms OSM1 and OMS2, and FUV
detector door shall be verified either by
execution of engineering tests or as part of
normal SMOV operations.
L.10.4.2.1.11 The functionality of the COS Pt-Ne and D2 routine
calibration lamps shall be verified either by
execution of engineering tests or as part of
normal SMOV operations.
L.10.4.2.1.12 Verify that there is no light leakage from COS COS-37
Calibration Lamps which affects other SIs
observing in parallel.
L.10.4.2.2 COS Contamination Requirements
L.10.4.2.2.1 COS operations shall be managed to minimize COS-19
the risk of contamination of its optical surfaces COS-34
by outgassing material. The COS external
shutter shall be used to provide protection
against illumination by the bright earth. A
contamination monitor program shall be
initiated as soon as possible after the servicing
mission (COS CARD item 3.4.12.20).
L.10.4.2.2.2 Upon release the COS instrument shall COS-04
undergo a period of depressurization and COS-06
decontamination; a) the FUV detector door COS-22
shall not be opened until the COS internal COS-23
pressure is less than 100 micro-Torr for 12
consecutive hours, b) the NUV MAMA detector
HV shall not be turned on until the internal
pressure is less than 20 micro-Torr for 12
consecutive hours, c) the FUV XDL detector
HV shall not be turned on until the internal
pressure is less than 10 micro-Torr for 12
consecutive hours, d) the D2 and Pt-Ne lamps
shall not be operated until the internal pressure
is less than 10 micro-Torr for 12 consecutive
hours. (COS CARD items 2.4.12.3, 2.4.12.4,
2.4.12.7, 2.4.12.8, 3.14.12.14)
L.10.4.2.2.3 The HV of the FUV XDL detector and the NUV COS-22
MAMA detector shall be off when the FUV
detector door opens in case of release of gases
during the opening of the door.
L.10.4.2.3 COS Science Verification and Calibration
L.10.4.2.3.1 Internal NUV calibrations shall be conducted COS-05
and measurements of the post-launch COS-07
alignment of the optics shall be obtained. COS-10
These include; a) a detector dark image, b) an
internal wavelength calibration spectrum using
each NUV grating at each central wavelength
setting, c) a TA1 image of the wavelength
calibration lamp, d) intensity of each lamp in a
single mode.
L.10.4.2.3.2 The relationship between the HST coordinate COS-08
system and the COS primary science aperture
(PSA) shall be measured. The NUV channel in
the TA1 mode shall be used to locate the PSA
in the HST V2, V3 coordinates.
L.10.4.2.3.3 The locations of the spectra for each NUV COS-09
mode shall be measured.
L.10.4.2.3.4 The NUV channel shall be focused. Conduct a COS-09
focus scan of each of the NUV gratings at one
central wavelength setting and of the TA1
mirror while observing an astronomical target.
L.10.4.2.3.5 The target acquisition algorithms for NUV
operations shall be tested and verified.
L.10.4.2.3.5.1 NUV undispersed light target acquisition in COS-11
ACQ and ACQ/IMAGE mode shall be tested.
L.10.4.2.2.5.2 NUB dispersed light target acquisition in ACQ, COS-12
ACQ/PEAKD and ACQ/PEAKXD mode shall be
tested.
L.10.4.2.3.6 The imaging performance of the NUV channel
shall be calibrated.
L.10.4.2.3.6.1 The PSF in NUV imaging (TA1) mode shall be COS-13
measured.
L.10.4.2.3.6.2 The place scale of the NUV detector in imaging COS-13
(TA1) mode shall be measured.
L.10.4.2.3.6.3 The throughput of the NUV imaging (TA1) COS-13
mode shall be tested both in mirror A and
mirror B configurations.
L.10.4.2.3.7 The spectrographic performance of the NUV
channel shall be calibrated.
L.10.4.2.3.7.1 The zero point offsets in the dispersion COS-14
relations for the NUV spectroscopic modes for COS-15
each central wavelength setting shall be
measured.
L.10.4.2.3.7.2 The spectral resolution of the NUV COS-16
spectroscopic modes shall be measured. COS-17
L.10.4.2.3.7.3 The spetial resolution of the NUV spectroscopic COS-17
modes shall be measured.
L.10.4.2.3.7.4 The flat-field response of the NUV detector COS-18
shall be measured.
L.10.4.2.3.7.5 The sensitivity of each NUV grating for each COS-19
central wavelength setting shall be measured.
L.10.4.2.3.7.6 The stability of a single mode of the NUV COS-20
channel over several orbits shall be
characterized to determine if there are
signatures of structural or thermal distortions in
the data.
L.10.4.2.3.7.7 The acquisition of spectra having S/N>30 using COS-21
normal data acquisition and reduction
techniques shall be demonstrated for each
NUV mode. Spectra having S/N>100 for a
single NUV medium resolution mode shall be
demonstrated.
L.10.4.2.3.8 Internal FUV calibrations shall be conducted COS-24
and measurements of the post-launch COS-25
alignment of the optics shall be obtained. COS-27
These include; a) a detector dark image, b) an
internal wavelength calibration spectrum using
each FUV grating at each central wavelength
setting, c) intensity of each lamp in a single
mode.
L.10.4.2.3.9 The locations of the spectra for each FUV COS-26
mode shall be measured. This is done by
observing an astronomical target and acquiring
a spectrum using G130M, G160M, and G140L
L.10.4.2.3.10 The FUV channel shall be focused. Conduct a COS-26
focus scan of each of the FUV gratings at one
central wavelength setting while observing an
astronomical target.
L.10.4.2.3.11 The target acquisition algorithms for FUV
operations shall be tested and verified.
L.10.4.2.3.11.1 FUV dispersed light target acquisition in COS-28
ACQ, ACQ/PEAKD and ACQ/PEAKXD mode
shall be tested.
L.10.4.2.3.12 The spectrographic performance of the FUV
channel shall be calibrated.
L.10.4.2.3.12.1 The zero point offsets in the dispersion COS-29
relations for the FUV spectroscopic modes for COS-30
each central wavelength setting shall be
measured.
L.10.4.2.3.12.2 The spectral resolution of the FUV COS-31
spectroscopic modes shall be measured. COS-32
L.10.4.2.3.12.3 The spatial resolution of the FUV spectroscopic COS-32
modes shall be measured.
L.10.4.2.3.12.4 The flat-field response of the FUV detector COS-33
shall be measured.
L.10.4.2.3.12.5 The sensitivity of each FUV grating for each COS-34
central wavelength setting shall be measured.
L.10.4.2.3.12.6 The stability of a single mode of the FUV COS-35
channel over several orbits shall be
characterized to determine if there are
signatures of structural or thermal distortions in
the data.
L.10.4.2.3.12.7 The acquisition of spectra having S/N>30 using COS-36
normal data acquisition and reduction
techniques shall be demonstrated for each
FUV mode. Spectra having S/N>100 for a
single FUV medium resolution mode shall be
demonstrated.
L.10.4.2.3.13 The position and throughput of the BOA, and COS-11
spectral resolution of the data acquired through COS-13
this aperture shall be measured. This is done COS-16
by observing an astronomical target in imaging COS-17
mode and acquiring a spectrum in each NUV COS-31
and FUV grating at a single central wavelength COS-32
setting.
L.10.4.3 ACS Verification
L.10.4.3.1 ACS Engineering Requirements
L.10.4.3.1.1 A hot pixel annealing procedure shall be ACS-04
executed just before CCD activation, and every
four weeks thereafter, thus resuming the
standard cadence in force before SM4.
L.10.4.3.1.2 The ability of the TEC to cool and stably control ACS-05
the CCD at their nominal operating
temperatures shall be tested and verified
through the engineering telemetry data during
the course of normal operations. Failure to
reach the expected temperature will trigger an
existing contingency program (CCD
temperature set point determination) that was
used successfully in SM3B.
L.10.4.3.1.3 Detector Characteristics. After reaching the ACS-06,
appropriate operating temperature, a mini- ACS-07,
functional test shall be executed for all ACS ACS-08,
detectors to characterize their performances in ACS-10
the new thermal environment. However, the
high voltage for the SBC detector shall not be
activated until at least four days after relase
and not until the pressure in the aft shroud has
been below 5e-6 Torr for at least 24 hours. The
minifunctional test shall consist of an enriched
version of the nominal daily/monthly monitoring
program and is to include bias, dark and flat
field frames. Calibration observations obtained
in the course of normal operations preceding
SM4 provide the baseline against which these
data shall be compared.
L.10.4.3.1.4 Following the successful activation of the CCD, ACS-09,
the standard UV monitoring program shall ACS-20
resume as soon as possible, limited initially to
the HRC. The SBC monitoring program will
need a choice of appropriate BEA targets for
which pre-SM4 observations are available.
L.10.4.3.2 ACS Target Acquisition Requirements
L.10.4.3.2.1 The location of a reference aperture shall be ACS-12
determined for all three ACS channels with
respect to the FGS reference frame to within an
accuracy of 1 arc second in V2-V3 coordinates
and 10 arc minute in aperture rotation angle by
observing a well-observed dense stellar field.
The same observations will be used to
investigate any possible changes in geometric
distortions.
L.10.4.3.2.2 The location of the coronographic spots shall ACS-15
be measured with one set of observations.
L.10.4.3.3 ACS Optical Alignment Requirements
L.10.4.3.3.1 The camera mode image quality at the ACS-16,
detectors over the full field shall be measured ACS-17
via broad and narrow band imaging of a sparse
L.10.4.3.3.2 A decrease of the encircled energy (within a ACS-13,
0.25 arc second diameter) by more than 3 ACS-14
sigma (5%) will trigger an existing contingency
program, successfully used in SM3B (ACS fine
corrector alignment), whereby the encircled
energy and image diameter are measured over
a grid of focus and tilt positions for both IM1
and M1 correctors. These measurements shall
be used to set the nominal corrector positions.
L.10.4.3.3.3 The ACS Point Spread Function (PSF) in ACS-18
coronographic mode shall be measured.
L.10.4.3.4 ACS Calibration Requirements
L.10.4.3.4.2 Detector Sensitivities and instrument ACS-11,
configurations. Observations of reference ACS-20
stellar fields (e.g. 47 Tuc and NGC188 for the
CCD, NGC6681 for the SBC) shall be obtained
for a subset of the ACS imaging modes and
filters. Through comparison with the existing
pre-SM4 data, these observations shall be
used to reveal and measure, for each ACS
channel, variations in: a) the detectors plate
scale, orientation and geometric distortion, b)
the relative location of each aperature with
respect to the FGS reference frame, c) the
instrumental relative and absolute sensitivity as
a function of wavelength, d) the uniformty of the
L.10.4.3.4.3 Variations in the ACS detectors' sensitivity to a ACS-11,
pixel-to-pixel scale and cosmetic defects shall ACS-20
be measured for all three channels through
observations with the internal calibration laps
L.10.4.4 NICMOS/NCS Verification
L.10.4.4.1 NICMOS/NCS Engineering Activation
Requirements
L.10.4.4.1.1 The ability to command NICMOS via the RIU, NIC-02
science data transmission via the SDF, and the
ability of NICMOS to transition between primary
operational states (HOLD, BOOT, SAA-OPER,
OPERATE and OBSERVE) shall be verified.
L.10.4.4.1.2 Operation of the NICMOS mechanisms (PAM, NIC-04,
FOM, and filter wheels) shall be tested. PAM NIC-06
motion over the range needed to assure focus
in all three NICMOS cameras (best achievable
focus for NIC3). The ability to reposition the
field offset mirror (FOM) over the range needed
to remove vignetting in NIC3 shall be
demonstrated. Filter wheel motion will be
verified for each filter position.
L.10.4.4.1.3 Verify the basic operating characteristics of the NIC-03
flight detectors through a series of multiple non-
destructive readouts as a function of bias
L.10.4.4.2 voltage.
NICMOS/NCS Target Acquisition
Requirements
L.10.4.4.2.1 The location of each NICMOS camera aperture NIC-07
shall be determined with respect to the FGS
reference frames to an accuracy of +/-2
arcseconds in V2-V3 coordinates and 7
arcminutes in aperture rotation angle for
Camera 2 and 1 degree for cameras 1 and 3.
L.10.4.4.2.2 The mode-2 coronagraphic target acquisition NIC-10
shall be characterized and measured with a
precision of ~1/10 of a pixel. Acquisition of the
target and the coronagraphic hole should be
shown to be repeatable, within the precision
given, using the on-board flight software.
L.10.4.4.3 NICMOS/NCS Optical Requirements
L.10.4.4.3.1 The optical plate scales at each of the detector NIC-08
focal planes shall be measured, with a
precision of better than 0.1% in each camera.
L.10.4.4.3.2 PAM focus setting should be measured to NIC-05
establish the best focus for each camer. The
encircled energy within 100 mas (200 mas for
camera 3) radius of an unresolved point source
shall be measured. In case the total wavefront
error exceeds lambda/14 for NIC1 and NIC2 at
1.1 and 1.6 microns, respectively, a fine optical
alignment program will be implemented.
L.10.4.4.3.3 Determine the optimum PAM position that NIC-11
maximizes the coronagraphic
image/background contrast ratio.
L.10.4.4.4 NICMOS/NCS Calibration Requirements
L.10.4.4.4.1 The performance of the NICMOS coronagraph NIC-12
shall be characterized. The goal is to provide
the best achievable target/background contrast
L.10.4.4.4.2 NICMOS geometric stability will be NIC-09
characterized by measuring the lateral motion
of the image in the Camera 2 focal plane.
L.10.4.4.4.3 Detector read noise and dark current shall be NIC-14
measured. The minimum acceptable levels of
performance are a read noise of <=40
electrons and a dark current of <=2.5
electrons/second.
L.10.4.4.4.4 HST+NICMOS thermal emission will be NIC-13
characterized in a subset of spectral elements
over the duration of SMOV.
L.10.4.4.5 NICMOS Cooling System (NCS) Engineering
Verification Requirements.
L.10.4.4.5.1 Configure the NCS to re-cool NICMOS NIC-01
detectors. The goal during SMOV is to verify
the capability to maintain the weighted average
of the neon inlet and outlet temperatures at a
desired setpoint in the range 72-73 K.
L.10.4.4.5.2 Verify the capability of the NCS to achieve a routine
NICMOS Cold Well temperature (as measured
by the 1-1 temperature sensor) of 77+/-2
degrees Kelvin and maintain it within 0.1K.
L.10.4.4.5.3 The NICMOS cooldown profile and the NIC-01
NICMOS dewar temperature stability shall be
characterized.
L.10.4.4.6 NICMOS/NCS Calibration and Performance
Requirements
L.10.4.4.6.1 The temperature of each NICMOS detector, NIC-14
along with its range of variation and the
timescale of variation, shall be determined.
Detector temperature stability shall be
characterized over periods of 60 sec, 2000 sec,
24 hours and 30 days.
L.10.4.5 STIS Verification Requirements.
L.10.4.5.1 STIS Engineering Requirements
L.10.4.5.1.1 STIS entry into each of four instrument states STIS-01
(Boot, Hold, Operate, Observe) shall be
demonstrated.
L.10.4.5.1.2 STIS entry into each of the defined detector STIS-01
states shall be demonstrated.
L.10.4.5.1.3 STIS command and engineering data interface STIS-03
via the RIU and science data transmission via
the Science Data Formatter (SDF) shall be
verified by monitoring of normal configuration
and science activities.
L.10.4.5.1.4 Onboard memory will be checked by STIS-02
performing dumps of EEPROM, PROM, EDAC
RAM and Buffer RAM.
L.10.4.5.1.5 Conduct a test of the ability to write to and read STIS-02
from the CS Buffer RAM.
L.10.4.5.1.6 Verify the proper functioning of all STIS STIS-04
mechanisms needed for routine operations (the
three MSM wheels, the aperture wheel, CIM,
echelle blockers, CCD shutter, aperture door, &
mode isolation shutter) over the full ranges of
motion needed for normal operations.
Verification of the corrector alignment
mechanisms will be done, if necessary, as part
of any needed alignment or focus adjustments,
but movement of corrector mechanisms should
otherwise be minimized.
L.10.4.5.1.7 Check the functioning of the calibrations lamps STIS-08
used for routine science and SMOV operations
(LINE, Tungsten, HITM1, & HITM2). If one or
more of these lamps either shows significantly
degraded behavior or fails to function, make
those changes which are necessary to support
science operations; these may include changes
to the ground system and/or on-board tables to
allow substitution of one of the operable lamps
for the critical functions of a failed one.
Verification of the Krypton and Deuterium
lamps may be deferred until after SMOV.
L.10.4.5.1.8 The CCD shall be annealed to ameliorate hot STIS-05
pixels that have accumulated.
L.10.4.5.1.9 During the course of routine operations routine
throughout SMOV, the temperature variations
of each detector will be monitored and
compared to previous side-2 values. The ability
of the CCD TEC to cool that detector to the
required operating temperature range will be
evaluated.
L.10.4.5.1.10 Perform a mini-functional test of the STIS CCD. STIS-06
L.10.4.5.1.11 Verify the proper functioning of the MAMA STIS-17
detectors by following procedures similar to STIS-18
those defined for MAMA anomalous recovery
(STIS ISR 98-03). A MAMA detector should not
be otherwise used prior to completing this
functional test. The high voltage for the STIS
MAMA detectors will not be activated until at
least four days after release.
L.10.4.5.1.12 The STIS Deuterium and Krypton lamps will not normal
be operated until 3 weeks after release, as
required by a Constraints and Restrictions
Document.
L.10.4.5.2 STIS Target Acquisition Requirements
L.10.4.5.2.1 The location of a reference STIS camera STIS-09
aperture shall be determined with respect to the
FGS reference frames to an accuracy of 1 arc
second in V2-V3 coordinates and 10 arc
minutes in aperture rotation angle.
L.10.4.5.2.2 The ability to acquire and properly center STIS-09,
targets with standard ACQs and the ability to STIS-11,
center targets in small apertures with STIS-13,
ACQ/PEAK exposures will be demonstrated for STIS-15
both standard and E1 aperture positions.
L.10.4.5.3 STIS Optical Alignment Requirements
L.10.4.5.3.1 An aperture throughput test using an external STIS-09
target shall be used to assess STIS focus. The
slit plane encircled energy vs. wavelength shall
also be measured using this external target. If
throughput is down by more than 3 sigma (7%),
relative to the expected mean after correction
for expected secular sensitivity changes,
further tests and perhaps a STIS corrector
alignment and/or focus adjustment shall be
done. This test is dependent on the setting of
the HST secondary mirror position, which must
have been first set to nominal focus.
L.10.4.5.3.2 The positioning of the STIS aperture wheel STIS-08
should be checked for a representative subset
of STIS apertures, and compared to previous
side-2 measurements. If operationally
significant discrepancies are found in the
relative aperture positions, a full
remeasurement of all aperture locations will be
done, and appropriate updates made to ground
and on-board calibration tables.
L.10.4.5.3.3 For each optical element in the MSM, (except STIS-11
for MAMA imaging modes), the location of a
lamp spectrum or slit image on the detector
appropriate for that optical element shall be
compared to previous side-2 values.
Operationally significant shifts shall be
corrected by updating on-board mechanism
calibration tables. Only one MSM position of
each optical element need be tested. Checks of
MAMA imaging mode alignments may be
deferred until after SMOV.
L.10.4.5.3.4 The spectroscopic image quality and cross STIS-13
dispersion PSF at each detector will be
measured as a function of position and
wavelength using an external point source
target. This test is dependent on the settings of
the HST secondary mirror position and of the
STIS corrector mechanism, which must have
been first set to their nominal values.
L.10.4.5.3.5 To measure image drifts in the typical post- STIS-11
SM4 thermal environment, the pointing and
PSF stability of the OTA-STIS CCD
combination when observing an external target
shall be monitored over a single orbit
immediately following an attitude change that is
expected to produce a significant thermal
change in STIS.
L.10.4.5.4 STIS Calibration Requirements
L.10.4.5.4.1 The dark rate for each detector shall be STIS-19
measured at normal operating temperatures. STIS-20
For the CCD, bias and read-noise
measurements will also be made. Sufficient
dark and bias measurements will be done to
allow proper calibration of other STIS SMOV
and ERO data. Sufficient NUV MAMA dark
measurements will be taken to ensure that the
phosphorescent window glow has declined to a
level that will allow routine observations.
L.10.4.6 Early Release Observations (ERO)
L.10.4.6.1 SMOV activities shall include early release ERO-01
observations with at least the COS, WFC3,
STIS, and if restored, ACS science
instruments. The resulting science data
products shall be released into the public
doman to demonstrate the improved/restored
HST capabilities.
L.10.4.7 OTA/FGS Verification Requirements
L.10.4.7.1 OTA/FGS Cross-SI & Observatory Focus
L.10.4.7.1.1 Post-HST-release focus state shall be Waived
determined with ACS/HRC early in SMOV,
during the first month of ACS ops. Extant HRC
science requirement on focus is ~ 5 mic of
Secondary Mirror motion (including breathing
effects). This requirement has been waived.
L.10.4.7.2 OTS/FGS Cross-SI Positional Alignment
L.10.4.7.2.1 Confirm ACS, NIC, & STIS pre-SM4 V2,V3 OTA-02
locations to within 2 arcsec & orientations to 0.2
deg of last pre-SM4 determination with
contingency. Note this requirement of SI to
FGS alignment from the OTA point of view is
less stringent than the 1 to 2 arcsec, & 0.1 to
0.17 deg given by ACS, NIC, & STIS in their
SMOV requirements (L.10.4.3.2, L.10.4.4.2,
and L.10.4.5.2).
L.10.4.7.2.2 Perform and confirm FGS-FGS alignment. L.10.4.7.3.3
L.10.4.7.3 FGS Commissioning/Recommissioning
L.10.4.7.3.1 Verify Guide Star Acquisition with FGS1&3. OTA-03
Verify that FGS1&3 remain able to acquire
guide stars and track them in finelock.
L.10.4.7.3.2 Optimize FGS2R2 S-curve. FGS2R2 OTA-04
interferometric performance across the FGS
FOV will be optimized for operations (i.e. the
guide function) via adjustment of the articulated
mirror assembly (AMA).
L.10.4.7.3.3 Establish FGS-FGS alignment for all three OTA-05
FGSs.
L.10.4.7.3.4 Calibrate Distortion & Plate Scale for FGS2R2 OTA-06
for operational (guiding) purposes.
L.10.4.7.3.5 Test FGS2R2 Guide Star Acquisition OTA-07
Capability. Verify that the new FGS can acquire
and track bright and faint guide stars with
operationally acceptable performance.
L.10.4.7.3.6 Characterize FGS1r & FGS3 Baseline Pre- OTA-08
SM4. Measure the S-curves at FOV center, the
geometric distortion across the FOV, and plate
scale for FGS1&3 approximately 1 month prior
to SM4 to establish a pre-SM4 baseline
characterization.
L.10.4.7.3.7 Re-commission FGS1r and FGS3 (Ops and OTA-09
Science). Verify the stability of the S-Curve and
the validity of the geometric distortion and plate
scale calibration of FGS1r and FGS 3 after
SM4 by comparison to pre-SM4 observations.
L.10.4.7.3.8 Check Near Term Stability of FGS2R2. At 2 & 4 OTA-04,
months after FGS2R2 commissioning, monitor OTA-06
changes to the S-curve amplitude and
morphology in order to verify the validity of the
values assigned to the guide star acquisition
and tracking parameters. This test will also
verify that the geometric distortion and plate
scale calibration established as part of
FGS2R2’s commissioning remain valid.
L.10.4.7.3.9 Calibrate FGS2R2 PMT. Data from the Mini- OTA-10
OFAD (L.10.4.7.3.4) will be analyzed to obtain
the counts versus magnitude calibration for
FGS2R2.
L.10.4.7.3.10 Map FGS2R2 Obscuration Zone (OCS). A OTA-11
subset of the data collection from the FGS2R2
S-curve Optimization (L10.4.7.3.2) will be
analyzed to determine the OCS Obscuration
Zone dimensions.
L.10.4.7.3.11 Calibrate FGS2R2 PMT Dark Count. Determine OTA-12
the average dark rate for each PMT (internal,
performed during SM4).
L.10.4.8 PCS Verification
L.10.4.8.1 Following release, the HST Pointing Control PCS-01,
System will be returned to normal operations PCS-02,
for SMOV with four gyros in the active control PCS-03,
loop, (no shadow mode). A fine attitude PCS-04,
reference will be uplinked to the spacecraft and CP-85,
the spacecraft will be maneuvered to point to CP-153,
the BEA attitude. The gyro biases will be CP-154
determined and maintained to within 0.014 arc-
seconds per second to allow successful guide
star acquisition at the transition to the Science
SMS.
L.10.4.8.2 If any gyros are changed out, the gyro to FHST PCS-04,
calibration shall be updated to an accuracy that PCS-06
reduces the attitude error following a vehicle
maneuver to one arc-second per degree of
slew or less. This calibration will be performed
immediately after the end of the BEA period.
Until then, history has shown slew miss-
distances of about six arc-seconds per degree
of slew.
L.10.4.8.3 The PCS shall acquire guide stars in fine lock. PCS-07,
SMS
L.10.4.8.4 Once guide star acquisitions have begun, 2- SMS
FGS acquisitions will be scheduled such that
the HST486 on-board gyro bias update
algorithm will maintain the gyro drift rate bias to
within 0.005 arc-seconds per second.
L.10.4.8.5 The vehicle jitter during periods of gyro hold routine
shall be measured.
L.10.4.8.6 Perform a Vehicle Disturbance Test (VDT) to PCS-08
characterize HST line-of-sight jitter, structural
dynamic responses, and disturbance sources.
The VDT is a passive test (not a forced
response test) using a low-bandwidth attitude
control law during gyro-hold with the rate gyros
in low mode. Obtain gyro-measured
disturbance time responses due to SCM, SA-3,
HGAs, RWAs, SSM thermal gradients, and
COS and WFC3 mechanism articulation. The
VDT shall consist of three separate tests that
need not occur consecutively. The overall
duration of the VDT is at least 12 orbits of
spacecraft time including (1) at least 2 orbits at
+V3 sunpoint while performing COS and WFC3
filter wheel articulation simulating routine flight
operations, (2) at least 5 orbits at +V3 sunpoint
after achieving thermal equilibrium (at least 36-
hours at +V3 sunpoint), and (3) at least 5 orbits
at –V1 sunpoint.
L.10.4.8.7 All gyros will be left in a powered on state SMS
through the gyro to FHST alignment calibration,
if it is to be performed. Following the
completion of the gyro to FHST alignment
calibration, the two gyros not in the active
control loop will be configured off. Following
the gyro to FHST calibration, one of the four
gyros will be removed from the control loop and
powered off.
L.10.4.8.8 The time allowed for OBAD maneuver will be SMS
managed to aid in attitude maintenance until
the slew miss-distances and gyro biases are
reduced to a sufficient level to permit
successful FGS acquisitions. The time will be
increased from 66 seconds for a 300 arc-
second maneuver to 105 seconds for a 1200
arc-second maneuver if large attitude errors
are anticipated prior to FGS acquisitions.
L.10.4.9 DMS*
L.10.4.10 I&C*
L.10.4.11 SIC&DH*
L.10.4.12 S&M*
L.10.4.13 TCS Verification
L.10.4.13.1 Verify predicted temperature changes due to TCS-01
NOBL installation on SSM Bays 5, 7 and 8. Bay
7 components are predicted to drop 3-4°C with
the installation of NOBLs. Bay 8 components
are predicted to drop 2°C with the installation of
NOBLs. Bay 5 components are predicted to
drop 8-10°C (TBD) with the installation of
NOBLs and removal of external MLI.
L.10.4.13.2 Verify predicted temperature changes on STIS deleted
MAMA components due to STIS Cooling
System installation.
L.10.4.14 EPS
L.10.4.14.1 Characterize the Replacement Battery EPS-01
Performance
L.10.4.14.2 Characterize Science Instrument and NCS EPS-02
Electrical Loads
L.10.4.15 ASCS* (deleted)
Requirement#Requirement Definition Spc Activity# Activity Execution
Name Time
L.10.4.7.3.12
FHST/FGS alignment contingency:
This activity provides data to restablish
the FHST/FGS alignment. The FG1
and FGS2 will be mapped in turn, while
the 3 FHTSs are concurrently being
mapped (2 at a time).
