CCR NUMBER: 4834
CRITICALITY: ROUTINE
DUE:4/27/01
DISTRIBUTION SHEET
HST LEVEL IIIA CCB MEMBERS
X
X
X
X
X
E.
P.
K.
D.
J.
X
X
X
INFO: only (Level IIIA or II)
D. Scheve/440
X M. Weiss/440
K. Kalinowski/440
X W. Gallagher/QSS/442
D. Leckrone/600/440
C. Coltharp/740/442
X
X
X
X
X
AD
B.
R.
K.
B.
D.
HOC:
Bruce/441
Dedalis/302/442
Hartnett/586/441
Kirkham/TRW/441
Knapp/581/441
E.
S.
B.
T.
Cheng/685
Cover/214.1
Fafaul/442
Griffin/442
X
X
X
Beyer/441
Burch/441
Carpenter/681
Douds/441
Gainsborough/441
X
X
X
X
X
X
X
X
X
X
3A
HOC:
Barasch/561/442
Baugh/568/442
Brinker/561/442
Broderick/563/442
Butler/QSS/442
Chamberlin/730/442
Coltharp/565/442
Dedalis/302/442
Fineberg/730/442
S.
L.
D.
B.
J.
Jeletic/441
Manfra/441
McGrath/214
Ruitberg/441
Sparacino/441
Leskiewicz/583/441
Mazzuca/583/441
Nguyen/545/442
Nims/584/441
Pepe/581/441
HST LEVEL IIIB CCB MEMBERS
X M. Jarosz/442
X M. Kienlen/442
R. King/442
X R. Lundquist/730/442
INFO:
(Level IIIB only)
D. Scheve/440
K. Kalinowski/440
J. Decker/440
AD
R.
M.
E.
R.
S.
K.
C.
R.
D.
J.
G.
M.
E.
S.
X
X
3A
3A
X
X
X
X
Hubbard/740/442
Jenkins/549/442
Kamen/730/442
Krupacs/740/442
Metzger/543/442
Miller/565/442
Nguyen/545/442
Pham/740/442
Phan/543/442
Purves/571/440
Sticka/303
Vernacchio/441
Watson/441
Wilkinson/441
M. Kienlen/442
R. Lundquist/730/442
M. Turczyn/730/442
X
X
X
X
X
L.
M.
H.
K.
J.
Purves/571/440
Simons/730/441
Wajsgras/563/441
Walyus/581/441
Wood/551/440
K. Miller/442
X R. Moe/442
3A R. Sticka/303/440
X R. Werneth/442
P. Burch/441
D. Douds/441
J. Gainsborough/441
M.
K.
B.
E.
J.
A.
D.
T.
M.
L.
R.
A.
W.
C.
E. Ruitberg/441
C. Wilkinson/441
P.
H.
S.
R.
X P.
X T.
X J.
X M.
3A J.
X D.
Salerno/565/442
Smith/740/442
Stanford/442
Strafella/730/442
Sullivan/740/442
Toutsi/303/442
Townsend/545/442
Turczyn/730/442
Wood/551/440
Zimbelman/730/442
HST LEVEL IV CCB
X
X
X
D. SIMPSON/582
F. SEXSON-RAYL
/BATC/WFC3
F. DOLAN/CREARE
R. KUTINA/ST ScI
X
X
X
X
T. NOTHEY/HSTOMS/581
F. SEXSON-RAYL
/BATC/AC
S. BUSCHING/JHU/AC
N. RINGEL/LMMS/CHAMP
X
J. ANDREWS/UCOL/COS
F. SEXSON-RAYL
/BATC/COS
L. HERRELL/JPL
N. PITERSKI/SWALES
11/3/00
HST FLIGHT PROJECTS CONFIGURATION CHANGE REQUEST
PROGRAM
HUBBLE SPACE TELESCOPE
TITLE
B/L SMR-3029 HST SM3B OBSERVATORY VERIF. PLAN
CCR NO.
4834
ORIGINATOR
DATE INITIATED
04/11/2001
ORIGINATOR'S CHG. NO.
EFFECTIVITY
AST
COSTAR
DADS
ESS
FS&S
FOC
FOS
HRS
HSP
HST
MOSES
NICMOS
ORU
OTA
A. VERNACCHIO/HST/441
SPONSOR/CODE
SA-I
SA-II
SI C&DH-I
SI C&DH-II
SSM
ST SCI
STAR
STIS
STOMS
VEST
WFPC-I
WFPC-II
OTHER
OPS/SM
A. VERNACCHIO/441
CHANGE CLASS
PHONE
301-286-1337
TYPE OF CHANGE
I
II
MILESTONE
INTERFACE
SOFTWARE
PRELIMINARY
DOCUMENT
POWER
OTHER
FORMAL
COST
NO
WEIGHT
DOCUMENTS OR SOFTWARE AFFECTED
SMR-3029
PROBLEM
The attached draft version of SMR-3029 HST Servicing Mission 3B Observatory Verification Plan dated March
30, 2001 requires baselining by the HST Level 2 CCB. This document establishes the plan for verifying that the
HST Orbital Replacement Units and Orbital Replacement Instruments installed, replaced, or serviced on the
HST Observatory are functioning properly. The plan commences once the HST has been released from the
Orbiter's Remote Manipulator System and terminates upon initiation of normal science operations with all
scientific instruments. Participating organizations are GSFC/Code 440, GSFC/Code 441, GSFC/Code 442, ST
ScI, STOMS, BATC/ACS, JHU, LMMS/CHAMP, Creare Inc., and GSFC/Code 582.
PROPOSED SOLUTION
Baseline the attached draft version of SMR-3029 HST SM3B Observatory Verification Plan by the Level 2
Configuration Control Board. The document will be maintained by the HST Configuration Management (CM)
Office/Code 440. Changes will be submitted by Configuration Change Requests (CCRs) and Preliminary
Specification Change Notices (PSCNs).
BOARD ACTION
APPROVE
APPROVE WITH
CHANGE
DISAPPROVE
WITHDRAW
APPROVAL LEVEL
REQUIRED
LEVEL I HQS
LEVEL II JSC
LEVEL II GSFC
LEVEL III
(A) OPERATIONS
(B) SERVICING
CRITICALITY LEVEL
PROCUREMENT CHANGE ORDER CLASSIFICATION
EMERGENCY
ROUTINE
URGENT
URGENT
OPTION 1
OPTION 1
ROUTINE
OPTION 2
OPTION 2
EMERGENCY
LEVEL IV
CONTR/ASSOC
COMMENTS
LEVEL IIIA CHAIRPERSON
DATE
LEVEL IIIB CHAIRPERSON
DATE
LEVEL II CHAIRPERSON
DATE
05/04/1999
I
SM R-3029
Draft
March 30, 2001
HUBBLE SPACE TELESCOPE
THIRD SERVICING MISSION B
OBSERVATORY VERIFICATION
PLAN
MARCH 2001
Goddard Space Flight Center
Greenbelt, Maryland
SMR-3029
Draft
March 30, 2001
CONTENTS
Section
Page
1. INTRODUCTION ............................................. 1-1
1.1
SCOPE ............................................... 1-6
1.2
CONFIGURATION CONTROL ............................... 1-9
2. OVERVIEW OF THE HST OBSERVATORY VERIFICATION PROGRAM ..... 2-1
2.1
ACTIVITY SUMMARY FORMAT ............................. 2-1
2.2
STRUCTURES AND MECHANISMS SUBSYSTEM ................. 2-4
2.2.1
2.3
2.4
NOBL Thermal Monitoring ..................... 2-5
ELECTRICAL POWER SUBSYSTEM .......................... 2-7
2.3.1
SAIII Drive System Performance .............. 2-8
2.3.2
SAIII Power Generation Performance ......... 2-10
2.3.3
Power Control Unit (PCU) Performance ....... 2-12
OPTICAL TELESCOPE ASSEMBLY/FINE GUIDANCE SYSTEM .... 2-14
2.4.1
Guide Star Acquisition Verification ........ 2-15
2.4.2
Verification of Operational Calibrations ... 2-17
2.4.3
FGS Mini-OFAD .............................. 2-19
2.4.4
FGS-to-FGS Alignment ....................... 2-20
2.4.5
FGS K-Factor Determination ................. 2-22
2.4.6
FGS Jitter Test ............................ 2-24
2.4.7
FGS Astrometer Calibration Verification .... 2-26
ii
SMR-3029
Draft
March 30, 2001
CONTENTS (Continued)
Section
2.5
Page
POINTING CONTROL SUBSYSTEM ......................... 2-28
2.5.1
FHST Field of View Check ................... 2-29
2.5.2
First Attitude Determination and Initial Gyro
Drift Rate Bias Determination .............. 2-31
2.6
2.5.3
Attitude Initialization .................... 2-33
2.5.4
FHST/FHST Alignment ........................ 2-34
2.5.5
RGA Polarity Check ......................... 2-36
2.5.6
Gyro/FHST Alignment ........................ 2-37
2.5.7
FHST/FGS Alignment ......................... 2-39
2.5.8
Vehicle Disturbance Test (VDT) ............. 2-41
2.5.9
Transfer Function Test (TFT) ............... 2-44
ADVANCED CAMERA FOR SURVEYS ........................ 2-47
2.6.1
Load and Dump On-Board Memory .............. 2-49
2.6.2
Science Data Buffer Check .................. 2-51
2.6.3
CCD Functional ............................. 2-53
2.6.4
CCD Temperature Set Point Determination .... 2-56
2.6.5
ACS SBC Anomalous Recovery Test ............ 2-58
2.6.6
ACS SMOV Contamination Monitoring .......... 2-60
2.6.7
ACS to FGS Alignment ....................... 2-62
2.6.8
HRC Coronagraph Acquisition ................ 2-64
2.6.9
ACS Coarse Corrector Alignment ............. 2-67
2.6.10 ACS Fine Corrector Alignment ............... 2-69
2.6.11 ACS Image Quality and PSF Measurement ...... 2-71
2.6.12 HRC Coronagraph Repeatability .............. 2-73
2.6.13 ACS Image Stability Verification ........... 2-75
2.6.14 CCD and SBC Flat Fielding Stability ........ 2-78
iii
SMR-3029
Draft
March 30, 2001
CONTENTS (Continued)
Section
Page
2.6.15 ACS Sensitivity ............................ 2-82
2.6.16 SBC Detector Mini-Functional ............... 2-83
2.6.17 SBC Dark Rate Measurement .................. 2-84
2.6.18 ACS SBC Image Quality and PSF Measurement .. 2-86
2.6.19 Scattered Light in Coronagraphic Observations2-88
2.6.20 ACS Ramp Filter Test ....................... 2-90
2.6.21 CCD and SBC Geometric Distortion ........... 2-93
2.6.22 ACS Grism/Prism Performance Check .......... 2-96
2.6.23 ACS CCD Hot Pixel Annealing ................ 2-98
2.6.24 CCD Flash Verification .................... 2-100
2.7
DATA MANAGEMENT SUBSYSTEM ......................... 2-102
2.8
INSTRUMENTATION AND COMMUNICATION SUBSYSTEM ....... 2-102
2.9
SCIENTIFIC INSTRUMENTS CONTROL AND DATA
HANDLING SUBSYSTEM ............................... 2-102
2.10 POINTING AND SAFEMODE ELECTRONICS ASSEMBLY ........ 2-102
2.11 CORRECTIVE OPTICS SPACE TELESCOPE AXIAL REPLACEMENT 2-102
2.12 SPACE TELESCOPE IMAGING SPECTROGRAPH .............. 2-103
2.12.1 Pre-SM Calibration ........................ 2-104
2.12.2 CCD Functional ............................ 2-106
2.12.3 Image Quality ............................. 2-108
2.12.4 MAMA Dark vs. Temperature ................. 2-110
2.12.5 Jitter Test ............................... 2-112
2.12.6 End of BEA Test ........................... 2-114
2.12.7 Contamination Monitor ..................... 2-116
2.12.8 CCD Bias .................................. 2-118
2.12.9 CCD Darks ................................. 2-120
2.12.10 MAMA Darks ................................ 2-122
iv
SMR-3029
Draft
March 30, 2001
CONTENTS (Continued)
Section
Page
2.12.11 Corrector Alignment ....................... 2-124
2.13 NEAR INFRARED CAMERA MULTI-OBJECT SPECTROMETER .... 2-125
2.13.1 NICMOS Filter Wheel Mechanism Test ........ 2-126
2.13.2 NICMOS FOM Operation Test ................. 2-128
2.13.3 NICMOS Flats/Quantum Efficiency ........... 2-129
2.13.4 NICMOS Detector Read Noise/Shading/Cosmic Ray
Rates ..................................... 2-131
2.13.5 NICMOS Transfer Function Test ............. 2-133
2.13.6 NICMOS Fine Optical Alignment ............. 2-135
2.13.7 NICMOS NIC3 Fine Optical Alignment ........ 2-137
2.13.8 NICMOS Focus Monitor ...................... 2-139
2.13.9 NICMOS Aperture Locations ................. 2-141
2.13.10 NICMOS Plate Scale ........................ 2-143
2.13.11 NICMOS Mode 2 Target Acquisition Test ..... 2-145
2.13.12 NICMOS Coronagraphic Performance .......... 2-147
2.13.13 NICMOS Internal Flats ..................... 2-149
2.13.14 NICMOS Photometry Test .................... 2-151
2.13.15 NICMOS SAA CR Persistence Test ............ 2-153
2.13.16 NICMOS Astronomical Persistence Test ...... 2-155
2.13.17 NICMOS Thermal Background ................. 2-157
2.13.18 NICMOS Grisms Absolute Sensitivity ........ 2-159
2.13.19 NICMOS Grisms Wavelength Calibration ...... 2-160
2.14 NICMOS Cooling System (NCS) ....................... 2-162
2.14.1 Start NICMOS Cooling System (NCS) ......... 2-163
2.15 WIDE FIELD/PLANETARY CAMERA 2 ..................... 2-169
v
SMR-3029
Draft
March 30, 2001
CONTENTS (Continued)
Section
Page
2.15.1 WFPC2 Transition From Protect Safe Mode to Hold
Mode to Protect Decontamination Mode ....... 2-170
2.15.2 WFPC2 Cool Down, Contamination Monitor and
Focus Check ................................ 2-172
2.15.3 WFPC2 Lyman Alpha Check .................... 2-174
2.15.4 WFPC2 Flat Field Calibration ............... 2-176
2.15.5 WFPC2 Relative Photometry Calibration ...... 2-177
2.15.6 WFPC2 Point Spread Function Verification ... 2-178
2.15.7 WFPC2 Internal Monitors .................... 2-179
2.16 EARLY RELEASE OBSERVATIONS ....................... 2-181
2.16.1 Early Release Observations ................ 2-182
3. SMOV NOMINAL TIMELINE .................................... 3-1
3.1
REAL-TIME COMMAND PHASE ............................. 3-6
3.1.1
3.2
HEALTH AND SAFETY SPC PHASE ......................... 3-6
3.2.1
3.3
Real-Time Command Phase Activity Table....... 3-6
Health and Safety SPC Phase Activity Table . 3-11
SCIENCE MISSION SPECIFICATION COMMAND PHASE ........ 3-11
3.3.1
SMS Command Phase Activity Table ........... 3-11
APPENDIX A REQUIREMENTS TRACEABILITY MATRIX.................. A-1
vi
SMR-3029
Draft
March 30, 2001
ILLUSTRATIONS
Figure
Page
1-1
SMOV Management Organization............................ 1-3
1-2
SMOV Phase Activity Flow................................ 1-7
3-1
SMOV Timeline Summary................................... 3-3
3-2
SMOV Network Timeline................................... 3-4
vii
SMR-3029
Draft
March 30, 2001
TABLES
Table
Page
2-1
Verification Activity for the Structure & Mechanisms.... 2-4
2-2
Verification Activity for the EPS....................... 2-7
2-3
Verification Activity for the OTA...................... 2-14
2-4
Pointing Control Subsystem SMOV Activities............. 2-28
2-5
ACS SMOV Activities.................................... 2-47
2-6
STIS SMOV Activities................................... 2-86
2-7
NICMOS SMOV Activities................................ 2-125
2-8
Verification Activity for the NICMOS Cooling System... 2-162
2-9
WF/PC-2 SMOV Activities............................... 2-169
2-10 ERO Activities........................................ 2-181
3-1
SMOV Milestone Schedule................................. 3-2
3-2
Sample Activity Table................................... 3-5
3-3
Real Time Command Phase Activity Table.................. 3-8
3-4
Health and Safety SPC Phase Activity Table............. 3-12
3-5
SMS Command Phase Activity Table....................... 3-13
A-1
Verification Requirements Table......................... A-3
viii
SMR-3029
Draft
March 30, 2001
ACRONYMS
ACE
Actuator Control Electronics
ACP
Astronaut Control Panel
ACQ
Acquisition
ACS
Actuator Control Subsystem/Advanced Camera for Surveys
AD
Activity Description/Aperture Door
ADC
Analog to Digital Converter
ADRS
Astrometry Data Reduction System
AFD
Aft Flight Deck
AFM
Actuator Folding Mirror
AI
Artificial Intelligence
AM
Amplitude Modulation
AMS
Actuator Mechanism Subsystem
AOS
Acquisition of Signal
AP
Application Processor
ARU
Attitude Reference Update
AS
Aft Shroud
ASCII
American Standard Code for Information Interchange
ASCS
Aft Shroud Cooling System
AT
Aliveness
ATC
Absolute Time Command
ATP
Absolute Time Processor
AURA
Association of Universities for Research in Astronomy
A & V
Assembly and Verification
BAE
British Aerospace
BAT
Battery
BDF
Block Data Format
BEA
Bright Earth Avoidance
BER
Bit Error Rate
BLD
Bi-Level Discreet
BOD
Bright Object Detector
ix
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
BOP
Bright Object Protection
BOT
Beginning of Tape
BOW
Bright Object Warning
BPI
Bits per Inch
bps
Bits per Second
BPSK
Binary Phase Shift Keying
C
Celsius/Centigrade
CAD
Coarse Attitude Determination
CAL
Calibration
CARD
Constraints and Restrictions Document
CASH
Cross Aft Shroud Harness
CC
Configuration Controller/Command and Control
CCA
Configuration Control Article
CCB
Configuration Control Board
CCBD
Configuration Control Board Directive
CCC
Charge Current Controller
CCD
Charge-coupled Device
CCD/POM
Charge-coupled Device/Pick-off Mirror
CCL
Closed Conference Loop
CCR
Configuration Change Request
CCS
Control Center System
CCTV
Closed Circuit Television
C&DH
Control and Data Handling
CDBS
Calibration Data Base System
CDI
Command Data Interface
CDOS
Customer Data Operations System
CDU
Command Data Unit/Command Detector Unit
CEA
Central Electronics Assembly
CF
Command Format
CG
Center of Gravity/Command Groups
x
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
CIF
Computer Interface (Module)
CL
Command Loader
CLPS
Calibration Lamp Power Supply
CM
Contamination Monitoring/Configuration Management
cm
Centimeter
CMD
Command
CMS
Command Management System
C/O
Checkout
COMM
Communications
COMP
Computer
CONN
Connector
COP
Contingency Operations Procedure/CoProcessor
COSTAR
Corrective Optics Space Telescope Axial Replacement
CPL
Capillary Pump Loop
CPM
Central Processor Module
CPU
Central Processing Unit
CR
Change Request
CRB
Change Review Board
CS
Crew Systems/Control Section
CSS
Coarse Sun Sensor
CSSA
Coarse Sun Sensor Assembly
CT
Current Telemetry
CTE
Charge Transfer Efficiency/Coefficient of Thermal
Expansion
CU/SDF
Control Unit/Science Data Formatter
CVL
Cryro Vent Line
CVZ
Continuous Viewing Zone
D/A
Digital-to-Analog
DAC
Digital-to-Analog Converter
dB
Decibel
xi
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
dB/Hz
Decibel-Hertz
DB
Data Base
DB
Diode Bus
DBA
Diode Bus Assembly
DBC
Diode Bus Controller
DBMS
Data Base Management System
DC
Detector Controller
DCE
Deployment Control Electronics
DCF
Data Capture Facility
DEC
Declination/Digital Equipment Corporation
DF-224
HST/SSM Flight Computer
DH
Data Handling
DIM
Data Input Module/Data Interface Module (OCE)
DIU
Data Interface Unit
DM
Data Management
DMS
Data Management Subsystem
DMU
Data Management Unit
DN
Derived Nominal/Digital Number
DOB
Deployable Optical Bench (COSTAR)
DOC
Data Operations Center
DOD
Depth of Discharge
DOV
Director of Orbital Verification
DPC
Direct Power Converter
DRD
Data Requirements Document
DSN
Deep Space Network
E/A
Ephemeris/Attitude
ECA
Electronics Control Assembly
EC/LSS
Environmental Control/Life Support Systems
ECU
Electronic Control Unit
ED
Engineering Data
xii
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
EDAC
Error Detection and Correction
EDB
Engineering Data Base
EMI
Electromagnetic Interface
EMU
Extra-vehicular Mobility Unit
ENG
Engineering
EOD
Enter Orbit Day
EOF
End of File
EON
Enter Orbit Night
EOT
End of Tape
EP/TCE
Electronic Power & Thermal Control Electronics
EP/TCS
Electronic Power & Thermal Control System
EPER
Edge Pixel Extended Response
EPS
Electrical Power Subsystem
ERO
Early Release Observation
ESA
European Space Agency
ESM
Electronic Support Module
ESS
Engineering Support System
ESTR
Engineering and Science Tape Recorder
ETR
Engineering Tape Recorder/Eastern Test Range
EU
Engineering Unit
EV
Extra Vehicular
EVA
Extra-vehicular Activity
FAD
Fine Attitude Determination
FALIGN
FHST Alignment
FDF
Flight Dynamics Facility
FF3
Fold Flat 3
FGE
Fine Guidance Electronics
FGS
Fine Guidance Sensor
FGSS
FGS System
FHST
Fixed Head Star Tracker
FIFO
First-in First-out
xiii
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
FM
Frequency Modulation
FMT
Format
FO
Flight Operations (MOC)
FOC
Faint Object Camera
FOM
Field Off-set Mirror
FOT
Flight Operation Team
FOV
Field of View
FPA
Focal Plane Assembly
FPAS
Focal Plane Assembly Shroud
FRP
Functional and Performance Requirements
FS
Finish to Start
FSK
Frequency Shift Keying
FSS
Flight Support System/Flight Servicing Structure
FS&S
Flight Systems and Servicing
FSW
Flight Software
FUV
Far Ultraviolet
FWD
Forward
FWHM
Full Width Half Maximum
FWM
Filter Wheel Mechanism
GBU
Gyro Bias Update
GEA
Gimbal Electronics Assembly
GG
Gravity Gradient
GGM
Gravity Gradient Mode
GHz
Gigahertz
GMT
Greenwich Mean Time
GO
General Observer
GRND
Ground
GS
Ground System/Guide Star
GSE
Ground Support Equipment/Ground Systems Engineering
GSFC
Goddard Space Flight Center
xiv
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
GSOWG
Ground Systems and Operations Working Group
GSSS
Guide Star Selection System
GSTDN
Ground Spacecraft Tracking & Data Network
HGA
High Gain Antenna
HGAS
High Gain Antenna System
HGBU
High Gyro Bias Update
HLD
High Level Discrete (Command Type)
HOPRS
HST Observations Problem Reports
HRC
High Resolution Camera
H & S
Health and Safety
HST
Hubble Space Telescope
HSTAR
Hubble Space Telescope Anomaly Report
HSTP
Hubble Space Telescope Project
HV
High Voltage
H/W
Hardware
HWCC
Hardware Change Control
Hz
Hertz
I & C
Instrumentation and Communications Subsystem
ICU
Instrumentation Control Unit
ID
Identification
IDB
Internal Data Base
IDL
Interactive Data Language
I/F
Interface
INTFLAT
Internal Flat
I/O
Input/Output
IOU
Input Output Unit
ips
Inches Per Second
IR
Infrared
IRAF
Image Reduction Analysis Facility
xv
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
I & T
Integration and Test
ITS
Internal Test Source
IUE
International Ultra-Violet Explored
JSC
Johnson Space Center
k
Kilo
KA
Keep Alive
KBPI
Kilobits Per Inch
KBPS
Kilobits Per Second
Kbytes
Kilobytes
kg
Kilogram
km
Kilometer
KSC
Kennedy Space Center
LBBIAS
Long Baseline Bias
LED
Light Emitting Diode
LGA
Low Gain Antenna
LGBU
Low Gyro Bias Update
LHCP
Left Hand Circular Polarization
LLD
Low Level Discrete
LMSC
Lockheed Martin Space Company
LMTO
Lockheed Martin Technical Operations
LMU
Logical Memory Unit
LOS
Line of Sight/Loss of Signal
LSB
Least Significant Bit
LVPS
Low Voltage Power Supply
m
Meter
MA
Multiple Access
MAMA
Multi-anode Microchannel Array
xvi
SMR-3029
Draft
March 30, 2001
ACRONYMS (Continued)
Mbps
Megabits Per Second
MCC
Mission Control Center
MCE
Monitor and Control Electronics
MCP
Microchannel Plate
MCU
Mechanism Control Unit
MEB
Main Electronics Box
MET
Mission Elapsed Time
MF
Major Frame
MHz
Megahertz
min
Minute
MIQ
Maximum Image Quality
MLI
Multi-Layer Insulation
mm
Millimeter
MM
Maintenance Mission
MMI
Man-Machine Interface
MOC
Mission Operations Contractor
MOI
Moment of Inertia
MOM
Mission Operations Manager
MOR
Mission Operations Room
MOU
Memorandum Of Understanding
MPO
Mission Planning Office
MPT
Mission Planning Terminal
Msec
Millisecond
MSFC
Marshall Space Flight Center
MSS
Magnetic Sensing System
MT
Magnetic Torquer
MTB
Magnetic Torquer Bar
MTE
Magnetic Torquer Electronics
MTP
Master Test Procedure/Master Timing Pulse
MTS
Magnetic Torquing System
MU
Memory Unit
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ACRONYMS (Continued)
MUX
Multiplexer
N/A
Not Applicable
NASA
National Aeronautics and Space Administration
NASCOM
NASA Communications Network
NCC
NICMOS Cryogenic Cooler/Network Control Center
NCS
NICMOS Cooling System
ND
Neutral Density
NGC
New General Catalog
NIC
Near Infrared Camera
NICMOS
Near-Infrared Camera and Multi-Object Spectrometer
nmi
Nautical Miles
NOBL
New Outer Blanked Layer
NSSC-1
NASA Standard Spacecraft Computer, Model 1
NUV
Near Ultraviolet
OA
Operations Astronomer
OBC
On-Board Computer
OC
Operations Controller
OCC
Operations Control Center
OCCO
Oven Controlled Crystal Oscillator
OCE
Optical Control Electronics
OCS
Optical Control Subsystem
OFAD
Optical Field Angle Distortion
OFLS
Off-Line System
O&GS
Operations and Ground Systems
OLD
Off Load Devices (Solar Array)
OLS
On-Line System
OMS
Orbital Maneuvering System
O/P
Output
OPD
Operations Department of ST ScI
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ACRONYMS (Continued)
OPS
Operations
ORD
Operations Requirements Document
ORI
Orbital Replacement Instrument
ORU
Orbital Replaceable Unit
OTA
Optical Telescope Assembly
OTASIM
Optical Telescope Assembly Simulator
OV
Observatory Verification
PAM
Pupil Adjustment Mechanism
PASS
POCC Application Software Support
P/B
Playback
PC
Planetary Camera
PCDU
Power Control and Distribution Unit
PCEA
Pointing Control Electronics Assembly
PCM
Pulse Code Modulation
PCS
Pointing Control Subsystem
PCSIU
PCS Interface Unit
PCU
Power Control Unit
PDA
Photon Detector Assembly
PDB
Project Data Base
PDM
Primary Drive Motor/Primary Deployment Mechanism
PDU
Power Distribution Unit
PGSC
Payload General Support Computer
PI
Principal Investigator/Payload Interrogator
PID
Proportional Integral Derivative
PIP
Payload Integration Plan
PIT
Processor Interface Table
P/L
Payload
PM
Primary Mirror
PMT
Photo Multiplier Tube
PMU
Physical Memory Unit
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ACRONYMS (Continued)
PN
Planetary Nebula
POCC
Payload Operations Control Center
POL
Point of Light
POM
Pick off Mirror
PORTS
Preliminary Operations Requirements & Test Support
PRCS
Primary Reaction Control System
PRD
Program Requirements Document/Project Reference Data
PRS
PORTS Refurbishment System
PROM
Programmable Read Only Memory
PRT
Planned Real-Time
PSCN
Preliminary Specification Change Notice
PSEA
Pointing and Safemode Electronics Assembly
PSF
Point Spread Function
PSI
Pounds per Square Inch
PSK
Phase Shift Keying
PSP
Payload Signal Processor
PSTOL
PORTS Systems Test and Operations Language
PWR
Power
Q(ch)
Quadrature-phase (channel)
QCI
DF-224 On-board Quaternion (variable name in FSW)
QD
Quick Disconnect
Q & I
Quadrature-phase and In-phase (channel)
QCM
Quartz Crystal Monitor
QPSK
Quadrature-phase Shift Keying
RAM
Random Access Memory
REFOC
Refocus
REC
Record
REL
Release
REV
Revolution/Revision
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ACRONYMS (Continued)
RF
Radio Frequency
RFI
Radio Frequency Interface
RGA
Rate Gyro Assembly
RHCP
Right Hand Circular Polarization
RIU
Remote Interface Unit
RMGA
Retrieval Mode Gyro Assembly
RMS
Remote Manipulator System
ROP
Routine Operating Procedure
ROSI
Raytheon Optical System Inc.
rpm
Revolutions Per Minute
RSU
Rate Sensor Unit/Remote Sensing Unit
R/T
Real-time
RTC
Real-time Command
RTCS
Real-time Command Sequence
RW
Reaction Wheel
RWA
Reaction Wheel Assembly
SA
Solar Array/Single Access
SA3
Solar Array Three (Replacement Arrays)
SAA
South Atlantic Anomaly
SAC
Sensor Analysis & Calibration
SACOPS
Sensor Analysis & Calibration Operations
SADA
Solar Array Drive Adapter
SADE
Solar Array Drive Electronics
SADM
Solar Array Drive Mechanism
SAGA
Solar Array Gain Augmentation
SAT
SSA Transmitter
S-band
1500 - 5200 MHz
SBC
Solar Blind Channel
S/C
Spacecraft
SCAMA
Switching, Conferencing and Monitoring Arrangement
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ACRONYMS (Continued)
ScI
Science Institute
SCR
Schedule Confirmation Request (NCC)/Strip Chart
Recorder
SD
Science Data
SDAS
Science Data Analysis Software
SDF
Science Data Formatter
SDM
Secondary Deployment Mechanism
SDN
Schedule Deletion Notification (NCC)
SDPF
Sensor Data Processing Facility
SDU
Signal Distribution Unit
SE
Systems Engineering
sec
Seconds
SEER
HST Systems Engineering Evaluation Room
SESD
Science and Engineering Systems Division
SHP
Standard Header Packet
SI
Scientific Instrument
SIAF
Science Instrument Aperture definition File
SIC
Spacecraft Identification Code (NCC)
SI C&DH
SI Control and Data Handling Subsystem
SIM
Simulation/Simulator
S & M
Structures and Mechanisms Subsystem
SM
Servicing Mission/Safe Mode/Secondary Mirror
SM3A
Third Servicing Mission A
SM3B
Third Servicing Mission B
SMA
Secondary Mirror Assembly (OTA)
SMC
Safe Mode Computer
SMEA
Safe Mode Electronics Assembly
SMIT
Service Mission Integrated Timeline
SMM
Science Mission Manager (ScI)
SMOV
Servicing Mission Observatory Verification
SMS
Science Mission Specification
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ACRONYMS (Continued)
SMU
STFS Safemode Utility
SOC
State of Charge
SOFA
Selectable Optical Filter Assembly
SOP
Standard Operating Procedure
SOR
Science Operations Room
SP
Sun Point
SPA
Solar Panel Assembly
SPC
Stored Program Command
SPIF
Shuttle-POCC Interface Facility
SR
Schedule Result (NCC)
SS
Safing Subsystem/Start to Start/ Shift Supervisor
SSA
S-band Single Access
SSATX2-R
S-band Single Access Transmitter 2 (Replacement)
SSD
Space Systems Division (LMCO)
SSE
Space Support Equipment
SSM
Support Systems Module
SSPCP
STFS Special SPS Processor
SSR
Solid State Recorder
ST
Space Telescope
STAT
Space Telescope Astrometry Team
STDN
Spaceflight Tracking and Data Network
STDOC
Space Telescope Data Operations Center
STFS
Flight Software Subsystem (DF224)
STIS
Space Telescope Imaging Spectrograph
STOCC
Space Telescope Operations Control Center
STOMS
Space Telescope Observatory Management System
STR
Science Tape Recorder
STS
Space Transportation System
STSDAS
Space Telescope Science Data Analysis System
ST ScI
Space Telescope Science Institute
ST ScIF
Space Telescope Science Institute Facility
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ACRONYMS (Continued)
S/W
Software
SYNC
Synchronization
TBD
To Be Determined
TBR
To Be Resolved
TBS
To Be Specified
TC
Thermal Control
T & C
Telemetry and Command
TCE
Thermal Control Electronics
TCS
Thermal Control Subsystem
TDRS
Tracking and Data Relay Satellite
TDRSS
Tracking and Data Relay Satellite System
TDRST
Tracking and Data Relay Satellite Terminal
TEC
Thermoelectric Cooler
TFC
Telemetry Format and Control
TFT
Transfer Function Test
TLM
Telemetry
TP
Timed Processor
TTRB
Telescope Time Review Board
TTSC
Telescope Time Steering Committee
TRSWCC
Trim Relay Software Charge Control
TSPC
Timed Special Processor
URL
Uniform Resource Locator
UTC
Universal Time Coordinated
UV
Ultraviolet
VAP
Velocity Aberration Parallax
VCS
Vapor Cooled Shield
VDD
Version Description Document
VDT
Vehicle Disturbance Test
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ACRONYMS (Continued)
VEL
Velocity
VEST
Vehicle Electrical System Test Facility
VIK
Voltage Improvement Kits
VISFLATS
Visible Flats
VOCC
VEST Operations Control Center
VSC
Voltage Sensing Circuit
VSS
Vehicle Support Software
VTFE
Voltage Temperature Front End
WD
White Dwarf
WFC
Wide Field Camera
WF/PC
Wide Field Planetary Camera
WF/PC2
Wide Field Planetary Camera II
WFS
Wave Front Sensor
ZOE
Zone of Exclusion
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TBD/TBR LIST
Item No.
1.
2.
3.
4.
5.
6.
7.
Text
Location
Section
2.6.4
Section
2.13.5
Section
2.13.11
Section
2.13.13
Section
2.13.17
Section
2.14.1
Section
2.16.1
Description
ACS-06 – CCD Temperature
Set Point Determination
NICMOS-05 – NICMOS
Transfer Function Test
NICMOS-12 – NICMOS Mode 2
Target Acquisition Test
NICMOS-14 – NICMOS
Internal Flats
NICMOS-18 – NICMOS Thermal
Background
NCS-01 – Start NICMOS
Cooling System (NCS)
ERO-01 – Early Release
Observations
xxvi
Responsible
Party
Due Date
STScI
07/01/01
STScI
07/01/01
STScI
07/01/01
STScI
07/01/01
STScI
07/01/01
STScI
05/31/01
STScI
07/01/01
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1.
INTRODUCTION
The Hubble Space Telescope (HST) Servicing Mission Observatory
Verification (SMOV) program for Servicing Mission 3B (SM3B)
program has been established to verify that the HST Orbital
Replacement Units (ORUs), and Orbital Replacement Instruments
(ORIs) installed, replaced, or serviced on the HST Observatory
are functioning properly.
The SMOV program commences once the
HST has been released from the Orbiter's Remote Manipulator
System (RMS), and terminates upon initiation of normal science
operations with all scientific instruments.
The SMOV Manager is responsible for the Observatory Verification
operations of the HST Observatory.
The SMOV Manager is
chairperson of the SMOV Management Team, which is composed of
representatives from the HST Operations and Ground Systems
Project (O&GS), the HST Flight Systems and Servicing Project
(FS&S), and the Space Telescope Science Institute (ST ScI).
The
SMOV Manager coordinates all rapid turnaround changes with the
Telescope Time Steering committee (TTSC).
The SMOV Management organization is headed by the SMOV Manager
and is supported by the SMOV Planning Group consisting of
representatives from a number of elements from within the Project
including prime mission contractors and other directorates at the
GSFC.
Its responsibility is to efficiently and safely conduct
the Observatory Verification activities while concurrently
allowing the maximum amount of normal science operations to take
place.
This responsibility is expected to extend for
approximately four months after Servicing Mission 3B (SM3B).
The
SMOV organization verifies the performance of the newly installed
hardware and conduct appropriate tests to ensure the Observatory
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is functioning properly.
Figure 1-1 shows the SMOV Management
organization.
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SMO V
MANAGER
SMO V
MANAGEMENT
TEA M
SMO V
PLA NNING
GRO UP
SCI ENCE &
ENG INEERING
TEA MS
PUBLIC
AFFAIRS
CONTROL
CENTER
OPERATI ONS
STS cI
INS TITU TE
FIGURE 1-1
SMO V Manageme nt Organiz ation
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The SMOV Management Team has the following responsibilities:
•
Publish the SMOV Plan and its subsequent updates
•
Resolve SMOV planning and scheduling conflicts and issues
•
Define/adjust priorities for SMOV activities
•
Track SMOV progress and report status to the HST Project
Manager
•
Identify and reallocate failed SMOV activities and
observations as appropriate
•
Track SMOV test results
•
Provide the weekly SMOV candidate activity list to the ST
ScI at least one week before the generation of the flight
SMS is due.
This one week lead time will gradually be
increased as the critical path, linked activities are
completed (i.e., once the alignments are complete)
•
Interface with the HST Senior Scientist for NASA Public
Affairs planning and information
•
Define the content requirements and coordinate inputs for
the SMOV Execution report.
Servicing Mission SI calibration and alignment activity progress
will be reported to the ST ScI's Telescope Time Review Board
(TTRB) on a weekly basis.
The TTRB will provide senior science
oversight to the SMOV Management Team and will be called upon to
address requests for repeated SMOV science-related activities or
requests for additional data, when the requests exceed six orbits
of observing time.
HST Observations Problem Reports (HOPRs) will
be used to document SMOV observations that are repeated during
the verification period such as SI alignment and calibrations.
For those cases where the SMOV activity failed to execute in its
entirety due to problems such as safemode entry or guide star
acquisition failures, HOPRs will not be utilized.
All requests
for additional SMOV spacecraft time, in excess of six orbits, to
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accomplish the goals of the SI SMOV programs will be reviewed
with and recommended for approval/rejection by the TTRB.
The ST ScI SMOV Lead will be the common link between the TTRB and
the Project SMOV Management Team.
The Lead will be responsible
for coordinating any TTRB reviews and for reporting back to the
SMOV
Management Team.
If the observation problem has been caused by a
spacecraft or subsystem failure/anomaly, the Lead will file an
HST Anomaly Report, if one has not already been filed.
The three divisions involved in day-to-day operations of the HST
are represented on the TTRB, namely the Data Systems Division,
Science and Engineering Systems Division (SESD), and the Science
Support Division (SSD), and the Servicing Mission Office.
The
TTRB will make recommendations to the ST ScI Director's Office on
the disposition of requests for additional SMOV time allocation,
in excess of six orbits, with Director's Office concurrence on
recommendations required within the week following the TTRB
disposition.
The importance of timely disposition is recognized
and will be supported whenever possible.
In the event that
additional information is required before a decision can be
reached, the appropriate proposer/team members will be asked to
present this information to the TTRB or a cognizant TTRB splinter
group.
A closure review will be conducted at the end of SMOV in which
representatives of the SM Verification Team and the TTRB will be
expected to serve as review/panel members.
This closure review
will consist of a walkthrough of the documented SMOV objectives
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and requirements and how they have been met or what liens exist
against the program and how they will be closed.
The SMOV activity flow is graphically portrayed in Figure 1-2.
It should be noted that this is a high-level functional plan, and
is not intended to represent the exact ordering of activities for
any given day. The SMOV plan provides a "big picture" view of the
observatory verification program, whereas the HST Command Plan is
the medium through which on-orbit activities are scheduled,
executed and verified during the Real-Time (R/T) and Health and
Safety (H&S) Command Phases.
Science Mission Specifications
(SMS) provide for scheduling and execution of activities during
the SMS command phase.
Note: The Servicing Mission Integrated Timeline (SMIT) and
Command Plan will be developed by the Servicing Mission
Operations Working Group.
These documents will provide the
detailed timeline and implementation approach to be used to
conduct the SMOV activities described in the Real-Time and Health
and Safety phases of the SMOV plan.
1.1
SCOPE
Section 2 summarizes the activities included in the Observatory
Verification Program for the affected HST subsystems, science
instruments, and ground systems.
Section 3.0 contains a SMOV
plan that reflects activities in tabular format.
For clarity and
ease of use, the overall SMOV plan has been broken down into
three major phases, which are determined primarily by the way
activities are executed.
These phases are:
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SMOV PLA N
PROPOSA L GENERA TION
PROPOSA L
IMPL EMENTA TION A ND TEST
TESTING/TRA INING
STA RT SMOV OPERATIONS
REPL AN PROBL EM
SMOV OBSERV ATIONS
SMS/COMMAND
LOA D GENERA TION
FOR OPER. W EEK
EXECUTE OPERA TIONA L WEEK
DA TA PROCESSING
A ND ANA LY SIS
SMOV MA NA GEMENT
TEAM
smov r e su lts
A LL SMOV
A CTIV ITIES COMPLETE
OBSERV ATORY V ERIFICA TION
COMPLETE
SMOV CLOSURE REVIEW
Figure 1-2.
SMOV Phase Activity Flow
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•
Real-time Command Phase during this phase all activities
are executed via real-time commands from the STOCC.
It
is the shortest phase of the SMOV program (approximately
1 day), and covers from HST release from the Orbiter RMS
to activation of the Health and Safety SPC Load.
•
Health and Safety Load Phase activities during this phase
are executed by using a combination of Real-time and
Stored Program Commands, with the majority of the
commanding accomplished via SPCs.
This phase begins once
the uplinked Health and Safety Load is activated and HGA
tracking is initiated, and terminates upon transition
from the Health and
•
Safety Load to a Science Mission Specification generated
SPC load.
The Health and Safety Load phase covers
approximately a 1-day period.
•
Science Mission Specification Phase in this phase the
majority of commands are executed from a SPC load
generated by a Science Mission Specification (SMS).
This
does not preclude however, real-time commanding where
required.
This phase makes up the largest portion of the
SMOV program beginning when the HST is able to support
normal operations via SMS generated SPC loads, and ends
when normal science operations begins.
Appendix A contains a matrix which traces the Level III mission
operations functional requirements applicable to SMOV activities
identified in this plan.
These requirements were a flow-down
from Servicing Mission 3B (SM3B) Level II Requirements (STR-80)
and drive the SMOV program.
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1.2
CONFIGURATION CONTROL
This document shall be controlled by the Office of the Associate
Director of Flight Projects for HST, Goddard Space Flight Center
(GSFC) via the HST Level II Configuration Control Board (CCB).
After formal baselining by the HST Project CCB, any changes to
this document will be accomplished via defined CCB procedures.
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2.
OVERVIEW OF THE HST OBSERVATORY VERIFICATION PROGRAM
Section 2 summarizes the activities (categorized by HST subsystem or
science instrument) that are required to execute the HST Observatory
Verification Program.
The SMOV Plan begins during Segment 3 of the
Servicing Mission Integrated Timeline, when the HST is released from
the Orbiter.
Note:
While the general outline of activities of the SMOV Plan is
reflected in this document, the subsequent proposal generation process
has changed many of the approaches and details within each activity.
A detailed description of the most current version of each SMOV
activity is found by referring to each pertinent proposal.
All SMOV proposals and ROP/Line Range numbers will be listed and
updated at the following Web site:
http://www.stsci.edu/public/propinfo.html
2.1
ACTIVITY SUMMARY FORMAT
Activity Summaries provide the data used to develop the SMOV plan.
They are structured according to the following format, supplying the
specified information shown:
TITLE:
ID:
Paragraph and basic function to be performed.
A unique identification number used to categorize and track each
activity summary.
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APPLICABLE REQUIREMENTS:
Number of the SMOV Requirement to which
this Activity applies.
DESCRIPTION:
performed.
Detailed abstract of the activity that is to be
Included in the description is the purpose for executing
the activity, as well as expected results upon completion of the task.
HOW THE ACTIVITY IS BEST IMPLEMENTED:
Activities may be implemented
using real-time (R/T) commands, stored program commands (SPCs) from a
health and safety computer load, SPCs generated from a Science
Institute Science Mission Specification (SMS), or passive analysis.
DEPENDENCIES:
A listing of prior activities, pre-conditions, and
constraints or restrictions that affect in some way
the activity being described.
the execution of
Also included here are the time delays
associated with each of the designated dependencies.
DURATION:
Expected time to complete the activity.
This time does not
include the times associated with dependencies.
RESULTS:
Detailed description of the expected results or products
generated by completing this activity.
ANALYSIS:
Identifies the required data processing/analysis of
activity results, as well as the ground system updates to continue the
SMOV program.
COMMENTS:
Any further information not previously discussed that is
felt to be pertinent to the execution of the activity.
AUTHOR/ORG/TEL #/E-MAIL:
The authors name, organization, work
telephone number, and e-mail address.
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DATE:
Original date the activity summary was completed, or last
revised.
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2.2
STRUCTURES AND MECHANISMS SUBSYSTEM
Table 2-1 shows the verification activity that must be accomplished
during
SMOV
to
verify
the
thermal
environment
after
the
installation to support normal operations.
Table 2-1
Verification Activity for the Structures & Mechanisms
Activity
Summary #
TCS-01
Observatory
Verification Activity
NOBL Thermal Monitoring
2-4
Execution Duration
Phase
Hr:min
Real-Time
N/A
NOBL
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2.2.1
ID:
NOBL Thermal Monitoring
TCS-01
APPLICABLE REQUIREMENTS: J.10.4.13
DESCRIPTION: The determination of the impact of NOBL installation
is expected to be ongoing for Bays 5, 6, 7 and 8, likely through
and past the SMOV period. The Bay 5 temperatures will be
monitored after NOBL installation for a preliminary determination
of impacts.
Bays 6 through 8 impacts are expected to be small,
perhaps visible during trending. Bay 5 is expected to have
greater impacts due to changing the heat rejection
characteristics of the bay. Since the changes are not expected to
have critical impacts, no specific thermal verification is really
warranted for the SMOV period. Typically the verification of
heater systems and thermal impacts is done on an ongoing basis,
and not tied to the SMOV period, because there are no HST
verification periods dedicated to remaining at certain attitudes
and equipment configurations for thermal verification. Further
correlation of the thermal model beyond the current levels (well
correlated to flight data) does not seem critical enough to
warrant taking the 2-3 days of stable HST configuration needed
for additional correlation data.
HOW THE ACTIVITY IS BEST IMPLEMENTED: HST temperatures are
trended periodically, catching the cold and hot environments as
they occur in the science mission schedule.
Since trending prior
to and post SM3B will be done to determine any thermal changes to
the vehicle, a specific on-orbit engineering test (i.e., stable
thermal conditions for 2 to 3 days) is not required.
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DEPENDENCIES: Continue after the NOBL installation.
DURATION: Through and past the SM3B/SMOV period.
RESULTS: Understanding of the effects of the NOBL on HST thermal
Conditions: N/A
ANALYSIS: N/A
COMMENTS: N/A
AUTHOR/ORG/TEL #/E-MAIL: J. Piquero/HST Thermal Systems LMTO/(301) 901-6181/piquero.jorge@lmmail.hst.nasa.gov
DATE:
April 5, 2000
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2.3 ELECTRICAL POWER SUBSYSTEM
Table 2-2 shows the verification activity that must be accomplished
during SMOV to verify the performance after the installation of the
new Solar Array’s and the Power Control Unit (PCU).
Table 2-2
Verification Activity for the EPS
Activity
Summary #
Observatory
Verification Activity
Execution Duration
Phase
Hr:min
EPS-01
SAIII Drive System Performance
Real-Time
N/A
EPS-02
SAIII Power Generation Performance
Real-Time
N/A
EPS-03
Power Control Unit (PCU) Performance Real-Time
N/A
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2.3.1
ID:
SAIII Drive System Performance
EPS-01
APPLICABLE REQUIREMENTS: J.10.4.14.1.1
DESCRIPTION: Solar Array 3 (SA-3) drive system performance will
be characterized during the SA-3 Functional Test and throughout
the SM-3B Mission Timeline and SMOV period.
The sensed positions
for both the +V2 and –V2 wings will be verified to be within +/3.5 degrees of the commanded position when operating within the
range 0 to 130 degrees, and +/- 5.0 degrees outside this range.
The maximum command profile error during the solar array slews
will also be verified to be less than the safemode test threshold
(10 degrees for 3 seconds). Slew performance will be verified by
analysis of normal EPS telemetry. No special test is required
during SMOV since telemetry is available during SMS commanding.
HOW ACTIVITY IS BEST IMPLEMENTED: Analysis Task Only
DEPENDENCIES: Installation of new Solar Arrays.
DURATION: Throughout the entire SM-3B/SMOV period.
RESULTS: Verify sensed positions are within expected commanded
position limits.
Verify maximum command profile errors are less
than the safemode test threshold.
ANALYSIS: Solar array slews will be monitored in near real-time
throughout the SM-3B Mission Timeline.
Routine trend data will
be reviewed for all SMOV and normal SMS commanding. Slew
performance post SM-3B will be compared to performance prior to
SM-3B.
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COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Stan Krol / EPS MOSES / 301-901-6101 /
skrol@hst.nasa.gov
Date:
January 11, 2001
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2.3.2
ID:
SAIII Power Generation Performance
EPS-02
APPLICABLE REQUIREMENTS: J.10.4.14.1.2
DESCRIPTION: Solar Array 3 (SA-3) power system performance will
be characterized during the SA-3 Functional Test and throughout
the SM-3B Mission Timeline and SMOV period. Power performance
will be assessed and compared to beginning of life predictions
that account for expected degradation.
To the extent possible,
power measurements will be calculated when HST is at orbit noon,
when the sun vector is within +/- 10 degrees of the –V1 axis,
when the solar array to sun incidence angle is less than 5
degrees, and when all the available CCC K-relays and SPA Trim
Relays are closed.
HOW ACTIVITY IS BEST IMPLEMENTED: Analysis Task. A SA power
measurement data take will be performed during the Vehicle
Disturbance Test (VDT). For the data take during the VDT, HST
will be maneuvered to the anti-sun attitude (Sun vector to within
+/- 10 degrees of the -V1, and SA incidence angle less than 5
degrees) and SA Slew Minimization will be turned off.
DEPENDENCIES: Installation of new Solar Arrays.
DURATION: Throughout the entire SM-3B/SMOV period.
RESULTS: Verify that SA3 power output performance meets beginning
of life prediction.
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ANALYSIS: Solar array power will be monitored in near real-time
throughout the SM-3B Mission Timeline.
Routine trend data will
be reviewed for all SMS commanding. Power generation performance
post SM-3B will be compared to performance prior to SM-3B.
COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Stan Krol / EPS MOSES / 301-901-6101 /
skrol@hst.nasa.gov
Date:
March 19, 2001
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2.3.3
ID:
Power Control Unit (PCU) Performance
EPS-03
APPLICABLE REQUIREMENTS: J.10.4.14.1.2
DESCRIPTION: The Power Control Unit (PCU) performance will be
characterized during the PCU Functional Test and throughout the
SM-3B Mission Timeline and SMOV period. Power performance shall
be verified for the expected load range following SM-3B.
No
special test is required during SMOV since telemetry is available
during SMS commanding
HOW ACTIVITY IS BEST IMPLEMENTED: Analysis Task Only
DEPENDENCIES: Installation of new PCU.
DURATION: Throughout the entire SM-3B/SMOV period.
RESULTS: Verify Battery current and voltages are within expected
values. Bus voltages, Bus Impedance, load currents and structure
currents will also be monitored to ensure correct power
performance.
Verify SPA Trim Relay and CCCK Relay operation via status
telemetry and current flow.
ANALYSIS: PCU performance will be monitored in near real-time
throughout the SM-3B Mission Timeline.
COMMENTS: None
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AUTHOR/ORG/TEL #/E-MAIL:
Stan Krol / EPS MOSES / 301-901-6101 /
skrol@hst.nasa.gov
Date:
January 11, 2001
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2.4
OPTICAL TELESCOPE ASSEMBLY/FINE GUIDANCE SYSTEM
Prior to initiating the first verification activity for the OTA/FGS,
the system has been brought to its normal operating configuration.
Table 2-3 shows the verification activities that must be accomplished
during
SMOV
to
verify
the
performance
of
the
Optical
Telescope
Assembly/Fine Guidance System to support normal science operations.
Table 2-3
Verification Activity for the OTA
Activity
Summary #
Observatory
Verification Activity
FGS/OTA-01 Guide Star Acquisition
Execution
Phase
Duration
Hr:min
SMS
04:30
SMS
18:00
FGS/OTA-03 FGS Mini-OFAD
SMS
07:30
FGS/OTA-04 FGS-to-FGS Alignment
SMS
06:00
FGS/OTA-05 FGS K-Factor Determination
SMS
07:30
FGS/OTA-06 FGS Jitter Test
SMS
03:00
FGS/OTA-07 FGS Astrometer Calibration
SMS
N/A
Verification
FGS/OTA-02 Verification of Operational
Calibration
Verification
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2.4.1
ID:
Guide Star Acquisition Verification
FGS/OTA-01
APPLICABLE SMOV REQUIREMENT: J.10.4.8.5
DESCRIPTION: Guide star pairs will be acquired in finelock by the
FGSs. A pair of guide stars will be acquired by two FGSs, tracked
in finelock for a few (~5) minutes, after which time the PCS will
drop to gyros. The same pair will be reacquired in finelock and
tracked for an additional ~5 minutes. This test will be repeated
with a different FGS designated to acquire the primary guide
star. Each of the three FGSs will in turn be designated to
acquire a primary guide star. The total test will require 3 HST
orbits, and possibly less if a suitable CVZ pointing can be
utilized. This test occurs within the BEA following the release
of HST from the orbiter.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: Successful completion of J.10.4.8.4, the gyro-toFHST alignment process.
DURATION: 3 HST orbits, within BEA.
DATA REQUIREMENTS: The data need to be downlinked, either in
real-time or by recorder readout, within two hours.
ANALYSES & RESULTS: N/A
COMMENTS: N/A
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AUTHOR/TELEPHONE/EMAIL/DATE:
Ed Nelan / 410-338-4992 / nelan@stsci.edu / 18-Jan-2000
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2.4.2
ID:
Verification of Operational Calibrations
FGS/OTA-02
APPLICABLE SMOV REQUIREMENT: J.10.4.7.2.1
DESCRIPTION: The distortions, plate scale, and FGS-FGS alignment
for each FGS shall be measured by observing the standard
astrometric star cluster M35, which is accessible to HST from
September through May each year. The test for each FGS will be a
single orbit visit. The telescope pointing, ORIENT, and selected
target stars for each visit will be identical to the appropriate
pre-SM3B baseline visit for the given FGS. In each visit
approximately 25 stars distributed through out the FGS field of
view will be observed in Position Mode, and their relative
angular positions will be determined during post observation data
analysis. These relative positions will be compared to the
appropriate pre-SM3B baseline data set to allow for a measurement
of any changes in the optical distortions and or plate scale in a
given FGS. Furthermore, by using identical, astrometric guide
stars in the pre and post SM3B visits, the FGS-FGS alignments can
be assessed for changes.
The S-curve morphology and amplitude in each FGS will be obtained
by observing the standard star Upgren69 in Transfer Mode. These
data will be compared to pre-SM3B baseline data. The test in each
FGS will be a single orbit visit. If there are changes to the
distortion, alignment, or S-curve morphology and amplitude that
are sufficiently large to compromise the reliability of guide
star acquisition and/or telescope pointing performance under FGS
control, the appropriate contingency calibration proposal shall
be executed.
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IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: For the pre-SM3B observations there are no
dependencies. For the post-SM3B observations the guide star
acquisition test must succeed (FGS/OTA-01).
DURATION: 12 external HST orbits (6 pre-SM3B, 6 post-SM3B)
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: N/A
COMMENTS: Note, these are non-BEA observations.
AUTHOR/TELEPHONE/EMAIL/DATE:
Ed Nelan / 410-338-4992 / nelan@stsci.edu / 18-Jan-2000
2-18
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2.4.3
ID:
FGS Mini-OFAD
FGS/OTA-03
APPLICABLE SMOV REQUIREMENT: J.10.4.7.2.2
DESCRIPTION: If necessary, as indicated by the results of
FGS/OTA-02, the optical field angle distortion (OFAD) will be recalibrated for a given FGS. The appropriate onboard flight
software tables and PDB shall be updated as necessary.
The OFAD will be recalibrated in a given FGS by observing
selected stars from the standard astrometric star cluster M35 at
a variety of telescope pointings and ORIENTS. The apparent
changes in the relative angular positions of the stars as
function of telescope orientation and translation shall be used
the recompute the OFAD in that FGS. For a given FGS, the
operational OFAD calibration will require 5 HST orbits.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: FGS/OTA-02
DURATION: 5 HST orbits per FGS.
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: N/A
COMMENTS: Note that this is a contingency activity only.
AUTHOR/TELEPHONE/EMAIL/DATE:
Ed Nelan / 410-338-4992 / nelan@stsci.edu / 18-Jan-2000
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2.4.4
ID:
FGS-to-FGS Alignment
FGS/OTA-04
APPLICABLE SMOV REQUIREMENT: J.10.4.7.2.3
DESCRIPTION: If necessary, as indicated by the results of
FGS/OTA-02, the FGS-FGS alignment calibration shall be performed
and the appropriate alignment matrices will be computed. Onboard
tables and the PDB shall be updated with the new calibration
parameters.
The FGS-FGS alignment calibration for a given FGS shall be
determined by observing, with that FGS, selected stars in the
standard astrometric star cluster M35 in Position Mode with the
telescope's V1 pointing and orient held fixed. The stars will be
distributed across the FGS field of view. The alignment of this
particular FGS with respect to the others
will be determined by
using specific, astrometric guide star pairs in the guiding FGSs.
The calibration for a given FGS shall require 4 HST orbits. The
V1 pointing and orientation will remain fixed, but different
guide star pairs will be used for each orbit. These "lever arms"
from the FGS being calibrated to the guide star positions will be
used to determine the FGS-FGS alignment.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: FGS/OTA-02
DURATION: 4 HST orbits per FGS.
DATA REQUIREMENTS: N/A
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ANALYSES & RESULTS: N/A
COMMENTS: Note that this is a contingency activity only.
AUTHOR/TELEPHONE/EMAIL: Ed Nelan/410-338-4992/nelan@stsci.edu
DATE: January 18, 2000
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2.4.5
ID:
FGS K-Factor Determination
FGS/OTA-05
APPLICABLE SMOV REQUIREMENT: J.10.4.7.2.4
DESCRIPTION: If necessary, as indicated by the results of
FGS/OTA-02, the S-curves in a given FGS will be obtained at 5
locations in the FOV. These data will be used to update the FGS
commanding database so that appropriate K-factor values used for
the acquisition and tracking of guide stars can be computed. The
standard star Upgren69 will be observed at the standard "5 points
of light" positions in the FGS (these correspond to the -45, -22,
0, +22, +45 degree azimuthal position along the FGS centerline).
The S-curves will be obtained in both the F583W filter and the
2/3 PUPIL. The 2/3 PUPIL data will be used to recompute the
optimal values of the guide star acquisition parameters K1X, K1Y,
K3X, K3Y, KZ, and KB. These values will be used to update the FGS
commanding database.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: FGS/OTA-02
DURATION: 5 HST orbits per FGS.
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: N/A
COMMENTS: Note that this is a contingency activity only.
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AUTHOR/TELEPHONE/EMAIL:
Ed Nelan 410-338-4992 /nelan@stsci.edu
DATE: January 18, 2000
2-23
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2.4.6
ID:
FGS Jitter Test
FGS/OTA-06
APPLICABLE SMOV REQUIREMENT: J.10.4.7.2.5
DESCRIPTION: The FGSs will be used to measure the jitter
experience by HST during the operation of the NCS.
The Astrometer FGS1r will be used to observe selected stars in
both Position Mode and Transfer Mode. These measurements are to
be obtained after SM3B, but both before and during NCS operation.
The before/after data sets will be compared to determine the
affect, if any, of the NCS on HST pointing performance and jitter
characteristics. The test will consist of two identical single
orbit visits, one to execute before NCS turn on (but after SM3B),
and the second to execute while NCS is operating under steady
state.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: FGS/OTA-01
DURATION: 2 HST orbits, one to execute pre-NCS turn on, one
to execute with NCS in steady state (cold).
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: N/A
COMMENTS: N/A
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AUTHOR/TELEPHONE/EMAIL:
Ed Nelan 410-338-4992 /nelan@stsci.edu
DATE: January 18, 2000
2-25
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2.4.7
ID:
FGS Astrometer Calibration Verification
FGS/OTA-07
APPLICABLE SMOV REQUIREMENT: J.10.4.7.3.1
DESCRIPTION: The photometric response, distortions, plate scale,
and S-curve morphology and amplitude will be measured in the
Astrometer FGS. These data will be used to recertify the
Astrometer for scientific observations.
The Astrometer FGS will be used to observe selected stars in
Position Mode in the standard astrometric star cluster M35 to
measure their relative angular positions. The data will be
compared to an identical data set (same V1 pointing and telescope
ORIENT) obtained before SM3B. If the changes in distortions and
plate scale are within the astrometry error budget than the
Astrometer will be certified to resume scientific observations in
Position Mode.
The Astrometer FGS will be used to observe the standard star
Upgren69 in Transfer Mode with the F583W filter to evaluate the
changes, if any, of the S-curve morphology and amplitude as a
result of SM3B, by comparing the new observations to similar data
acquired before SM3B. If the changes are sufficiently small,
i.e., no greater than what is typically seen over comparable time
periods, the Astrometer will be certified to resume scientific
observations in Transfer Mode.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: FGS/OTA-01
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DURATION: These data will be acquired by the activities
associated with FGS/OTA-02, so no additional HST orbits will be
required.
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: N/A
COMMENTS: For the post BEA observations. the execution of the
guide star acquisition test must be successful.
AUTHOR/TELEPHONE/EMAIL: Ed Nelan 410-338-4992 /nelan@stsci.edu
DATE: January 18, 2000
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2.5
POINTING CONTROL SUBSYSTEM
Table 2-4 shows the verification activities that must be accomplished
during SMOV to verify the performance of the Pointing Control System
to support normal science operations.
Table 2-4
Pointing Control Subsystem SMOV Activities
Activity
Observatory
Summary #
Verification Activity
Execution
Phase
Duration
Hr:min
PCS-01
FHST Field of View Check
Real-Time
03:00
PCS-02
First Attitude Determination
Real-Time
06:00
(Initial Gyro Drift Rate Bias
Determination)
PCS-03
Attitude Initialization
Real-Time
01:00
PCS-04
FHST/FHST Alignment
Real-Time
31:00
PCS-05
RGA Polarity Check
SMS
03:00
PCS-06
Gyro/FHST Alignment
SMS
56:00
PCS-07
FHST/FGS Alignment
SMS
75:00
PCS-08
Vehicle Disturbance Test (VDT)
SMS
27:00
PCS-09
Transfer Function Test (TFT)
SMS
29:00
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2.5.1
FHST Field of View Check
ID: PCS-01
APPLICABLE REQUIREMENT: Preliminary to J.10.4.8.1 and J.10.4.8.2.
DESCRIPTION: The proper mapping of all three FHSTs must be verified to
ensure the success of all subsequent PCS Verification activities. The
FHSTs will be commanded to perform maps of their full FOV and the
observations will be examined for adequacy to support subsequent
activities.
HOW THE ACTIVITY IS BEST IMPLEMENTED: R/T COMMAND
DEPENDENCIES: FHSTs powered on.
DURATION: Three hours.
RESULTS: Verification that the FHSTs are mapping successfully and that
a sufficient number of observations have been obtained from each FHST
to support subsequent attitude determinations and calibrations.
ANALYSIS: Data will be processed through the SAC Fine Attitude
Determination application. Observations will be plotted on FOV grid
and the stars will be identified. The attitude results and statistics
will be evaluated. At least two FHSTs must be successfully mapping in
order to continue to initialize gyro drift rate bias determination.
COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Martin Gakenheimer/HTSI/301-901-6054/
mgakenheimer@hst.nasa.gov
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DATE:
January 3, 2001
2-30
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2.5.2
First Attitude Determination and Initial Gyro Drift Rate Bias
Determination
ID:
PCS-02
APPLICABLE REQUIREMENT: J.10.4.8.2.
DESCRIPTION: The purpose of this activity is to compute the initial
high and low mode gyro drift rate biases.
During this activity the
S/C is in normal mode maintaining a constant attitude.
The FHST maps
are used to measure the vehicle attitude drift due to the
uncompensated gyro drift rate bias. There will be three FHST map
periods, with the gyro mode switched from high to low in the middle of
the second map period. Observations from the first and second periods
will be used to measure the high mode gyro bias, and observations from
the second and third periods will be used to measure the low mode
bias. The new gyro drift biases will be uplinked to the Spacecraft.
HOW THE ACTIVITY IS BEST IMPLEMENTED: R/T COMMAND
DEPENDENCIES: Coarse attitude are determined.
FHSTs are turned on.
FHST FOV check is successful.
DURATION: Six hours. Three hours for the mapping, and three hours for
the data processing, data validation, and Table load generation.
RESULTS: High and low mode gyro drift rate bias Table Loads will be
generated and uplinked to the vehicle. The uncompensated gyro drift
rate bias should be reduced to less than .05 arcseconds per second.
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ANALYSIS: The RGA Calibration application with the Long Baseline Bias
(LBBIAS) option will be used to compute the initial high and low mode
gyro drift rate biases. The fine attitude results and statistics will
be quality assured. The gyro bias change results will be compared to
the expected changes. The ground system will be updated with the new
gyro drift rate biases in order to proceed to the attitude
initialization and return to normal operations.
COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Martin Gakenheimer/HTSI/301-901-6054/
mgakenheimer@hst.nasa.gov
DATE:
January 3, 2001
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2.5.3
ID:
Attitude Initialization
PCS-03
APPLICABLE REQUIREMENT: J.10.4.8.1.
DESCRIPTION: Compute a Fine Attitude using FHST map data and use the
result to update the on-board quaternion, QCI. This is needed in
preparation for transition to normal operations.
HOW THE ACTIVITY IS BEST IMPLEMENTED: R/T COMMAND
DEPENDENCIES: FHST FOV check completed successfully. High and low mode
gyro biases have been uplinked to the vehicle.
DURATION: One hour.
RESULTS: Attitude Reference Update to vehicle. Planned real-time slew
to desired attitude. The vehicle will be within .2 degrees of the
desired attitude to allow communication via the HGAs, and return to
normal operations.
ANALYSIS: Any planned real time slew is constraint checked by the
Interactive Pointing Control System program.
Coarse attitude results
will be used to initialize the Fine Attitude processing.
COMMENTS: Forward link needed to send ARU/PRT to vehicle.
AUTHOR/ORG/TEL #/E-MAIL:
Ed Kimmer/ATSC/ (301) 901-6179/
ekimmer@hst.nasa.gov
DATE:
April 19, 1999
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2.5.4
ID:
FHST/FHST Alignment
PCS-04
APPLICABLE REQUIREMENT: J.10.4.8.3.
DESCRIPTION: Verify that the FHST/FHST alignment has not changed
following the Servicing Mission. The vehicle will be at a constant
attitude, and each pair of FHSTs will be commanded to perform a map of
the full field of view. An FHST/FHST alignment will be computed and
compared to the pre-Servicing Mission alignment. The FHST maps will be
repeated as a backup to the first set.
HOW THE ACTIVITY IS BEST IMPLEMENTED: R/T COMMAND
DEPENDENCIES: Vehicle under normal operations.
Accurate gyro biases
uplinked to vehicle.
DURATION: Seven hours of data collection and 24 hours of data
processing and analysis.
RESULTS: FHST/FHST alignment table loads may be uplinked to the
vehicle if the boresight separation between any pair of FHSTs has
changed by more than 20 arcseconds.
ANALYSIS: The data will be prepared by running the SAC Fine Attitude
program to compute attitudes from the FHST map data. The prepared data
will be processed by the SAC FALIGN program to compute an FHST/FHST
alignment with FHST 1 as the reference tracker.
The application
reports the change to the boresight separation for each pair of
trackers.
If necessary an alignment will be written to a calibration
file, and the ground system will be updated with the new alignment.
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COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Ed Kimmer/ATSC/ (301) 901-6179/
ekimmer@hst.nasa.gov
DATE:
April 19, 1999
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2.5.5
ID:
RGA Polarity Check
PCS-05
APPLICABLE REQUIREMENT: Contingent on the replacement of one or more
of the RSUs.
Preparation work for J.10.4.8.4.
DESCRIPTION: In order to confirm the RGA polarity a positive and
negative 1 degree slew will be executed about each vehicle axis. The
FHSTs will be mapping throughout this period and will be used as a
reference.
HOW THE ACTIVITY IS BEST IMPLEMENTED: R/T COMMAND
DEPENDENCIES: FHSTs able to perform mapping.
DURATION: 3 hours.
RESULTS: Verification that the RGAs are sensing vehicle motion with
the correct polarity.
ANALYSIS: Data will be processed through the PASS Fine Attitude
Determination application. The attitude before and after each slew
will be computed and the attitude change will be compared to the
commanded slew.
COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Martin Gakenheimer/HTSI/301-901-6054/
mgakenheimer@hst.nasa.gov
DATE:
May 3, 1999
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2.5.6
ID:
Gyro/FHST Alignment
PCS-06
APPLICABLE REQUIREMENT: J.10.4.8.4.
Contingent on the replacement of
one or more of the RSUs.
DESCRIPTION: This activity is performed to compute the alignment of
the gyros to the FHSTs. The scale factors and high mode bias are also
determined. The purpose is to reduce the attitude errors after large
maneuvers to less than one arcsecond per degree of slew. Six maneuvers
are executed that allow measurements to be obtained along each of the
gyro input axes. Before and after each maneuver the FHSTs are
commanded to execute a map of the full field of view.
Attitude
changes computed from the FHST data are compared to attitude changes
derived from the gyro data in order to solve for the RGA/FHST scale
factor/alignment matrix and the gyro biases. A follow-up set of six
maneuvers is executed to verify the alignment results after they have
been uplinked to the vehicle.
HOW THE ACTIVITY IS BEST IMPLEMENTED: SMS Proposal.
DEPENDENCIES: FHST/FHST alignment must be verified, or updated if it
has changed. The high mode gyro bias should be updated as close as
possible to the start of this activity.
No significant data gaps can
exist. Preferably implement this activity with gyros in high mode.
DURATION: About 56 hours. The maneuvers require about 8 hours to
execute. Approximately 24 hours are required to process the data and
generate table loads. Another 8 hours are required for the
verification slews and about 16 hours to process the data.
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RESULTS: RGA/FHST scale factor/alignment and gyro bias Table loads for
uplink to the vehicle.
Following this calibration attitude errors
after a large maneuver are sufficiently small to allow FHST updates to
remove them.
ANALYSIS: The data is prepared in the SAC Fine Attitude application.
Attitudes are computed before and after each maneuver using FHST
observations. An attitude change is computed by integrating gyro data
for the maneuver period. The prepared data is processed by the SAC RGA
Calibration program. The ground system is updated with the new
alignments allowing for successful FHST updates.
COMMENTS: None
AUTHOR/ORG/TEL #/E-MAIL:
Ed Kimmer/ATSC/ (301) 901-6179/
ekimmer@hst.nasa.gov
DATE:
April 19, 1999
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2.5.7
ID:
FHST/FGS Alignment
PCS-07
APPLICABLE REQUIREMENT: J.10.4.8.5.
This is a Contingency Activity.
DESCRIPTION: The purpose of this activity is to align the FHSTs to the
FGS system. This will allow computation of accurate attitudes for FHST
updates following maneuvers, and for vehicle Attitude Reference
Updates. FGS 3 will map out its field of view using coarse track
astrometry observations. Comparing observed star positions to a
catalog, SAC will compute the vehicle attitude and the FHST/FGS
alignments.
(This is an abbreviated pattern match).
HOW THE ACTIVITY IS BEST IMPLEMENTED: SMS Proposal.
DEPENDENCIES: Gyro/FHST alignment.
DURATION: The data take requires approximately 3 hours and the
subsequent data processing requires about 48 hours. An additional 24
hours is needed by SACOPS personnel to update calibration files to be
used for future SMS processing.
RESULTS: FHST/FGS and modified RGA table loads for uplink to the
vehicle.
This will allow for successful guide star acquisitions to be
achieved. This is a contingency activity that will be implemented if
guide star acquisitions are not successful and FHST to FGS alignment
miscalibration is the cause.
ANALYSIS: None
COMMENTS: None
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AUTHOR/ORG/TEL #/E-MAIL:
Ed Kimmer/ATSC/ (301) 901-6179/
ekimmer@hst.nasa.gov
DATE:
April 19, 1999
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2.5.8
ID:
Vehicle Disturbance Test (VDT)
PCS-08
APPLICABLE REQUIREMENT: J.10.4.8.7
DESCRIPTION: The purpose of the VDT is to characterize
uncompensated environmental disturbances acting upon the HST
during normal operation.
The VDT is a passive test (not a
forced-response test) used to obtain signatures for both
externally induced (e.g. SA-3) and internally induced (e.g. NCC)
disturbances for comparison with past VDT results.
The
disturbances observed will be used as the nominal on-orbit
disturbances in pointing control simulations until the next VDT
is run.
The test occurs after release, and most of the VDT can be run
during the BEA period.
The –V1 sunpoint portion of the VDT
occurs after the BEA period is complete.
The VDT shall consist
of five separate tests that need not occur consecutively.
The
overall duration of the VDT tests is at least 17 orbits of
spacecraft time including (1) at least 1 full orbit at +V3
sunpoint prior to NCC operation while performing ACS Filter Wheel
moves simulating routine flight operations, (2) at least 5 full
orbits at +V3 sunpoint prior to NCC operation, (3) at least 1
full orbit at +V3 sunpoint during NCC startup, (4) at least 5
full orbits at +V3 sunpoint while NCC is operating at steadystate, and (5) at least 5 full orbits at –V1 sunpoint with the
NCC operating at steady-state.
At the beginning of each test,
the attitude control law gains are switched to maneuver gains,
and the gyros are commanded to low mode.
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control law configuration will be restored at the end of each
test.
HOW THE ACTIVITY IS BEST IMPLEMENTED: Stored Program Command and
SMS
DEPENDENCIES: PN Format, vehicle in gyro hold, gyros in low mode,
SAGA filter off, attitude control law maneuver gains (low
bandwidth controller), and two different solar array angles are
used.
VAP processing shall remain off during VDT intervals, and
no vehicle slews shall be scheduled during VDT test intervals
that may turn-on VAP processing.
Forward link opportunities
shall be provided after planned vehicle slews to disable VAP
processing prior to VDT tests.
At the end of each test, SMS
scheduled null slews and full maneuver attitude updates shall be
performed to re-enable VAP processing and to correct attitude
errors prior to subsequent science operations.
FHST maps shall
be scheduled in the SMS during the VDT for monitoring vehicle
attitude.
Continuous SSR data recording shall occur during test
intervals.
DURATION: Seventeen orbits: 12 orbits at +V3 sunpoint with 90degree solar array angle, and 5 orbits at –V1 sunpoint with 0degree solar array angle.
RESULTS: Verify that the HST is in the prescribed configuration
during the test, and confirm that external disturbances are being
measured by monitoring gyro count mnemonics and control law
position path mnemonics.
ANALYSIS: Data will be processed by the Pointing Control System
group.
Disturbances occurring during this test will be
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classified by source item and characterized for comparison to
previously measured disturbances.
Results and observations will
be documented in a final report within four months of the
servicing mission.
COMMENTS: It is preferable to have a 2-guide star FGS acquisition
(with no moving target maneuvers) prior to each VDT interval to
ensure that a fresh gyro bias is available (OBSINT method) before
the test begins.
This ensures that minimal attitude drift occurs
during the extended gyro hold intervals required by the test.
AUTHOR/ORG/TEL #/E-MAIL:
Brian Clapp/LMTO/(301) 901-
6062/brian.clapp@lmco.com
DATE:
January 8, 2001
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2.5.9
ID:
Transfer Function Test (TFT)
PCS-09
APPLICABLE REQUIREMENT: J.10.4.8.8.
DESCRIPTION: Contingent upon analysis of PCS performance postSM3B, perform a Transfer Function Test (TFT).
The TFT is a
forced response test that measures HST system modal parameters
(modal gains, modal damping ratios and frequencies) by applying a
RWA forcing function and measuring RGA gyro response.
This test
will be performed if PCS analysis of post-SM3B HST flight data
(such as the VDT) suggests that HST system modal parameters
significantly differ from pre-SM3B analytical models.
On-orbit
modal parameters that differ from pre-SM3B models can cause
degraded performance of the HST attitude control system because
of reductions in stability margins and/or increased vehicle
jitter.
The test occurs after release and after the Vehicle Disturbance
Test is complete.
The overall duration of the TFT is
approximately 18 orbits (contiguous) of spacecraft time that
includes nine orbits in the +V3 sunpoint orientation and nine
orbits at –V1 sunpoint.
While in each orientation, three orbits
will be allocated for applying forcing functions about each of
the three vehicle axes.
Forced response of the HST is required
at two different vehicle attitudes because HST modal parameters
are a function of solar array angle.
At the beginning of the
test, Stored Program Commands are activated to establish
“modified PN Format” telemetry, to switch the attitude control
law to the maneuver gain set, and to command the gyros to low
mode.
The nominal telemetry format and attitude control law
configuration will be restored at the end of the test.
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HOW THE ACTIVITY IS BEST IMPLEMENTED: Stored Program Command and
SMS
DEPENDENCIES: If performed, the TFT shall occur at least 24-hours
after completion of the Vehicle Disturbance Test.
The NCC
shall either be off or operating at steady state temperature (out
of surge).
Modified PN Format, vehicle in gyro hold, gyros in
low mode, SAGA filter off, attitude control law maneuver gains
(low bandwidth controller), and two different solar array angles
are used.
VAP processing shall remain off during the TFT, and no
vehicle slews shall be scheduled during the TFT that may turn-on
VAP processing.
Forward link opportunities shall be provided
after planned vehicle slews to disable VAP processing prior to
resuming TFT tests.
At the end of the test, SMS scheduled null
slews and full maneuver attitude updates shall be performed to
enable VAP processing and to correct attitude errors prior to
subsequent science operations.
FHST maps shall be scheduled in
the SMS during the TFT for monitoring vehicle attitude.
Continuous SSR data recording shall occur during test intervals.
DURATION: Eighteen orbits: 9 orbits at +V3 sunpoint with 90degree solar array angle, and 9 orbits at –V1 sunpoint with 0degree solar array angle.
RESULTS: Verify that the HST is in the prescribed configuration
during the test, and confirm that the commanded torque forcing
functions are being applied to the vehicle by monitoring
telemetry.
Verify that the gyro measured vehicle response is
consistent with pre-test simulation results.
If possible,
provide near-real time processing of telemetry for quick-look
transfer function results.
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ANALYSIS: Data will be processed by the Pointing Control System
and Safing groups.
On-orbit modal parameters will be extracted
using standard modal processing methods.
Results and
observations will be documented in a final report within four
months of the servicing mission.
COMMENTS: It is preferable to have a 2-guide star FGS acquisition
(with no moving target maneuvers) prior to the TFT to ensure that
a fresh gyro bias is available (OBSINT method) before the test
begins.
This ensures that minimal attitude drift occurs during
the extended gyro hold intervals required by the test.
AUTHOR/ORG/TELEPHONE/E-MAIL:
Brian Clapp/LMTO/(301) 901-
6062/brian.clapp@lmco.com
DATE:
January 8, 2001
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2.6
ADVANCED CAMERA for SURVEYS
Table 2-5 shows the verification activities that must be accomplished
during SMOV to verify the performance of the Advanced Camera for
Surveys (ACS) to support normal science operations.
Table 2-5
ACS SMOV Activities
Activity
Observatory
Summary #
Verification Activity
Execution Duration
Phase
Hr:min
ACS-02
Load and Dump On-Board Memory
R/T
00:20
ACS-03
Science Data Buffer Check
R/T
12:00
ACS-05
CCD Functional
SMS
22:50
ACS-06
CCD Temperature Set Point
R/T
N/A
Determination
ACS-08
ACS SBC Anomalous Recovery Test
R/T
03:00
ACS-10
SMOV Contamination Monitoring
SMS
04:30
ACS-11
ACS to FGS Alignment
SMS
03:00
ACS-12
HRC Coronagraph Acquisition
SMS
04:30
ACS-13
Coarse Corrector Alignment
SMS
09:00
ACS-14
Fine Corrector Alignment
SMS
21:00
ACS-15
Image Quality & PSF Measurement
SMS
06:00
ACS-16
HRC Coronagraph Repeatability
SMS
06:00
ACS-17
Image Stability Verification
SMS
24:00
ACS-18
CCD & SBC Flat Fielding Stability
SMS
36:00
ACS-20
ACS Sensitivity
SMS
24:00
ACS-21
SBC Detector Mini-Functional
SMS
00:10
ACS-22
SBC Dark Rate Measurement
SMS
10:30
ACS-23
SBC Image Qual. & PSF Measurement
SMS
04:30
ACS-25
Scat. Light in Coronagraphic Obs.
SMS
07:30
ACS-26
Ramp Filter Test
SMS
06:00
ACS-27
CCD & SBC Geometric Distortion
SMS
09:00
ACS-29
Grism/Prism Performance Check
SMS
09:00
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Table 2-5 (Continued)
ACS SMOV Activities
Activity
Summary #
Observatory
Verification Activity
Execution Duration
Phase
Hr:min
ACS-31
CCD Hot Pixel Annealing
SMS
28:00
ACS-32
CCD Flash Verification
SMS
04:00
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2.6.1 Load and Dump On-Board Memory.
ID:
ACS-02
APPLICABLE REQUIREMENTS: J.10.4.3.1.4
DESCRIPTION: This activity is a test and verification of the ACS
dump of CS memory capability. Areas to dump include: EEPROM,
PROM, EDAC RAM, and Buffer RAM with the CS in OPERATE mode.
With the MAMA Interface Electronics (MIE) and CS both in OPERATE,
perform a full dump of the Control Section's (CS) EEPROM, PROM,
and EDAC RAM. Then copy MIE data from MIE RAM and MIE PROM to CS
Buffer RAM. Finally, dump the portion of the CS Buffer RAM
containing the data as normal science images. (Note: The
remainder of CS Buffer RAM is checked in another proposal.)
IMPLEMENTATION METHOD: Special commanding
DEPENDENCIES: N/A
DURATION: 20 min
DATA REQUIREMENTS: 8 MB
ANALYSES AND RESULTS: Analysis of the CS and MIE memory data dump
images produced in this visit will have to be coordinated with
Michelle Troeltzsch at GSFC Code 582 who will have the necessary
ground images for comparison with the memory dump images.
COMMENTS: This proposal requires special commanding to execute.
When executed, Michelle Troeltzsch at GSFC/Code 582 should be
contacted to analyze the dump data.
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AUTHOR/TELEPHONE/EMAIL: Vicki Balzano/4736/balzano@stsci.edu
DATE: November 9, 2000
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2.6.2 Science Data Buffer Check
ID:
ACS-03
APPLICABLE REQUIREMENTS: J.10.4.1.5
DESCRIPTION: The ACS Science Buffer RAM is checked for bit flips
during SAA passages. This is followed by a Control Section (CS)
self-test consisting of writing/reading a specified bit pattern
from each memory location in Buffer RAM and a similar test for
MIE RAM. The MIE must be placed in BOOT mode for its self-test.
The CS Buffer RAM self-test as well as the bit flip tests are all
done with the CS in Operate.
Using the set buffer memory macro, write zeros into CS Buffer RAM
prior to passage into the SAA and then dump buffer memory to SSR
after exit from the SAA to check for bit flips. This Buffer RAM
check should be executed several times, both inside and outside
the SAA. Then use the CS self test macro to conduct a pattern
test of CS Buffer RAM and check the memory fail counter after the
test has completed. Repeat for a similar MIE self test. The MIE
will need to be in BOOT mode for its self-test.
IMPLEMENTATION METHOD: Special commanding
DEPENDENCIES: N/A
DURATION: 8 orbits, none of which pointed (always internal
darks).
DATA REQUIREMENTS: 132 MB
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ANALYSES AND RESULTS: If at the end of the CS buffer test, any of
the Results Tables are non-zero entries, a status buffer message
(931) with the number of
errors generated will be issued by the
FSW. If this occurs, contact Michelle
Troeltzsch at GSFC/Code
582 for further analysis.
COMMENTS: This proposal requires Special Commanding to execute
and the MIE to be in BOOT mode for the MIE self-test. For both
the CS and MIE self-tests, a memory monitor must be set to check
the results of the tests. The CS tests are done in OPERATE so
that CS paging is enabled and all 34 megabytes of memory are
available for testing.
AUTHOR/TELEPHONE/EMAIL: Vicki Balzano / 4736 / balzano@stsci.edu
DATE: November 9, 2000
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2.6.3 CCD Functional
ID:
ACS-05
APPLICABLE REQUIREMENTS: J.10.4.3.1.7, J.10.4.3.1.8, J.10.4.3.4.2
DESCRIPTION: (1) Measure baseline performance and commandability
of CCD subsystems using exposures of bias frames, darks, and flat
fields with the tungsten lamps. HRC: 68 Biases, 8 Darks, 8 Flat
fields; WFC: 29 Biases, 8 Darks, 8 Flats (Full), 8 Flats (subarray).
(2) Parallel and serial EPER and FPR will be measured in WFC and
HRC. EPER and FPR CTE data will be collected at 17 (WFC) and 18
(HRC) signal levels with three repeats at each signal level. The
proposal calls for a sequence of exposures with increasing
integration times that will be used
function of
signal level.
to measure CTE
as a
Crossed filter elements, a
configuration prohibited for science observations, are necessary
for the WFC exposures at the lowest signal levels. A total of 75
trailing serial over-scan pixel and 75 virtual over-scan rows are
readout in each EPER exposure. A short dark frame is taken with
the same timing pattern used for the exposure at the beginning
and at the end of each visit. Pointed observatory time is not
required for the measurements.
All data is acquired using the
internal tungsten calibration lamp(s).
(3) Measure baseline performance of the on-board compression
algorithm for WFC data.
Procedure is carried out purely with
internal targets - 4 Biases and 4 Darks. Observations do not need
to be contiguous.
(4) Routine Monitor: This program will be executed once a day to
monitor the read noise, the development of hot pixels and to test
for any level source of noise.
For each CCD at the default gain
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setting and read out configuration we will obtain 1 bias, 1 short
dark (60 s), 1 long dark (960s), and 1 short dark (60 s). The
procedure is carried out purely with internal targets. The
exposures do not need to be contiguous.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: ACS06 CCD temperature set point determination.
DURATION: Note. No external targets are required.
(1) 10.4 hrs
(2) 22.5 hrs
(3) 87 m
(4) 66 m per day
DATA REQUIREMENTS: (1) 84 full HRC frames (178 MB), 45 full WFC
frames (1472 MB) and 8 WFC sub-arrays (17 MB) will be downloaded.
(2) 168 full HRC frames (356.1 MB) and 110 full WFC frames
(3598.1 MB)
will be down-loaded.
(3) 8 full WFC frames (261.7 MB) will be down-loaded.
(4) 4 full HRC frames (8.48 MB) and 4 full WFC frames (130.84 MB)
will be down-loaded daily.
ANALYSES AND RESULTS: (1) Provide baseline measurements of
levels and readout noise values for
measurements
of average dark rate
of dark rate values
all 4
bias
amplifiers,
(e-/pix/sec) and histogram
per pixel, gain conversion factors and sub-
array readout performance. After cleaning for cosmic rays,
average bias frames will be determined for the 4 quadrant mode
and for single amp readout.
The difference between pairs of
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bias frames will be
used to determine the
read noise.
of the dark frames will be used to derive the dark
The sum
image,
average rates, dark histograms, and hot pixel position.
Relative
gain calibration will be derived by comparing signal levels from
the flat
field images at different gain settings.
(2) Dedicated software is already available to reduce both EPER
and FPR data for HRC and WFC CCD. We will determine a baseline
for monitoring of the effects of radiation damage.
(3) We will measure the baseline performance of the on-board
compression algorithm for WFC data.
(4) We will use the observations to measure the basic performance
of the detectors on a daily basis. We will identify hot pixels
for the calibration pipeline.
COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Marco Sirianni - Mark Clampin / 410-5160779 - 410-338-4177
/ sirianni@pha.jhu.edu - clampin@stsci.edu
DATE: December 12, 2000
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2.6.4
ID:
CCD Temperature Set Point Determination
ACS-06
APPLICABLE REQUIREMENTS: J.10.4.3.1.9
DESCRIPTION: Command the CCD temperature set point to
successively lower temperatures, starting at -TDB C and
decreasing by TBD degrees each time.
At each commanded
temperature, monitor engineering telemetry of CCD temperature
diode reading for 24 hour. Assess the stability of that
temperature over the 24 hour period, looking for orbital or
longer-term variations. Stop going colder when the temperature is
no longer controlled to a stability better than 1 degree peak-topeak.
IMPLEMENTATION METHOD: the set point shall be adjusted via
"engineering only" commanding at pre-planned times. No real-time
adjustments are required.
DEPENDENCIES: None
DURATION: 4 - 5 days
DATA REQUIREMENTS: None
ANALYSES AND RESULTS: Plot engineering telemetry readings of CCD
temperature sense diode and assess the stability of the
temperature control at each setting. Choose as the set point the
lowest temperature at which control to better than 1 C variation
(peak-to-peak) is achieved.
Command that set point and leave it
as long as no degradation in temperature stability is observed.
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COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Marco Sirianni - Mark Clampin / 410-5160779 - 410-338-4177 / sirianni@pha.jhu.edu - clampin@stsci.edu
DATE: December 12, 2000
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2.6.5
ID:
ACS SBC Anomalous Recovery Test
ACS-08
APPLICABLE REQUIREMENTS: J.10.4.3.1.8
DESCRIPTION: This procedure will be used for the initial turn-on
of the ACS MAMA detector and for recovery after an anomalous
shutdown, as might result from a bright object violation or
hardware problem.
The test is in three stages with all voltages returned to zero
between stages. Beginning with all voltages off, first the low
voltage is turned on and the amplifier thresholds set to a lower
than normal value of 0.28V which allows noise counts to be
measured to prove basic operation of the electronics.
For the second stage, thresholds are set to their normal 0.48V,
the low voltage is turned on and the Global Monitor set to turn
the MAMA off if the count rate becomes dangerously high. The high
voltage is advanced in 50V stages up to 2000V (300V less than the
normal operating value), with counts being monitored at each
stage. The field voltage is ramped up to 100V and a 720 second
MAMA dark image taken.
Stage 3 is a full ramp up to 2300V performed in the same manner,
followed by ramping up the field voltage to its normal 1000V.
Another 720 second dark image is taken.
IMPLEMENTATION METHOD: The activity requires real-time commanding
and monitoring of count rates. It is a goal to schedule visits
while a TDRSS is visible.
DEPENDENCIES: The MAMA will not be operated within 30 days of the
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servicing mission. (Requirement J.10.4.3.1.11) The MAMA ACS M3
fold mirror will be in the HRC position. Stages 2 and 3 of the
procedure will not be performed within 24 hours of an anomalous
shutdown. Each stage must await satisfactory analysis of the
previous stage before proceeding. Event flag 2 is used to
regulate the commanding. All activities with MAMA high voltage
turned on must be scheduled to avoid SAA passages. If ACS08 is
successful, ACS09. the MAMA Fold Analysis,
should immediately
follow while the high voltage is on.
DURATION: Stage 1 takes 20 minutes and is followed by a 24 hour
waiting period before stage 2. Stage 2 takes 53 minutes and is
followed by another 24 hour
waiting period before stage 3 which
takes 69 minutes. The active period is therefore 162 minutes
spread over slightly more than two days.
DATA REQUIREMENTS: Continuous access to the engineering data is
required.
Two dark images are taken each 2 Megabytes in size.
Data analysis consists of
comparing count rates and dark images
with previous examples.
COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Colin Cox/410-338-4792
DATE: July 25, 2000
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2.6.6
ID:
ACS SMOV Contamination Monitoring
ACS-10
APPLICABLE SMOV REQUIREMENT: J.10.4.3.1.10; J.10.4.3.1.11
DESCRIPTION: This program has two main goals: (1) manage ACS
operations to minimize the risk of contamination of its optics by
materials out-gassed during servicing activity, and (2) initiate
a program to monitor the UV sensitivity of HRC and SBC as early
as possible after the SM. For 4 weeks following the release of
the observatory, during the early period of out-gassing, bright
earth viewing should be limited, and the cal door must be closed
while HST is pointing at the bright earth to protect its optics
from being polymerized by reflected solar UV light. In addition,
during this period there will be no high voltage operation of the
SBC MAMA detector.
The ACS UV sensitivity of the HRC will be monitored using a
standard star twice a week in the first week, once a week for the
first 3 months, and once a month thereafter. The standard should
be chosen to provide 10,000 counts per resolution element in less
than 10 min. through the F220W, F250W and F330W filters of HRC.
The chosen targets are G191B2B (05 05.5 +52 50, fall/winter) and
GD153(12 57 +22 02, spring/summer), both of which are white dwarf
standards that
have been used for the SMOV contamination monitor
with STIS. CCD observations with the HRC shall be performed first
before the MAMA detector on the SBC is turned on.
For the SBC, the globular star cluster NGC 6681 (18.7h -32deg)
will be observed through all five longpass filters (F115LP,
F125LP, F140LP, F150LP, F165LP). This cluster contains several
well-observed stars with STIS, which can be used as photometric
standards to calibrate SBC sensitivity. For contamination
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monitoring purposes, the frequency of observations will be the
same as for the HRC.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS14, ACS Fine Corrector Alignment, must be
successfully completed prior to implementation of ACS10.
DURATION: 3 orbits (1 for HRC and 2 for SBC) per week for the
first 3 months; 3 orbits per month thereafter.
DATA REQUIREMENTS: 12 HRC and 20 SBC images (70 MB) will be downlinked in the first week, 6 HRC and 10 SBC images (35 MB) per
week in the first 3 months, and 6 HRC and 10 SBC images per month
thereafter.
ANALYSIS & RESULTS: Encircled energy and sensitivity (observed
counts/absolute flux) will be derived and compared with the first
measurements. They will be examined as a
wavelength.
function of time and
Verify whether or not the ACS UV sensitivity is
degrading with time.
COMMENTS: Depending on the exact launch date, the choice of NGC
6681, which is unavailable Nov.--Feb., may necessitate a delay in
monitoring the SBC sensitivity. This activity may be combined
with ACS15, 27: SBC Image
Quality, PSF measurement and Geometric
Distortion.
AUTHOR/telephone/email: Hien D. Tran / 410-516-5560 /
tran@pha.jhu.edu
DATE: November 11, 2000
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2.6.7
ID:
ACS to FGS Alignment
ACS-11
APPLICABLE SMOV REQUIREMENT: J.10.4.3.2.1
DESCRIPTION: Mapping of the ACS detector coordinate frame to the
FGS frame will be determined from observations of an astrometric
field with the ACS HRC and WFC detectors. (The equivalent SBC
measurements will be performed as a separate activity relating
the HRC and SBC detector frames.)
Substantial POS-TARG offsets
of the OTA in two orthogonal directions will be performed between
image sets. This activity must be performed after ACS14, Fine
Corrector Alignment, has been successfully completed, and must
precede ACS12, Coronagraph Acquisition Verification. Guide stars
from the astrometric catalog associated with the selected target
field must be used. The recommended target field is NGC 188,
which has been used for the STIS alignment in SMOV2, has a
suitable star density, and (at decl = + 85 deg) is always
available. For this activity, images through only a single filter
are required and only low SNR in a few astrometric stars is
required, such that their image centroids can be determined
within 0.5 px.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS14, Fine Corrector Alignment, must be
successfully completed prior to this activity.
DURATION: 2 orbits
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DATA REQUIREMENTS: 6 WFC full frame images (200 MB) and 6 HRC
images (14MB) will be downlinked.
FGS frame (V2-V3) positions of
the astrometric stars in each field during the observations must
be provided promptly.
Matt Lallo is the expected SISD interface regarding acquisition
of these coordinates, given the astrometric catalog coordinates
of the target field stars and
the guide stars.
ANALYSES & RESULTS: Analysis will consist of determining the
centroid positions of all astrometric stars in each field to
accuracy of <0.5 px and relating those to their FGS frame
positions. Aperture orientations and plate scales from this
analysis will be corroborated with the image position changes
between the POS-TARG offset images. The PDB SIAF aperture
descriptions will be updated for the ACS HRC and WFC, and if the
offsets from current values are significant, the SBC aperture
descriptions may also be adjusted similarly, in advance of SBC
observations. Also, the rotation matrix used by the ACS NSSC-1
FSW to compute target acquisition slews may be updated.
COMMENTS: This activity may be combined with ACS15, ACS Image
Quality and PSF Measurement, using the same target field.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: October 10, 2000
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2.6.8
ID:
HRC Coronagraph Acquisition
ACS-12
APPLICABLE SMOV REQUIREMENTS: J.10.4.3.2.2, J.10.4.3.2.3
DESCRIPTION: This is a two-part activity for the purposes of (1)
determining the relative positions of the coronagraphic field
masks and the "Fastie Finger," and
(2) verifying the ability of
the flight software (FSW) to perform isolated point source
acquisition onto the coronagraphic masks and Fastie Finger.
Successful execution of these acquisitions will also demonstrate
the ability of the FSW to calculate the centroid of the target
positions and to perform automated telescope pointing.
To determine the positions of the coronagraphic masks and Fastie
Finger, good signal-to-noise HRC images of a wide-angle, bright,
diffuse source will be recorded.
Candidate targets are M42
(Orion Nebula; RA = 5 hr) for a Fall/Winter SMOV, M8 (Lagoon
Nebula; RA = 18 hr) for a Spring/Summer SMOV, or Earth during HST
occultation.
The nebular targets will be imaged through F606W;
Earth will be imaged through F334N.
Telescope pointings will be
selected to minimize the number of field stars within the nebulae
that will saturate the detector.
Regardless of target
selection, sufficient signal-to-noise should be obtained within
one orbit.
After determining the locations of the masks and Fastie Finger,
two unsaturated images of an isolated, 4th-5th magnitude solartype (G0-G5 V) star acquired at the nominal HRC aperture will be
recorded through F220W with the coronagraph fully deployed.
(The
star must be non-variable and have no known circumstellar
features or emission.)
The star will then be offset by the FSW
to the center position of the 1.8-arcsec diameter mask.
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images of the occulted star will be recorded through F220W with
exposure times that permit both unsaturated imaging of the
residual diffraction spot at the center of the mask and good
signal-to-noise in the wings of the coronagraphic PSF.
The star
will then be re-acquired at the nominal HRC aperture and another
two unsaturated images recorded.
The FSW will then offset the
star to the center position of the 3.0-arcsec diameter mask.
Two
images of the occulted star will be recorded with an exposure
time that permits good signal-to-noise in the wings of the
coronagraphic PSF.
(Unless the 3.0 arcsec mask and the Fastie
Finger are grossly misaligned, no short exposure of the occulted
star is needed.)
retracted.
The coronagraph mechanism will then be
The star will again be re-acquired at the nominal HRC
aperture and another two unsaturated images recorded.
The FSW
will then offset the star to a location on the Fastie Finger.
Two images of the occulted star will be recorded with an exposure
time that permits good j signal-to-noise in the wings of the
coronagraphic PSF.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS11 (ACS to FGS Alignment) must be successfully
completed prior to this activity.
DURATION: 3 orbits
DATA REQUIREMENTS: 18 HRC images (40 MB) will be down-linked.
Data should be delivered to the archive without delay; subsequent
SMOV observations depend on the coronagraphic mask positions
resulting from this activity.
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ANALYSES & RESULTS: The positions of the coronagraphic masks and
Fastie Finger will be determined from their shadows cast under
quasi-flat field illumination. Pixels with values within 90% of
the minimum transparency of each coronagraphic mask will be
mapped for subsequent stability monitoring.
The ability of the
FSW to position a star behind the 1.8 and 3.0 arcsec masks and
the Fastie Finger will be determined from the centroids of the
star in the acquisition images and from the symmetry of the
scattered light encircling the masks.
For the 1.8 arcsec mask,
the position of the occulted star can be verified from the
residual diffraction spot at the center of the star's image.
(No
such verification can be performed for the 3.0 arcsec mask unless
it is badly misaligned with the Fastie Finger.)
COMMENTS: The first part of this activity (determining the
positions of the coronagraphic masks and Fastie Finger) can be
executed in tandem with ACS16 (HRC Coronagraph Repeatability)
using the same illumination source.
AUTHOR/telephone/email:
David Golimowski / 410-516-6181 /
dag@pha.jhu.edu
DATE: November 2, 2000
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2.6.9
ID:
ACS Coarse Corrector Alignment
ACS-13
APPLICABLE SMOV REQUIREMENT: J.10.4.3.3.1
DESCRIPTION: This activity attempts to nearly optimize the ACS
image quality over the fields of both the WFC and HRC channels by
adjusting the IM1 and M1 corrector mechanisms in both tip/tilt
(cylinder rotation) and focus. These observations of a moderate
density star field constitute the "first light" external images
for the HST/ACS. High SNR images will be obtained through the
F502N narrow band filter to permit accurate phase retrieval
estimates of the residual aberrations. Small focus offsets will
be performed between the 3 images constituting each set, to
remove focus ambiguity. The activity will proceed in three
iterations, with pre-planned uplink opportunities for corrector
mechanism adjustment after each observation. The recommended
target is NGC 188, which (at latitude + 85 deg) is always
available and has a suitable density and magnitude distribution.
IMPLEMENTATION METHOD: Proposal, with pre-planned real-time
uplink of new corrector mechanism positions.
DEPENDENCIES: ACS06, CCD Temperature Set Point Determination,
must be successfully completed prior to implementation of ACS13.
DURATION: 6 orbits. 2 orbits at each of three epochs, with ~24 hr
separation.
DATA REQUIREMENTS: For each of 3 iterations: 6 WFC full frame
images (200 MB) and 6 HRC images (14 MB) will be downlinked. The
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images from each iteration must be available for analysis at
least 18 hr before the planned uplink for corrector adjustment.
ANALYSES & RESULTS: Phase retrieval analysis will be performed
for selected
(isolated, well-exposed) stars throughout the field
to determine the coma and focus wavefront error contributions,
which will be used to determine the corrector offsets in cylinder
rotation and focus travel to optimize the images. The corrective
actions will be computed using special IDL software that has been
developed and successfully used for the ground alignments. The
mechanism offsets will be specified in motor step units, relative
to the current positions, at least 12 h prior to the planned
uplinks for their implementation.
COMMENTS: This activity will also result in an initial estimate
of the ACS aperture positions, orientations and plate scales, in
anticipation of activity ACS11.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: October 5, 2000
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2.6.10
ID:
ACS Fine Corrector Alignment
ACS-14
APPLICABLE SMOV REQUIREMENT: J.10.4.3.3.1
DESCRIPTION: This activity refines the WFC and HRC corrector
alignments in order to optimize image quality over their
respective fields. Two visits are required, the first to perform
a fine focus scan, and the second to perform a tip and tilt scan,
after the optimal focus has been set. The same target field,
filters and exposure times as in activity ACS13 will be used.
The focus scan will comprise 7 positions, with 250 (WFC) or 150
(HRC) step offsets between them, and centered about the best
positions found in ACS13.
Tip/tilt scans will be in +/- 3 step
offsets in a 3x3 grid about the positions resulting from ACS13.
Each scan will terminate at the initial position.
Image (CR-
split) pairs will be obtained at each scan position.
IMPLEMENTATION METHOD: Proposal, with real-time uplink of optimal
focus positions prior to tip/tilt scan and of optimal cylinder
positions after the second visit (and prior to activity ACS15,
ACS Image Quality and PSF Measurement).
DEPENDENCIES: ACS13, ACS Coarse Corrector Alignment must be
successfully completed prior to implementation of ACS14.
DURATION: 14 orbits; 7 orbits for each visit.
DATA REQUIREMENTS: For visit 1, 16 WFC images (530 MB) and 16 HRC
images (34 MB) will be downlinked.
For visit 2, 20 WFC images
(660MB) and 20 HRC images (42 MB) will be downlinked. The
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complete set of images from each visit must be available 24 h
prior to the scheduled uplink for the corrector offsets.
ANALYSES & RESULTS: Encircled energy, peak fraction and FWHM
analysis will be performed for a subset of the stars representing
the full field of each detector (selected for isolation from
nearby stars and high SNR) for each scan position. The optimal
focus and tip/tilt (cylinder rotation) of the IM1 and M1
mechanisms will then be determined and provided, in units of
motor steps from the current positions, at least 12 h prior to
the scheduled uplink.
COMMENTS: Care must be taken when crafting the focus scans to
assure that the focus motor temperatures will not reach their red
limits. This may require explicit pauses built into the proposal,
especially for the HRC; WFC images naturally pad the times
between focus motions with their relatively lengthy read and dump
times.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: October 5, 2000
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2.6.11
ID:
ACS Image Quality and PSF Measurement
ACS-15
APPLICABLE SMOV REQUIREMENT: J.10.4.3.3.2; J.10.4.3.3.5
DESCRIPTION: This activity will obtain a series of images to
evaluate the point source image quality over the fields of view
of the ACS HRC and WFC channels in normal imaging (noncoronagraphic) mode, after the corrector mechanisms have been
used to optimize the image focus and symmetry. A moderate density
open cluster will be the target. NGC-188 is suggested, since it
is available year-round and has suitable density and magnitude
distribution. Images will be obtained in the F502N and F625W
filters, with 0.5 px dithers in each axis.
A larger (~10 arcsec)
POS-TARG offset may be used to improve the sampling over the HRC
field, while maintaining mean star separation (>5 arcsec)
adequate for PSF evaluation to a reasonable radius.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS14, ACS Fine Corrector Alignment, must be
successfully completed prior to implementation of ACS15.
DURATION: 4 orbits; 1 per filter for WFC, 1 per filter for HRC
DATA REQUIREMENTS: 8 WFC images (260 MB) and 24 HRC images (50
MB) will be downlinked. Data should be delivered to the archive
without delay; subsequent SMOV observations are dependent on the
image quality verification that results from this activity.
ANALYSES & RESULTS: Encircled energy vs. radius, peak fraction
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(sharpness), and FWHM statistics will be derived for all stars
with adequate isolation and SNR in each field. Phase retrieval
analysis will be performed a selected star images through the
F502N filter to evaluate the residual aberration content. The
F625W EE values will be compared to the ACS CEI spec at 633 nm
and the F502N EEs with SMO-1000.
COMMENTS: The ACS SBC image quality will be assessed with a
separate activity. The far wings of the HRC and WFC PSFs may best
be characterized by deep images of more isolated point sources,
such as the targets used for the ACS sensitivity calibration.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: October 9, 2000
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2.6.12
ID:
HRC Coronagraph Repeatability
ACS-16
APPLICABLE SMOV REQUIREMENTS: J.10.4.3.1.6, J.10.4.3.3.3
DESCRIPTION: The stability of the HRC coronagraph will be
monitored by repeatedly deploying the cal/coronagraph door
mechanism and subsequently recording a quasi-flat field image.
Four cycles will be executed over the course of one orbit,
followed by another four cycles in one-orbit three hours later.
During the intervening two orbits, the coronagraph will be
retracted and stowed.
Eight quasi-flat field images will be
recorded during these two orbits to monitor stability of the
stowed configuration.
To determine the positions of the
coronagraphic masks and Fastie Finger, good signal-to-noise HRC
images of a wide-angle, bright, diffuse source are needed.
Candidate targets are M42 (Orion Nebula; RA = 5 hr) for a
Fall/Winter SMOV, M8 (Lagoon Nebula; RA = 18 hr) for a
Spring/Summer SMOV, or Earth during HST occultation.
The nebular
targets will be imaged through F606W; Earth will be imaged
through F334N.
Telescope pointings will be selected to minimize
the number of field stars within the nebulae that will saturate
the detector.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: None
DURATION: 4 orbits
DATA REQUIREMENTS: 16 HRC images (36 MB) will be downlinked.
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ANALYSES & RESULTS: The positions of the coronagraphic masks and
Fastie Finger will be determined from their shadows cast under
quasi-flat field illumination. Pixels with values within 90% of
the minimum transparency of each coronagraphic mask will be
mapped for stability monitoring.
COMMENTS: This activity can be executed in tandem with ACS12 (HRC
Coronagraph Acquisition) using the same quasi-flat field
illumination source.
AUTHOR/telephone/email:
David Golimowski / 410-516-6181 /
dag@pha.jhu.edu
DATE: November 2, 2000
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2.6.13
ID:
ACS Image Stability Verification
ACS-17
APPLICABLE SMOV REQUIREMENT: J.10.4.3.3.4
DESCRIPTION: This activity will monitor the location and focus
stability of external star images on the WFC and HRC during both
thermally quiescent and worst-case thermal slew conditions.
Bright star images will be observed with high SNR in sub-arrays,
alternating between the WFC and HRC channels. No ACS
configuration changes (other than shutter rotation) will be made
during the entire sequence. The observations will begin in a warm
S/C orientation, with sun angle of about 135 degrees, and offnominal roll (-V2 toward sun), to warm the ACS quadrant. After 8
orbits, the telescope will observe a target near the anti-solar
point, which represents a cold attitude, and images will continue
to be obtained for another 8 orbits. Small sub-arrays will be
used to reduce data volume and readout time and maximize temporal
sampling, such that image motion can be assessed on a time-scale
of ~ 1 minute. A variety of exposure times will be used, from the
minimal (0.1 and 0.5 s on HRC and WFC, respectively) to 100 s, to
assess jitter on shorter time-scales. The targets fields should
contain stars with a range of magnitudes such that high SNR can
be achieved on at least one star in each (WFC and HRC) sub-array
field,
without moving the telescope, at each exposure level.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS11, ACS to FGS Alignment, must be successfully
completed and its results incorporated into the PDB SIAF prior to
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implementation of ACS17. This will assure that the target stars
will be reasonably centered on the detector sub-arrays.
DURATION: 16 consecutive orbits; SAA free orbits should be
scheduled in the middle of the program, during the thermal slew,
to ensure more continuous coverage at that more critical time.
DATA REQUIREMENTS: 600 WFC 100x100 px sub-array images (14 MB)
and 600 HRC 200x200 px sub-array images (28 MB) will be downlinked.
ANALYSES & RESULTS: The images of like exposure time from each
detector will be cross-correlated to accurately (<.02 px)
determine the image drift rates as the observatory comes into
thermal equilibrium in both the hot and cold attitudes, and as it
passes through a significant thermal slew.
Images of various
exposure times will be compared (peak fraction, FWHM) to search
for evidence of jitter. Differences in image motion behavior
(magnitude and direction) between the WFC and HRC will be
interpreted as due to internal ACS instability, while coherent
drift is likely attributable to the OTA or to the ACS moving with
respect to the telescope.
The results will be compared with the
CEI image stability spec and may have ramifications regarding the
scheduling of science observations.
COMMENTS: Target selection is dependent on the time of
observations, but since target requirements are not stringent, no
difficulty is expected in selecting suitable targets for any
date.
AUTHOR/telephone/email: George Hartig/410-338-4966/
hartig@stsci.edu
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DATE: November 1, 2000
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2.6.14
ID:
CCD and SBC Flat Fielding Stability
ACS-18
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.5
DESCRIPTION: The stability and uniformity of the low-frequency
flat fields (L-flat) of all ACS detectors will be assessed by
using multiple pointing observations of globular clusters (Omega
Centauri, 47 Tucanae, and NGC6681) and/or Baade's window - thus
imaging moderately dense stellar fields. By placing the same star
over different portions of the detectors and measuring relative
changes in its brightness it will be possible to determine local
variations in the response of the detectors. Based on previous
experience with STIS, it is deemed that a total of nine different
pointings will suffice to provide adequate characterization of
the flat field stability in any given band. For each filter to be
tested, the baseline consists of 9 pointings with steps of ~20%
of the FOV in a diagonal cross pattern. During SMOV, the
complement of filters to be tested is limited to the following:
for the WFC, the SDSS filter set (F475W, F625W, F775W, F850LP);
for the HRC, the same as the WFC with the addition of F220W and
F330W; for the SBC, F125LP and F150LP. In order to provide
complementary data for the geometric distortion programs (ACS27),
and also to check that the distortion is not chromatic, three
additional exposures will be taken with each of F775W, F220W and
F125LP with a very small (~10 pixel) offset from the center (see
ACS27).
During the HRC/F625W observations a parallel observation is take
with the WFC to test that the image can be successfully
compressed as expected (originally program ACS32). Parallel
observing will only be activated for one orbit and when HRC is
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observing in a filter which is not fundamental to other programs
(namely geometric distortion).
IMPLEMENTATION METHOD: SMS.
All offsets will be done using POS-
TARG commands.
DEPENDENCIES: ACS14: ACS corrector alignment, ACS21: SBC detector
mini-functional (limited to the SBC). Note also that this
activity must be done in coordination with the Geometric
Distortion program.
DURATION: A total of 24 orbits as follows:
WFC + F475W
: 0
WFC + F625W
: 2
WFC + F775W
: 3
WFC + F850LP
: 2
HRC + F475W
: 0
HRC + F625W
: 2
HRC + F775W
: 3
HRC + F850LP
: 2
HRC + F220W
: 3
HRC + F330W
: 2
SBC + F125LP
: 3
SBC + F150LP
: 2
(from geometric distortion)
(from geometric distortion)
DATA REQUIREMENTS: This activity will produce 33 WFC images (1150
MB), 56 HRC images (125 MB), and 13 SBC images (28 MB). Data
should be promptly delivered to the archive, since flat fields
affect all ACS programs in SMOV, ERO and normal science
operations. To test on-board compression (originally program
ACS32), 3 full WFC images will be collected during one of the HRC
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orbits, generating another 100 MB worth of data (before
compression).
ANALYSES & RESULTS: Standard IDL or IRAF routines will be used to
find well exposed isolated stars (e.g. DAOFIND) and measure their
centroids and relative brightness across images. IDL code
developed by T. Brown (GSFC) for assessing the stability and
uniformity of STIS flat fields will be adapted to our specific
needs.
COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Guido De Marchi (STScI) / +1 410-338-4810
/demarchi@stsci.edu
DATE: November 7, 2000
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2.6.15
ID:
ACS Sensitivity
ACS-20
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.3
DESCRIPTION: The sensitivity of all three cameras will be tested
by observing a set of suitable spectrophotometric standards in
all band-passes. Targets include GD71 (or GD153) for the WFC and
HRC, NGC6681 for SBC broad band filters, and HS2027+0651 for SBC
medium band filter and prisms. A set of two CR-SPLIT images is
always taken with the CCDs, but no long time stability
(repeatability) is checked. All filters, including ramp filters,
will be tested. In order to minimize readout times and to keep
the data volume low, only a sub-array is read in WFC images of
size 512x512 pixel square.
In order to provide complementary data for the grism/prism
characterization program (ACS29), three additional images will be
taken with each prism by moving the target in the field of view.
These data will provide information on the stability and
uniformity of the wavelength response/calibration of the prisms
across the field of view.
IMPLEMENTATION METHOD: SMS, stored command.
DEPENDENCIES: ACS11: ACS to FGS alignment, ACS14: ACS fine
corrector alignment
DURATION: A total of 16 orbits as follows:
HRC all filters
4
WFC ramp filters
8
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WFC reg. filters
2
SBC prisms+narrow
1
SBC broad band
1
DATA REQUIREMENTS: This activity will produce 16 SBC images (32
MB), 116 WFC sub-images (116 * 0.5 MB = 58 MB), and 29 HRB images
(58 MB). Data should be promptly delivered to the archive, since
flat fields affect all ACS programs in SMOV, ERO and normal
science operations.
ANALYSES & RESULTS: Data will be analyzed using standard IDL and
IRAF (digiphot) aperture photometry routines to build encircled
energy profiles and to measure the total number of counts within
any given aperture. Comparing these results with the predictions
of SYNPHOT will provide absolute photometric calibration in each
bandpass.
COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Guido De Marchi (STScI) / +1 410-338-4810
/demarchi@stsci.edu
DATE: November 7, 2000
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2.6.16
ID:
SBC Detector Mini-Functional
ACS-21
APPLICABLE SMOV REQUIREMENT: J.10.4.3.1.6
DESCRIPTION: Operation of the SBC filter wheel will be tested.
The SBC has 12 filter wheel positions, four of them being
blocked. The SBC detector voltages will be off during this test.
Starting at whichever filter is in place, shift to each of the 12
positions in turn in one direction and confirm from engineering
telemetry that the position. has been reached.
Then proceed to
do 12 steps in the reverse direction.
IMPLEMENTATION METHOD: Stored commanding
DEPENDENCIES: None
DURATION: 10 minutes
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: Analysis consists of examining the
engineering position numbers and
confirming that they are as
commanded.
COMMENTS: N/A
AUTHOR/ORG/TEL #/E-MAIL: Colin Cox STSci /410-3384792/cox@stsci.edu/
DATE: November 8, 2000
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2.6.17
ID:
SBC Dark Rate Measurement
ACS-22
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.2
DESCRIPTION: Shortly after entering a block of non-SAA orbits,
the SBC high voltage will be ramped up to nominal observing
values.
The ACS M3 fold mirror will be in the HRC position and
the SBC filter wheel will be at an opaque blocker position.
per hour, an 1800-second SBC dark exposure will be taken.
Once
In
all, 10 such exposures will be taken over the course of 7 orbits.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS08 (SBC Anomalous Recovery Test) must be
successfully completed prior to this test.
ACS09 (SBC Fold
Analysis for Anomalous Recovery) is NOT required in advance.
DURATION: 7 orbits, in contiguous block of non-SAA orbits
DATA REQUIREMENTS: 10 SBC images (21 Mbytes total) will be
downlinked. Standard engineering data of SBC temperatures and
event rates will also be monitored.
ANALYSES & RESULTS: The count rate and image structure of the SBC
dark images will be characterized as a function of temperature
and time after turn on.
identified.
Hot spots in the dark images will be
The event counter rate in the engineering data will
also be examined as a function of time to search for any
day/night dependence that might be indicative of a light leak
(unlikely).
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COMMENTS: The principal point of this activity is to characterize
the dark rate and image structure as a function of SBC detector
temperature.
Because the SBC power will typically be off when it
is not observing, SBC observation sequences will be characterized
by turn on at a relatively cool tube temperature and gradual
warm-up of the detector over the course of the observing period.
This test will give an indication of what can be expected in the
way of detector background as a function of temperature and time
after turn on and thus will help guide science planning of SBC
observations.
AUTHOR/telephone/email: Randy Kimble/GSFC
kimble@ccd.gsfc.nasa.gov
DATE: November 22, 2000
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2.6.18
ID:
ACS SBC Image Quality and PSF Measurement
ACS-23
APPLICABLE SMOV REQUIREMENT: J.10.4.3.3.2; J.10.4.3.3.5
DESCRIPTION: This activity will obtain a series of images to
evaluate the point source image quality over the field of view of
the ACS SBC channel, after the corrector mechanisms have been
used to optimize the image focus and symmetry using the HRC
channel. NGC 6681 (18.7 h, -32 deg) will be the target, as this
star field has been used extensively by the STIS program for UV
PSF measurement and photometry. High SNR images will be obtained
in the F122M, F125LP and F150LP filters, with dithers in each
axis. The field will also be observed with the HRC
(F220W) to
establish the relative aperture location/orientation.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS14, ACS Fine Corrector Alignment, and ACS21, SBC
Detector Mini-functional Test, must be successfully completed
prior to implementation of ACS15.
DURATION: 3 orbits (~1 per filter)
DATA REQUIREMENTS: 12 SBC and 2 HRC images (30 MB) will be
downlinked. Data should be delivered to the archive without
delay; subsequent SMOV observations are dependent on the image
quality verification that results from this activity.
ANALYSES & RESULTS: Encircled energy vs. radius, peak fraction
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(sharpness), and FWHM statistics will be derived for all stars
with adequate isolation and SNR
in each field. The F122M EE
values will be compared to the ACS CEI and SMOV-1000 specs at 122
nm.
COMMENTS: The far wings of the SBC PSFs may best be characterized
by deep images of more isolated point sources, such as the
targets used for the ACS sensitivity calibration. Choice of
target NGC 6681 may require a delay in the implementation of this
activity, as it is unavailable from Nov through Feb. This
activity may potentially be combined with ACS27, SBC Geometric
Distortion, which should use the same target. However, it may be
safer to await the results of this test before continuing with
the SBC observations, in case the image quality is sub-par and
corrective action can be taken.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: October 19, 2000
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2.6.19
ID:
Scattered Light in Coronagraphic Observations
ACS-25
APPLICABLE SMOV REQUIREMENTS: J.10.4.3.3.5
DESCRIPTION: The scattered-light suppression of the HRC
coronagraph will be examined by obtaining several exposures of an
occulted star through F330W, F606W, and F814W, as a function of
position behind each coronagraphic mask.
non-peculiar, 4th-5
th
The target should be a
magnitude, solar-type (G0-G5 V) star with
no known circumstellar features or emission.
The star will be
acquired at the nominal center of the 1.8 and 3.0 arcsec masks
and at a designated location on the Fastie Finger.
At the nominal position of the 1.8 arcsec mask, four exposures of
different length through each filter will be recorded for the
purpose of obtaining
unsaturated images of the central
diffraction spot and the scattered light at distances of 1, 5 and
10 arcsec from the star.
The star will then be dithered to the
corners of a 2x2 pixel box centered on the nominal mask position.
At each dither position, a set of four images through F606W will
be recorded with the same exposure times used for that filter at
the nominal mask position. Thus, 28 images will be recorded for
the 1.8 arcsec mask.
The star will then be re-acquired at the nominal HRC aperture and
positioned at the nominal center of the 3.0 arcsec mask.
The
exposure-and-dither sequence described above will be repeated.
The coronagraph mechanism will then be retracted and the star
will be re-acquired at the nominal HRC aperture.
The star will
then be positioned at the nominal aperture of the Fastie Finger.
Two exposures through F606W will be recorded for the purpose of
assessing the small-angle and large-angle scattered light.
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IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS12 (HRC Coronagraph Acquisition) must be
successfully completed prior to this activity.
DURATION: 5 orbits
DATA REQUIREMENTS: 58 HRC images (128 MB) will be downlinked.
ANALYSES & RESULTS: Each set of images for each filter and star
position will be combined to produced one coronagraphic PSF with
good signal-to-noise over a dynamic range of 5 magnitudes between
0 and 10 arcsec from the star.
The combined PSFs will be
compared with models to assess the structure and cause of the
scattered light.
Absolute flux calibration will be obtained
using synphot analysis of a solar spectrum.
COMMENTS: N/A
AUTHOR/telephone/email:
David Golimowski / 410-516-6181 /
dag@pha.jhu.edu
DATE: November 2, 2000
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2.6.20
ID:
ACS Ramp Filter Test
ACS-26
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.3
DESCRIPTION: This program has 2 main goals: 1) to verify that the
desired wavelength has been correctly placed over the aperture;
2) to measure the throughput at a few selected wavelengths as a
function of position within the ramp filter monochromatic FOV.
These measurements will be carried out by imaging a known and
well observed (both HST and ground-based) planetary nebula (PN)
in several key emission lines -- [OII] 3727, [OIII] 5007, Halpha+[NII] and/or [SII] 6717,6731. These 3 (4) emission lines
fall onto three separate middle ramp segments -- FR388N, FR505N,
and FR656N -- and will allow intercomparison between the ACS ramp
filters and fixed bandpass narrow-band filters F502N ([OIII]
5007) and F658N (H-alpha + [NII]) for both the WFC and HRC
detectors.
The target PN need to be well observed by HST/WFPC2 and from the
ground. This will assure quick and fair assessment of both the
relative and absolute throughput of the ramp filters at the
wavelengths of the emission lines as well as our ability to
recover the real surface brightness distribution. In addition we
require the PN to be reasonably large (D > 1 arcmin) to make sure
the object fills out the ramp filter monochromatic FOV on both
the WFC and HRC detectors. Good candidates are the Ring Nebula or
the Eskimo Nebula
(http://hubble.stsci.edu/gallery/showcase/nebulae/n1.shtml).
The target (or some part of it) will be placed in one of the
middle ramp filters apertures, say WFC1-MRAMP. Images will then
be taken at the wavelengths of the emission lines 3727 ([OII],
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FR388N), 5007 ([OIII], FR505N), 6563 (H-alpha+[NII], FR656N) and
6525 ([SII], FR656N) and through the fixed bandpass narrow
filters F502N and F658N.
The observational sequence will be repeated with the HRC
detector.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS14, Fine Corrector Alignment, must be
successfully completed prior to this activity.
DURATION: 4 orbits (2 orbit WFC plus 2 orbit HRC)
DATA REQUIREMENTS: 12 WFC full frame images (385 MB) and 12 HRC
images (30 MB) will be downlinked.
ANALYSES & RESULTS: The analyses of each emission line image will
be as follows: First, reduction of the images will follow the
usual CALACS procedure by using the pFlat from the nearest broad
band filter including the wavelength of interest. We then apply a
low frequency flat field (lFlat) constructed from the GSFC lab
measurements of the ramp filters.
This is essentially an
"illumination" correction and is designed to recover the actual
surface brightness distribution of the extended source over the
monochromatic FOV of the ramp filter (for a given wavelength).
The image will then be compared with the existing WFPC2 and
ground-based images and with the ACS images taken through F502N
and F658N.
COMMENTS: This activity may be combined with ACS18, CCD and SBC
Flat Fielding Stability, using the same target field.
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AUTHOR/telephone/email: Zlatan Tsvetanov / 410-516-8585 /
zlatan@pha.jhu.edu
DATE: November 2, 2000
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2.6.21
ID:
CCD and SBC Geometric Distortion
ACS-27
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.1
DESCRIPTION: The geometric distortion of all ACS detectors will
be measured using multiple pointing observations of globular
clusters (Omega Centauri, 47 Tucanae, and NGC6681) and/or Baade's
window - thus imaging moderately dense stellar fields.
Centroid
position of stars will be used to tie down the geometric
distortion to about 0.2 pixels across the field of each detector.
These high quality baseline measurements of the distortion will
be ideal for diagnosing any temporal variations in later
calibration campaigns.
For WFC and HRC, 20 pointings in the blue
(F475W) will be used, allowing us to sample the full range of
spatial scales from 10 pixels to the detector width.
Care will
be taken to choose fields were all pointings can be obtained with
a single set of guide stars, allowing the plate scale to be
accurately determined.
by the WFPC2 team.
Our analysis method is based on that used
It will determine the relative offsets of the
pointings in pixels, and measure the geometric distortion in a
completely self-consistent manner.
A check of the distortion in
the red (F775W) will be done by adding three pointings offset by
about 10 pixels to observations of the same field in the same
band that will be done as part of the L-flat SMOV observations.
The distortion of the SBC in F125LP will be measured primarily
from L-flat observations of NGC6681 and by boot-strapping off of
HRC F220W observations of the same pointings.
In order to
accurately measure the stellar positions, three additional
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pointings (beyond those required for L-flats) offset by about 10
pixels will be required for both the HRC F220W and SBC F125LP
observations.
IMPLEMENTATION METHOD: SMS.
All offsets will be done using POS-
TARG commands.
DEPENDENCIES: To be done in coordination with the L-Flat SMOV
campaign.
DURATION: A total of 6 orbits as follows:
WFC + F475W
: 4 orbits
HRC + F475W
: 2 orbits
WFC + F775W
: data will be obtained in L-flat campaign
(9018)
HRC + F775W
: data will be obtained in L-flat campaign
(9019)
HRC + F220W
: data will be obtained in L-flat campaign
(9019)
SBC + F125LP : data will be obtained in L-flat campaign
(9024)
DATA REQUIREMENTS: This activity will produce 20 WFC images (688
MB), and 20 HRC images (43 MB).
The analysis will also
incorporate data from the L-flat campaign amounting to 4
additional WFC frames, 8 additional HRC frames and 13 additional
SBC frames.
Data should be promptly delivered to the archive,
since the determination and characterization of geometric
distortion impinges on almost all ACS programs in SMOV, ERO
and normal science operations.
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ANALYSES & RESULTS: Standard IDL or IRAF routines will be used to
find well exposed isolated stars (e.g. DAOFIND) and measure their
centroids. IDL code by S. Casertano used to measure the WFPC2
geometric distortion will be modified and automated for this
campaign.
COMMENTS:
N/A
AUTHOR/telephone/email: Gerhardt Meurer / +1 410 516 5154 /
meurer@pha.jhu.edu
DATE: November 3, 2000
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2.6.22
ID:
ACS Grism/Prism Performance Check
ACS-29
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.3
DESCRIPTION: This program has 2 main goals. 1) to measure the
dispersion of the WFC and HRC grisms/prisms, i.e. the positions
relative to an undispersed image as a function of wavelength. 2)
to measure the throughput as a function of wavelength. These
measurements will be carried out at several positions on the
detectors in order to verify that changes in the dispersion and
locations of the spectra are small.
In case of the throughput
measurements, the different positions are also needed to verify
that fringing is small.
The dispersions will be measured from spectra of spectral line
objects. For that purpose, suitable WR stars with available
spectra will be observed at five different locations on the
detector, one close to the center and four more close to the
edges. The center observations will be repeated once to verify
repeatability of the dispersion parameters after filter wheel
motion.
Each observation consists of one image without
disperser, followed by a second image with the prism or grism.
The location and distortions of the spectra as well as the final
throughput will be derived from spectra of the HST standard white
dwarfs G191B2B or GD153. Observations will be taken at positions
close to the ones selected for the wavelength calibrators. Again,
an undispersed image will be obtained before each spectrum.
IMPLEMENTATION METHOD: Proposal
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DEPENDENCIES: ACS14, Fine Corrector Alignment, must be
successfully completed prior to this activity.
DURATION: 6 orbits
DATA REQUIREMENTS: 22 WFC full frame images (700 MB) and 22 HRC
images (52 MB) will be downlinked.
ANALYSES & RESULTS: For the continuum sources, the analysis
consists of the following: First, the spectra will be "traced",
i.e. the location of the spectra of objects relative to their
undispersed counterparts will be measured at the different
positions in the field. Subsequently, extracted spectra of the
spectral line objects will be used to determine non-linear
dispersion and its change within the fields. Finally, this
wavelength calibration will be applied to extracted continuum
source spectra.
These spectra will be compared to the known
absolute fluxes of the white dwarfs in order to compute the
throughput of the grisms and their change over the field of view
in electrons/Jy.
COMMENTS: This activity may be combined with ACS18, CCD and SBC
Flat Fielding Stability, using the same target field.
AUTHOR/telephone/email: Wolfram Freudling / 01149-89-32006525 /
wfreudli@eso.org
DATE: October 15, 2000
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2.6.23
ID:
ACS CCD Hot Pixel Annealing
ACS-31
APPLICABLE SMOV REQUIREMENT: J.10.4.3.4.2
DESCRIPTION: The effectiveness of the CCD hot pixel annealing
process is assessed by measuring the dark current behavior before
and after annealing and by searching for any window contamination
effects. The CCD TEC will be turned off to allow CCD detector
temperature to rise. In addition, heaters will be activated. The
CCD will be left in an uncooled state for approximately 24 hours,
after which the heaters will be switched off, the TEC turned back
on, and the CCD cooled to normal temperature. Two dark images
will be taken both before the TEC are turned off and after they
have been turned on and the CCD returned to their normal
operating temperature. This test will be run simultaneously on
the WFC and HRC.
IMPLEMENTATION METHOD: SMS, stored command.
DEPENDENCIES: ACS05: CCD functional
DURATION: 28 hours
DATA REQUIREMENTS: This activity will produce four WFC images
(128 MB) and four HRC images (8 MB).
ANALYSES & RESULTS: The result of this test will be a
confirmation of the effectiveness of this technique for annealing
certain types of hot CCD pixels. Pixel by pixel comparison of
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dark images taken before and after the annealing will be run to
determine the fraction of hot pixels annealed
COMMENTS: This test should be scheduled approximately two weeks
after the CCD detector functional test is completed. This will
allow sufficient time for the CCD to experience the highly
radiative environment of the HST orbit.
AUTHOR/TELEPHONE/EMAIL: Guido De Marchi (STScI) / +1 410 338 4810
/ demarchi@stsci.edu
DATE: November 7, 2000
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2.6.24
ID:
CCD Flash Verification
ACS-32
APPLICABLE SMOV REQUIREMENT: J.10.4.3.1.7
DESCRIPTION: Operation of the WFC and HRC flash LEDs, on the
primary side (MEB 1) only, will be verified and the exposure
levels baselined. Each of the three current levels will be
exercised and measurements will be made on both "sides" of the
shutters, since the level and uniformity of the flash
illumination may be dependent on shutter position. Short-term
repeatability will also be evaluated with a series of identical
exposures with and without intervening shutter movement.
These calibration flash exposures are implemented as minimal
exposure time (0.1 or 0.5 s, for HRC and WFC, respectively) darks
or internals (with no cal lamp on), the latter to induce shutter
rotation. The flash duration will typically be the maximum (~40s)
to optimize SNR, but repeatability at the expected shortest
useful exposure time (~1s) will also be verified.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: ACS05, CCD Functional, must be successfully
completed prior to this activity.
DURATION: ~4 hrs, all internal, may be scheduled intermittently
during earth occultation periods.
DATA REQUIREMENTS: 20 WFC full frame images (680 MB) and 20 HRC
images (42 MB) will be down-linked.
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ANALYSES & RESULTS: Analysis will consist of determination of the
mean exposure level for each flash current on each detector, and
evaluation of the exposure uniformity and repeatability. The
latter will be determined by computing the smoothed ratio of
similar flash exposures and will be examined for correlations
with shutter "side" and exposure duration. The flash exposures
will be summed to produce a set of "super-flash" images for use
by the pipeline.
COMMENTS: Although the flash capability is not expected to be put
into routine use for science observations for several years,
after which time the radiation-induced CTE degradation will
warrant its use, this verification program will serve as a
baseline for comparison with future flash measurements and will
facilitate planning of the flash exposures.
AUTHOR/telephone/email: George Hartig / 410-338-4966 /
hartig@stsci.edu
DATE: January 6, 2001
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2.7
DATA MANAGEMENT SUBSYSTEM
There are no specific activities required for DMS Subsystem during
SMOV.
2.8
INSTRUMENTATION AND COMMUNICATION SUBSYSTEM
There are no specific activities required for I&C Subsystem during
SMOV.
2.9
SCIENTIFIC INSTRUMENTS CONTROL & DATA HANDLING SUBSYSTEM
There are no specific activities required for SIC&DH Subsystem during
SMOV.
2.10
POINTING AND SAFEMODE ELECTRONICS ASSEMBLY
There are no specific activities required for the PSEA during SMOV.
2.11
CORRECTIVE OPTICS SPACE TELESCOPE AXIAL REPLACEMENT
There are no specific activities required for the COSTAR Subsystem
during SMOV.
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2.12
SPACE TELESCOPE IMAGING SPECTROGRAPH
Table 2-6 shows the verification activities that must be accomplished
during SMOV to verify the performance of the Space Telescope Imaging
Spectrograph (STIS) to support normal science operations.
Table 2-6
STIS SMOV Activities
Activity
Observatory
Execution
Duration
Summary #
Verification Activity
Phase
Hr:min
STIS-00
Pre-SM Calibration
SMS
09:00
STIS-01
CCD Functional
SMS
09:00
STIS-02
Image Quality
SMS
04:30
STIS-03
MAMA Dark vs. Temperature
SMS
03:00
STIS-04
Jitter Test
SMS
03:00
STIS-05
End of BEA Test
SMS
01:30
STIS-06
Contamination Monitor
SMS
09:00
STIS-07
CCD Bias
SMS
01:30
STIS-08
CCD Darks
SMS
01:30
STIS-09
MAMA Darks
SMS
01:30
STIS-20
Corrector Alignment
SMS
N/A
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2.12.1
ID:
Pre-SM Calibration
STIS-00
APPLICABLE SMOV REQUIREMENT: Prerequisite for successful analysis
of "STIS-04 Jitter Test" and "STIS-05 End of BEA Test."
DESCRIPTION: Prepare for SMOV3B program. Prior to SMOV3B, perform
1 iteration of "STIS-04 Jitter Test" to assess feasibility of the
proposed jitter test.
Also, observe new flux standards (WD
2126+734, WD 0320-539, WD 0710+741, and WD 0214+568) needed to
completely cover all possible BEA dates.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: Execute prior to SM3B. Feasibility study for "STIS04 Jitter Test". Prerequisite for success of "STIS-05 End of BEA
Test".
DURATION: 2 external MAMA orbits (in 1 visit) for STIS-04
preparatory observations and 4 external orbits (in 4 visits) for
STIS-05 preparatory observations. Total of 5 visits.
DATA REQUIREMENTS: 80 MBytes prior to SM3B.
ANALYSIS & RESULTS: Analyze jitter data as described in "STIS-04
Jitter Test". No jitter is expected, but Monte Carlo analysis of
actual data will provide a realistic estimate of test
sensitivity. Reduce observations of new flux standards using
standard pipeline processing. Compare resulting fluxes with IUE
or other archival data.
Reduce observations again when "STIS-05
End of BEA Test" executes, just to ensure uniform processing of
data obtained before and after SM3B.
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COMMENTS: PI will be Valenti.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.2
ID:
CCD Functional
STIS-01
APPLICABLE SMOV REQUIREMENT: J.10.4.5.1.1, J.10.4.5.1.2,
J.10.4.5.4.1.1
DESCRIPTION: Validate proper functioning of CCD while obtaining a
baseline noise measurement prior to NCC turn-on. Verify that CCD
is still able to maintain a temperature setpoint of -83 C in the
early post-SM3 thermal environment. Measure CCD read noise from
multiple bias frames obtained in common science modes: amplifier
D, gains of 1 and 4 electrons/DN, and binning factors of 1x1 and
2x2.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: No prerequisites. This should be the first STIS CCD
proposal to execute during SMOV3B. This proposal should precede
NCC turn-on.
DURATION: 6 internal CCD orbits.
DATA REQUIREMENTS: 140 MBytes.
ANALYSIS & RESULTS: Subtract bias images pair-wise. Bin data
values in the resulting difference images into a histogram. For
each mode, fit the histogram with a Gaussian to determine a
robust estimate of the read noise. Compare the measured read
noise for each mode with historical values. These CCD noise
measurements will serve as a baseline for comparison with
analogous measurements (STIS-07) made after NCC turn-on. Obtain
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CCD temperatures from the standard engineering snapshots taken
before and after each exposure.
COMMENTS: This Program is pared down from the original CCD
functional in SM2 and the SM3A analog (8502). PI will be Valenti.
AUTHOR/telephone/mail: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.3
ID:
Image Quality
STIS-02
APPLICABLE SMOV REQUIREMENT: J.10.4.5.3.1, J.10.4.5.3.5.2
DESCRIPTION: Check image quality using two tests. In the first
test, use an ACQ/PEAK to dither the 0.1x0.09 aperture across a
point source to sample the PSF. Disperse light entering the
spectrograph onto the CCD using the G230LB grating. Relative
counts at different wavelengths give a measure of PSF shape at
different wavelengths. In the second test, image a point source
onto the CCD through the F28x50OII filter. Compare the resulting
PSF to the PSF shape prior to SM3.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: This proposal may execute after data for "STIS-01
CCD Functional" have been obtained. One iteration of this
proposal should precede NCC turn-on, while the second iteration
should follow NCC turn-on.
DURATION: 3 external CCD orbits per iteration. 2 iterations.
DATA REQUIREMENTS: 9 MBytes per iteration (18 MBytes total).
ANALYSIS: Examine relative count rate as a function of dither
offset and wavelength. Examine PSF shape apparent in [O II]
image. For both datasets, compare behavior in first iteration
(prior to NCC turn-on) with behavior seen prior to SM3B, both in
"STIS-00 Pre-SM Calibration" and in the STIS bimonthly monitor
program. Interpret any significant differences in terms of
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telescope and/or instrument focus. Compare behavior in second
iteration (after NCC turn-on) with behavior in first iteration.
Interpret any significant differences in terms of NCC
induced vibration.
COMMENTS: This program is analogous to SM3A proposal 8506. PI
will be Valenti.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/
valenti@stsci.edu
DATE: January 4, 2001
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2.12.4
ID:
MAMA Dark vs. Temperature
STIS-03
APPLICABLE REQUIREMENT: None. This proposal takes advantage of a
unique calibration opportunity during SMOV3B, when the MAMA
detectors will be colder than during normal operation.
DESCRIPTION: Measure dark rate for both MAMA detectors as a
function of instantaneous temperature and recent thermal history.
Make measurements at the beginning and end of 3 consecutive SAAfree passages.
IMPLEMENTATION METHOD: Proposal. Apply high voltage using
standard MAMA recovery procedures (STIS ISR 98-3).
DEPENDENCIES: To be useful, this proposal must be the first STIS
MAMA proposal to execute during SMOV3B. MAMA high voltage may not
be applied until at least 4 days after release (J.10.4.5.1.1). If
a reliable pressure sensor is operating in the aft shroud,
ambient pressure must drop below 1e-5 Torr prior to execution.
DURATION: 2 internal MAMA orbits per iteration. 3 iterations on
successive SAA-free passages.
DATA REQUIREMENTS: 32 MBytes per iteration (96 MBytes total).
RESULTS & ANALYSIS: Measure dark rates measurement to constrain
the existing model for phosphorescence from the face plate of the
NUV MAMA detector. The improved model will guide plans for use of
the Aft Shroud Cooling System (ASCS), when it is eventually
installed.
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COMMENTS: This program is analogous to SM3A proposal 8504. PI
will be Proffitt.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.5
ID:
Jitter Test
STIS-04
APPLICABLE SMOV REQUIREMENT: J.10.4.5.3.5.2
DESCRIPTION: Image a point source with the FUV MAMA detector in
TIMETAG mode. Use power spectra of image position versus time to
look for jitter at frequencies from about 0.2 to 100 Hz.
Local
count rate must be below the normal screening limit of 100 counts
per second per pixel. Global count rate from the source will be
roughly 100 counts per second over the entire detector. Minimize
the global count rate from geocoronal Lyman-alpha by observing a
relatively bright source through a low transmission filter.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: If "STIS03 MAMA Dark vs. Temperature" executes, it
should precede this program. In any case, MAMA high voltage may
not be applied until at least 4 days after release
(J.10.4.5.1.1). One iteration of this proposal should precede NCC
turn-on, while the second iteration should follow NCC turn-on.
DURATION: 2 external MAMA orbits per iteration. 2 iterations.
DATA REQUIREMENTS: 16 MBytes per iteration (32 MBytes total).
ANALYSIS: Divide the TIMETAG event list into equal time intervals
about 0.1 seconds in duration. Combine events in each time
interval to form a temporal sequence of images. For each image in
the sequence, calculate centroids along both detector axes. To
maximize measurement precision, calculate centroids using a
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uniform subset of all detector pixels. Use power spectra of
centroid position versus time to search for periodic motion of
the point source at the STIS detector. Use Monte Carlo techniques
to assess the significance of features in the power spectra.
For any significant periodic motion, determine the amplitude of
motion in pixels and estimate the corresponding slit losses for
commonly used science apertures.
COMMENTS: This program was not executed in SM2 or SM3A. Test
feasibility in "STIS-00 Pre-SM Calibration". Predict sensitivity
prior to execution of the relevant part of STIS-00. Each image in
the sequence will have low S/N, but roughly 400,000 total events
in 40,000 temporal samples should ultimately provide excellent
sensitivity. PI will be Valenti.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/
valenti@stsci.edu
DATE: January 4, 2001
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2.12.6
ID:
End of BEA Test
STIS-05
APPLICABLE SMOV REQUIREMENT: Apparently there is no formal Bright
Earth Avoidance (BEA) requirement in the official Requirements
Document, but a 12 day BEA period has been the basis for many
planning discussions.
DESCRIPTION: Use a G140L spectrum of a flux standard to assess
whether STIS sensitivity is significantly below pre-SM3
performance. Significantly degraded sensitivity will trigger
additional observations of flux standards to validate the initial
result and/or track subsequent (de)contamination. All standards
used in this program will have recent preparatory observations
obtained in the same configuration. Measurement accuracy will be
limited by global sensitivity fluctuations (less than 5%) rather
than photon counting statistics.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: From a health and safety standpoint, this proposal
can execute any time after MAMA high voltage is applied (at least
4 days after release, J.10.4.5.1.1). In practice, it is likely to
run after NCC turn-on. To allow ample time for outgassing,
schedule this proposal no earlier than 7 days after release. To
allow adequate time for analysis, execute this proposal at least
two days before a decision is needed whether to end BEA. Earlier
execution will allow more time for additional observations, if
necessary, without delaying the end of BEA. Obtain preparatory
observations as part of "STIS-00 Pre-SM Calibrations". This
program is the only test of whether it is safe to leave BEA.
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DURATION: 1 external MAMA orbit per iteration. Nominally only 1
iteration, but more are possible if the first iteration implies
significantly degraded sensitivity.
DATA REQUIREMENTS: 16 MBytes per iteration.
ANALYSIS: Reduce data from this program and all relevant pre-SM3B
observations with identical software. Bin extracted fluxes in
wavelength to reduce formal uncertainties per sample to less than
0.5%. Examine the ratio of fluxes measured before and after SM3B
for departures from unity greater than expected from normal
sensitivity fluctuations (less than 5%). A larger decrease in
sensitivity at shorter wavelengths would suggest contamination as
a contributor to the decrease in sensitivity.
COMMENTS: This program is analogous to portions of SM3A proposal
8514. Five well-chosen standards are adequate to guarantee that a
standard is always visible throughout the year in either the
northern or southern BEA zone. The newly selected set of
standards consists of WD 2126+734, WD 0320-539, GRW +70 5824, WD
0710+741, and WD 0214+568. GRW +70 5824 is regularly observed by
STIS in the relevant mode, but the other 4 proposed standards
will be observed as part of "STIS-00 Pre-SM Calibrations". PI
will be Valenti.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/
valenti@stsci.edu
DATE: January 4, 2001
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2.12.7
ID:
Contamination Monitor
STIS-06
APPLICABLE SMOV REQUIREMENT: J.10.4.5.1.6.2
DESCRIPTION: Use G140L spectra of the flux standard GRW +70 5824
to assess whether FUV sensitivity is significantly below
performance obtained during execution of "STIS-05 End of BEA" and
prior to SM3B. Significantly degraded sensitivity will trigger
additional observations of flux standards to validate the initial
result and/or track subsequent (de)contamination. GRW +70 5824 is
observed bimonthly in the same mode as part of the regular STIS
monitoring program. Measurement accuracy will be limited global
sensitivity fluctuations (less than 5%), rather than photon
counting statistics. Also obtain auxiliary NUV-MAMA and CCD
observations.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: This program should begin in the first week after
BEA ends. Since contamination must be negligible to end BEA, no
evidence of contamination is expected in this monitoring program.
Contingency planning should be limited to expedited (re)execution
of existing sensitivity tests, including this program.
DURATION: 6 external MAMA and CCD orbits per iteration. 1
iteration per week for 6 weeks after BEA ends.
DATA REQUIREMENTS: 32 MBytes per iteration (192 MBytes total).
ANALYSIS & RESULTS: Reduce data from this program in the same way
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bimonthly calibration observations of GRW +70 5824 are reduced.
Include newly extracted fluxes on a plot of historical flux
measurements. Use observed scatter to characterize measurement
uncertainty. A significant change in measured flux will trigger
additional observations and analysis.
COMMENTS: This Program is analogous to SM3A proposal 8505. This
program is also similar to "STIS-05 End of BEA Test", except that
execution after BEA ends allows more flexibility in target
selection PI will be Valenti.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.8
ID:
CCD Bias
STIS-07
APPLICABLE SMOV REQUIREMENT: J.10.4.5.4.1, J.10.4.5.4.1.1
DESCRIPTION: Measure CCD read noise from multiple bias frames
obtained in common science modes: amplifier D, gains 1 and 4
electrons/DN, and binning factors of 1x1, 1x2, 2x1, and 2x2.
Compare read noise measurements before and after NCC turn-on.
Construct standard calibration reference files for use in
pipeline reduction of SMOV3B data. Transition to analogous
calibration program when normal science begins.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: Prerequisite for transition to normal science
operation with the CCD. If convenient, begin program prior to the
first iteration of "STIS-02 Image Quality" to facilitate data
reduction. In any case, execute program at least once soon after
NCC turn-on to test the impact of NCC operation.
DURATION: 1 internal CCD orbit per day after this proposal
triggers and until transition into the corresponding calibration
program.
DATA REQUIREMENTS: 40 MBytes per iteration.
ANALYSIS & RESULTS: Measure read noise as in "STIS-01 CCD
Functional". Subtract bias images pair-wise. Bin data values in
the resulting difference images into a histogram. For each mode,
fit the histogram with a Gaussian to determine a robust estimate
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of the read noise. Compare the first read noise measurement after
NCC turn-on with measurements before NCC turn-on and before SM3B.
Diagnose any significant increase in read noise. Construct
standard calibration reference files following the same procedure
that is used in the corresponding calibration program.
COMMENTS: This program is analogous to SM3A proposal 8508 and
the standard calibration program to measure CCD bias each day.
PI will be Dressel.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.9
ID:
CCD Darks
STIS-08
APPLICABLE SMOV REQUIREMENT: J.10.4.5.4.1
DESCRIPTION: Obtain daily dark frames, as in the corresponding
calibration program. Construct standard calibration reference
files for use in pipeline reduction of SMOV3B data. Transition to
analogous calibration program when normal science operation with
the CCD begins.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: Prerequisite for transition to normal science
operation with the CCD. If convenient, begin prior to the first
iteration of "STIS-02 Image Quality" to facilitate reduction of
SMOV3B data. May begin any time prior to normal science
operations, if necessary.
DURATION: 1 internal CCD orbit per day after this proposal
triggers, continuing until transition into the corresponding
calibration program.
DATA REQUIREMENTS: 6 MBytes per iteration.
ANALYSIS & RESULTS: Construct standard calibration reference
files following the same procedure that is used in the
corresponding calibration program.
COMMENTS: This Program is analogous to SM3A proposal 8507. PI
will be Dressel.
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AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.10
ID:
MAMA Darks
STIS-09
APPLICABLE SMOV REQUIREMENT: J.10.4.5.4.1
DESCRIPTION: Obtain weekly dark frames, as in the corresponding
calibration program. Construct standard calibration reference
files for use in pipeline reduction of SMOV3B data. Transition to
analogous calibration program when normal science operation with
the MAMA detectors begins.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: Prerequisite for transition to normal science
operation with the MAMA detectors. If convenient, begin soon
after NCS turn-on to facilitate reduction of SMOV3B data. May
begin any time prior to normal science operations, if necessary.
DURATION: 1 internal MAMA orbit per week after this proposal
triggers and until transition into the corresponding calibration
program.
DATA REQUIREMENTS: 8 MBytes per iteration.
ANALYSIS & RESULTS: Construct standard calibration reference
files following the same procedure that is used in the
corresponding calibration program.
COMMENTS: This program is analogous to SM3A proposals 8509 and
8510. PI will be Proffitt.
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AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.12.11
ID:
Corrector Alignment
STIS-20
APPLICABLE SMOV REQUIREMENT: J.10.4.5.3.1
DESCRIPTION: If an adjustment of the STIS corrector is needed,
obtain images of a point source while stepping through corrector
positions. Use phase retrieval to determine best focus. Set the
corrector at best focus. Take a confirming image.
IMPLEMENTATION METHOD: Proposal.
DEPENDENCIES: Execute this contingency program only if data from
WFPC and "STIS-02 Image Quality" both imply that the STIS
corrector needs adjustment.
DURATION: External CCD orbits. Real time commanding.
DATA REQUIREMENTS: 44 MBytes per iteration, if this contingency
program executes.
ANALYSIS & RESULTS: Use phase retrieval of images obtained during
focus sweeps to determine the best focus.
COMMENTS: This Program is analogous to SM3A proposal 8512 and the
proposal used to align the corrector in SM2. PI will be Kriss.
AUTHOR/telephone/email: Jeff Valenti/410-338-2622/ valenti@stsci.edu
DATE: January 4, 2001
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2.13
Near Infrared Camera Multi-Object Spectrometer
Table 2-7 shows the verification activities that must be accomplished
during SMOV to verify the performance of the Near Infrared Camera
Multi-Object
Spectrometer
(NICMOS)
to
support
normal
science
operations.
Table 2-7
NICMOS SMOV Activities
Activity
Observatory
Execution
Duration
Summary #
Verification Activity
Phase
Hr:min
NICMOS-01
Filter Wheel Mechanism Test
SMS
03:00
NICMOS-02
FOM Operation Test
SMS
01:30
NICMOS-03
NICMOS Flats/ Quantum Efficiency
SMS
09:00
NICMOS-04
Detector Read Noise/ Shading/
SMS
18:00
Cosmic Ray Rates
NICMOS-05
Transfer Function Test
SMS
00:40
NICMOS-06
Fine Optical Alignment
SMS
21:00
NICMOS-07
NIC3 Fine Optical Alignment
SMS
07:30
NICMOS-09
Focus Monitor
SMS
09:00
NICMOS-10
Aperture Locations
SMS
09:00
NICMOS-11
Plate Scale
SMS
06:00
NICMOS-12
Mode 2 Target Acquisition Test
SMS
06:00
NICMOS-13
Coronagraphic Performance
SMS
09:00
NICMOS-14
Internal Flats
SMS
12:00
NICMOS-15
Photometry Test
SMS
24:00
NICMOS-16
SAA CR Persistence Test
SMS
07:30
NICMOS-17
Astronomical Persistence Test
SMS
04:30
NICMOS-18
Thermal Background
SMS
18:00
NICMOS-19
Grisms Absolute Sensitivity
SMS
03:00
NICMOS-20
Grisms Wavelength Calibration
SMS
03:00
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2.13.1
ID:
NICMOS Filter Wheel Mechanism Test
NICMOS-01
APPLICABLE SMOV REQUIREMENT: J.10.4.4.1.2
DESCRIPTION: A simple test to verify the mechanical operation of
each of the three filter wheel assemblies.
Each filter wheel
will be commanded to three filter positions and an internal flatfield exposure will be obtained at each position.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS cool down
DURATION: 2 orbits
DATA REQUIREMENTS: We will obtain 9 MULTIACCUM images with an
approximate total data volume of 37 MB.
ANALYSES & RESULTS: Each image will be examined for optical
artifacts and count-rates compared to pre-NCS predictions.
Result will be to verify the operability of the NICMOS filter
wheels.
RESPONSIBLE PARTIES:
STScI NICMOS group
COMMENTS: All filter wheel positions will be visited in SMOV
during the flat field test.
However, the purpose of this test is
to verify the operation of the filter wheel assembly as a whole,
and therefore it is not necessary to visit every filter position.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828,
noll@stsci.edu,
DATE: January 12, 2001
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ID:
NICMOS FOM Operation Test
NICMOS-02
APPLICABLE SMOV REQUIREMENT: J.10.4.4.1.2
DESCRIPTION:
This test verifies the FOM's mechanical operation.
The FOM will be moved to several positions and vignetting in NIC3
will be used to verify the motion.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS cool down
DURATION: 1 orbit
DATA REQUIREMENTS: 6 MULTIACCUM images with total data volume of
25 MB.
ANALYSES & RESULTS: Compare FOM position and rate telemetry with
pre-NCS performance. Analyze vignetting in NIC3 as a function of
FOM position. Verify that the FOM mechanical function remains at
pre-NCS level.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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ID:
NICMOS Flats/Quantum Efficiency
NICMOS-03
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.1
DESCRIPTION: Flat-field exposures in all three cameras will be
obtained once the NCS has reached a stable operating temperature
and will be repeated at two additional temperatures during the
temperature excursions that will be used to determine the final
NICMOS operating temperature.
The F110W and F160 W filters will
be measured in all three cameras and the F222M will be used as
well in NIC3.
The test will determine any changes in debris on
the detectors (grot), and will provide a measure of the quantum
efficiency of the detectors as a function of temperature.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS cool down, stable operating temperature
DURATION: 6 orbits
DATA REQUIREMENTS: 87 MB
ANALYSES & RESULTS: Flat fields will be compared to pre-NCS flats
to identify changes in contamination and to quantify changes in
quantum efficiency.
We will determine if additional debris has
been generated during the warm up and cool down of NICMOS and
will be able to produce bad pixel masks.
We will determine the
gain of the detectors at the temperatures provided by the NCS.
RESPONSIBLE PARTIES: STScI NICMOS group
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COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.4
ID:
NICMOS Detector Read Noise/Shading/Cosmic Ray Rates
NICMOS-04
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.5
DESCRIPTION: A series 30 of MULTIACCUM dark frames spanning 20
minutes each will be obtained, in parallel, in all three cameras.
At least 20 of these must be obtained when HST is not pointed at
the bright Earth, and all of them should be obtained away from
the SAA.
A subset of MULTIACCUM sequences will be used in order
to characterize "shading" which is treated as a component of the
dark current.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS final set point determined
DURATION: 12 orbits
DATA REQUIREMENTS:
374 MB
ANALYSES & RESULTS: Identify and clean cosmic ray events;
construct signal versus scatter plot to determine read noise.
Measurement of detector read noise and shading component of dark
current.
Measurement of cosmic ray event rate.
Confirmation
that the cosmic ray event rate is comparable to that measured in
Cycle 7.
RESPONSIBLE PARTIES: STScI NICMOS group
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COMMENTS: These observations may be scheduled as internals if
suitable spacecraft attitudes are available.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.5
ID:
NICMOS Transfer Function Test
NICMOS-05
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.2
DESCRIPTION: The purpose of this activity is to determine the
optimal detector DC offset voltage at the NCS operating
temperatures.
This voltage is adjusted to optimize the analog
signal processing A/D conversion.
This voltage is a function of
detector temperature so it will be repeated every (TBD) orbits
after the start of data taking with NICMOS.
The bias voltage
will be stepped from 0.0 to 0.5 V in 0.1 V step increments with 1
dark images at each point.
Data are taken with each detector.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS turn on
DURATION: Internal unpointed darks, no orbits.
minutes total per iteration.
Approximately 40
To be repeated 3 times during cool
down and once after final NCS setpoint is determined.
DATA REQUIREMENTS: 300 MB
ANALYSES & RESULTS: Correlate A/D output with bias voltage
settings. Determine optimal DC offset voltage.
voltages.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.6
ID:
NICMOS Fine Optical Alignment
NICMOS-06
APPLICABLE SMOV REQUIREMENT: J.10.4.4.3.2
DESCRIPTION: The purpose of this activity is to perform a series
of adjustments of the NICMOS pupil alignment mechanism to
establish the initial optical alignment in focus and tilt for all
three cameras.
A series of star field images will be obtained in
each camera in one filter.
Objectives: Establish PAM focus and X/Y tilt for each camera,
compare deviations relative to past performance.
region of PAM focus
included.
Cover enough
space to insure the optimal locations are
Allow sufficient time
(7-10 days) to analyze data and
uplink changes before the next activities.
Steps:
a) Do a 34-point focus sweep, +/- 8.5 mm along the PAM, in 0.5mm
steps, in one narrow band filter per camera.
b) Use PAM X/Y tilt and OTA offset slew compensations.
c) Focus sweep will be in the shortest wavelength narrow band
filter in each camera: CAM1=F095N, CAM2=F110W, CAM3=F108N
d) 9 point PAM X/Y tilt alignment grid, +/- 30 arcseconds about
camera 1 best focus position. This part of the proposal has to be
executed after the best PAM focus has been established for each
camera.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS semi-final set point determined
DURATION: 14 orbits
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DATA REQUIREMENTS: 215 MB
ANALYSES & RESULTS: Phase retrieval and encircled energy analysis
will be performed on these images to establish PAM focus
and X/Y tilt positions for each camera. These images will be
compared to pre-NCS images.
Focus and PAM alignment will be achieved, with accuracy levels
comparable to the pre-NCS performance.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: Test assumes focus positions are comparable to cycle 7.
Test design assumes implicitly that the year of inactivity has
not altered the parfocality of the filters in each camera.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.7
ID:
NICMOS NIC3 Fine Optical Alignment
NICMOS-07
APPLICABLE SMOV REQUIREMENT: J.10.4.4.3.2
DESCRIPTION: This proposal aims at establishing the best PAM/FOM
configuration for the NIC3 focus, assuming that the NIC3 defocusing characteristics are similar to the pre-NCS situation.
PAM sweeps over a restricted range around the NIC3 best focus
position will be obtained (~ 5 mm in PAM range, with 1 mm steps)
together with FOM sweeps along the Y direction (between 0
arcseconds and +20 arcseconds in 4 arcseconds steps).
Star field
images will be obtained in NIC3 in one short wavelength filter.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS semi-final set point determined
DURATION: 5 orbits
DATA REQUIREMENTS: 52 MB
ANALYSES & RESULTS: Phase retrieval and encircled energy analysis
will be performed on these images to establish best FOM focus for
camera 3. These images will be compared to pre-NCS images. Best
focus for NIC3 will be determined. FOM alignment will be achieved
for best NIC3 focus, with accuracy levels comparable to the preNCS performance.
RESPONSIBLE PARTIES: STScI NICMOS group
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COMMENTS: Separate test for NIC3 is needed because of the
different PAM range covered and the need to move the FOM to an
off-axis position to reduce vignetting.
Assumes conditions
similar to cycle 7.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.8
ID:
NICMOS Focus Monitor
NICMOS-09
APPLICABLE SMOV REQUIREMENT: J.10.4.4.3.2
DESCRIPTION: Steps in PAM focus, over the range +/- 8 mm, in 1 mm
steps, will be made to monitor the optimal focus and tilt
settings for all three NICMOS cameras. Images of a star field
will be obtained in all three cameras at short wavelengths at
each PAM position. The proposal will start 2 weeks after the Fine
Optical Alignment and will be repeated 6 weeks after Fine Optical
Alignment.
Test will cover sufficient region of PAM focus space
to insure the optimal locations are included.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06)
DURATION: 6 orbits
DATA REQUIREMENTS: 100 MB
ANALYSES & RESULTS: Phase retrieval and encircled energy will be
measured at each position of the PAM.
be determined for each camera.
Optimum PAM positions will
We will monitor focus stability
and maintain NICMOS best focus.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS:
No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.9
ID:
NICMOS Aperture Locations
NICMOS-10
APPLICABLE SMOV REQUIREMENT: J.10.4.4.2.1
DESCRIPTION: Observations of a standard astrometric field
will be obtained to establish the locations of the NICMOS camera
apertures in the vehicle (V2,V3) reference frame, with accuracy
of +/- 2 arcseconds.
The test will be repeated after an interval
of at least 28 days, to monitor temporal evolution, as a function
of focus position.
At least 3 stars must be observed on each
NICMOS camera. A series of exposures at offset field pointings
will be taken to facilitate the location of the NICMOS apertures
and to measure the rotation angle of the apertures.
Each
measurement shall be done at each Camera's best focus (best
PAM/FOM position, tentatively NIC1/2 and NIC3)
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 6 orbits
DATA REQUIREMENTS: 50 MB
ANALYSES & RESULTS: Measurement of star positions in images will
provide astrometric reference positions.
PDB update of NICMOS SIAF definitions.
The result will be a
Test will determine
NICMOS aperture positions in the HST focal plane.
blind pointing to ~2 arcseconds rms.
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RESPONSIBLE PARTIES:
COMMENTS:
STScI NICMOS group
No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.10
ID:
NICMOS Plate Scale
NICMOS-11
APPLICABLE SMOV REQUIREMENT: J.10.4.4.3.1
DESCRIPTION: Measure the plate scale, field rotation and field
distortion for each NICMOS camera.
solution will also be found.
The intercamera astrometric
Observations of an astrometric
field will be obtained in all three cameras.
The optical plate
scales at each of the detector focal plane shall be measured with
a precision of 0.25 NIC2 pixel (18.8 mas).
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 4 orbits
DATA REQUIREMENTS: 100 MB
ANALYSES & RESULTS: Measurement of star positions; update of
NICMOS SIAF entries; if necessary, update of NICMOS FSW in
support of Mode 2 Target Acquisition. Plate scales, field
rotation, and field distortions will be derived for each Camera.
The inter-camera astrometric solution will be improved.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.11
ID:
NICMOS Mode 2 Target Acquisition Test
NICMOS-12
APPLICABLE SMOV REQUIREMENT: J.10.4.4.2.2
DESCRIPTION: This test is designed to validate the ability of the
Mode 2 acquisition process of positioning the brightest wellexposed point target in a 128x128 pixel acquisition region within
1/4 pixel (18.5mas) of the center of the coronagraphic hole.
Mode 2 acquisition to be performed on a bright star and on a
double star
(in a field containing several stars) in Camera 2.
For each target, acquisitions will be performed with three
exposure times to investigate centroiding in saturation and
underexposure regimes as well as well-exposed images.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Aperture Location (NICMOS-10), NICMOS Plate
Scale (NICMOS-11)
DURATION: 4 orbits
DATA REQUIREMENTS: TBD
ANALYSES & RESULTS: Acquisition images will be examined.
Validation of NICMOS flight software for Mode 2 target
acquisition.
Validation of target location, centroiding,
coordinate transformation.
Verify ability of target to be
positioned within 1/4 pixel (18.5mas) of the center of the
coronagraphic hole.
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RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.12
ID:
NICMOS Coronagraphic Performance
NICMOS-13
APPLICABLE SMOV REQUIREMENT: J.10.4.4.2.2
DESCRIPTION: A series of stellar images will be taken in a
pattern with displacements as small as 1/4 pixel behind and near
the Camera 2 occulting spot.
Exposures will be sufficiently deep
to allow determination of the magnitudes of both the diffracted
energy rejection outside of the hole and the scattering floor, as
well as to look for local structures in the PSF as a function of
target decentration.
Wavelength dependent characteristic will be
examined in the F110W, F160W and F187N filters. Measurements will
be obtained using telescope roll angles of +/-18 degrees.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Mode 2 Target Acquisition Test (NICMOS-12)
DURATION: 6 orbits
DATA REQUIREMENTS: N/A
ANALYSES & RESULTS: Measurement of diffractive energy rejection
and scattering.
Determination of achievable local and global
source/background contrast ratios near the coronagraphic hole.
Validation of Coronagraphic performance to pre-NCS levels.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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ID:
NICMOS Internal Flats
NICMOS-14
APPLICABLE SMOV REQUIREMENT: J.10.4.4.1.2, J.10.4.4.4.1
DESCRIPTION: Pointed observation of a blank field target in each
camera with the internal calibration lamps both on and off. At
each position a 9-position dither will be used to remove
background sources.
measured once.
All wide and medium band filters will be
The test will be repeated after 4-8 weeks to test
stability when a subset of two filters per camera will be
checked.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS final set point determined
DURATION: 8 orbits (TBR)
DATA REQUIREMENTS: 1600 MB
ANALYSES & RESULTS: Assemble flat fields from dithered images.
Remove background sources using lamp off exposures. Demonstration
of flat fielding capability and stability using the internal
flat-field lamps.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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ID:
NICMOS Photometry Test
NICMOS-15
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.2, J10.4.4.4.3
DESCRIPTION: Observations of standard stars (one solar analog and
one white dwarf) at 5 wavelengths spanning the NICMOS wavelength
range (0.8 to 2.5 microns).
The observations will be obtained in
MULTIACCUM mode. This must be done in each camera, at the best
focus position of the camera.
In addition, one standard star
will be observed in each camera in one filter in a 5 by 5 grid
spanning 2/3 of that camera's field of view. This part of the
test will be repeated after 30 +/- 5 days to check stability.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 16 orbits
DATA REQUIREMENTS: 200 MB
ANALYSES & RESULTS: Measurement of flux from stellar images.
Throughput calibration for the NICMOS/NCS configuration.
Update of CDBS. Inter-camera photometric precision and stability.
The stated goal is 3% relative photometric accuracy.
stability over 30 days.
RESPONSIBLE PARTIES: STScI NICMOS group
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COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.15
ID:
NICMOS SAA CR Persistence Test
NICMOS-16
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.8
DESCRIPTION: A series 10 of MULTIACCUM dark frames spanning 20
minutes each will be obtained in parallel in all three cameras,
taken in pairs upon exiting the SAA and after the flight software
delay imposed for SAA persistence reduction.
The 10 darks will
cover a range orbital characteristics relative to the SAA.
The
MULTIACCUM sequences will be identical to those used in the
Detector Read Noise/ Shading/ Cosmic Ray Test.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS final set point determined
DURATION: 5 orbits
(could be scheduled as internals)
DATA REQUIREMENTS: 42 MB
ANALYSES & RESULTS: Measure deviations from gaussian distribution
of darks.
Measure timescales for returning to `nominal’
situation. Measurement of decay timescale for image persistence
due to cosmic rays.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.16
ID:
NICMOS Astronomical Persistence Test
NICMOS-17
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.8
DESCRIPTION: Long exposures of a bright star will be obtained
with each camera in MULTIACCUM mode.
Overexposure levels of 300-
500 times linear full well will be obtained.
The observation
sequence will be an overexposure, a 5-minute dark, a second
overexposure, and three 20-minute darks, all in MULTIACCUM.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 3 orbits
DATA REQUIREMENTS: 62 MB
ANALYSES & RESULTS: Measurement of residual signal level in dark
frames. Measurement of PSF to large radii. Measurement of effects
of severe overexposure of NICMOS detectors.
Measurement of the
outer portions of the PSF to determine dynamic range of NICMOS.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.17
ID:
NICMOS Thermal Background
NICMOS-18
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.7
DESCRIPTION: Observations in Camera 3 in the filters F110W,
F175W, F240M, F222M, F160W will be obtained at a variety of
spacecraft attitudes to characterize the thermal background light
from HST+Instrument which reaches the NICMOS focal plane.
In
addition, Camera 3 pure parallel exposures in the F222M filter
will be obtained for the entire duration of SMOV to establish the
stability of the HST+Instrument thermal emission.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NCS final set point determined
DURATION: 12 orbits (primary), 100 orbits (pure parallel)
DATA REQUIREMENTS: 1000 MB
(TBR)
ANALYSES & RESULTS: Measurement of background in each image
following removal of sources (accomplished by both multiple
positions (dithers) and multiple wavelength observations).
Measurement of the impact and stability of the HST+Instrument's
thermal emission under the new NICMOS/NCS configuration.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS:
If suitable attitudes are available, the pointed
orbits could be done as parallels.
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AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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2.13.18
ID:
NICMOS Grisms Absolute Sensitivity
NICMOS-19
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.9
DESCRIPTION: Observations of standard stars (one solar analog and
one white dwarf) will be obtained in two NICMOS grisms, G096 and
G141, and in the associated broad/medium band filters, at 5
positions on the detector, at the best NIC3 focus.
The
observations will be obtained in MULTIACCUM mode.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 2 orbits
DATA REQUIREMENTS: 145 MB
ANALYSES & RESULTS: Measurement of flux from star images and
spectra. Throughput calibration for the grisms in the NICMOS/NCS
configuration. Update of CDBS.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
DATE: January 12, 2001
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ID:
NICMOS Grisms Wavelength Calibration
NICMOS-20
APPLICABLE SMOV REQUIREMENT: J.10.4.4.4.9
DESCRIPTION: Observations of the planetary nebula Hb12 (or Vy2-2)
will be obtained in two NICMOS grisms, G096 and G141, and in the
associated broad/medium band filters, at 4 positions on the
detector, at the best NIC3 focus.
The observations will be
obtained in MULTIACCUM mode.
IMPLEMENTATION METHOD: Proposal, SMS
DEPENDENCIES: NICMOS Fine Optical Alignment (NICMOS-06), NIC3
Fine Optical Alignment (NICMOS-07)
DURATION: 2 orbits
DATA REQUIREMENTS: 33 MB
ANALYSES & RESULTS: Measurement of the position of the emission
lines. Mapping of wavelengths onto detector's pixels.
of the dispersion solution.
the two NICMOS grisms G096
Derivation
Wavelength dispersion solution for
and G141.
Update of CDBS.
RESPONSIBLE PARTIES: STScI NICMOS group
COMMENTS: No additional comments.
AUTHOR/TELEPHONE/EMAIL:
Keith Noll, 410-338-1828, noll@stsci.edu
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2.14
NICMOS COOLING SYSTEM
Table 2-8 shows the verification activity that must be accomplished
during SMOV to verify the performance after the installation of the
NCS to support normal operations.
Table 2-8
Verification Activity for the NICMOS Cooling System
Activity
Summary #
NCS-01
Observatory
Verification Activity
Start NICMOS Cooling System (NCS)
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Phase
Hr:min
Real-Time
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ID:
Start NICMOS Cooling System (NCS)
NCS-01
APPLICABLE SMOV REQUIREMENT: J.10.4.4.5.1, J.10.4.4.5.2,
J.10.4.4.5.3, J.10.4.4.6.1, and J.10.4.4.6.2
DESCRIPTION:
Purpose:
Configure the NCS to re-cool the NICMOS detectors, determine the
optimal science operating temperature for the NICMOS detectors,
and verify stable operation.
Goals:
1) Cool the NICMOS to the coldest possible temperature with HST
at a hot attitude and the NCC compressor operating near its
maximum allowable speed.
2) Measure NICMOS detector performance during the cool-down and
steady state operation of the NCS.
3) Demonstrate stability (+/-0.1K) of the NICMOS detector
temperature at the optimal science operating temperature.
4) Demonstrate repeatability (+/-0.1 K) of NICMOS detector
temperature following changes from the optimal science operating
temperature.
Methodology:
Execute step 1 of VDT (at least 1 full orbit at +V3 sunpoint
prior to NCC operation while moving the ACS Filter Wheel).
Execute step 2 of VDT (at least 1 full orbit at +V3 sunpoint
prior to NCC operation with no filter wheel motion).
As early as possible in the BEA period:
1) Start the NCS CPL.
Execute step 3 of VDT (at least 1 full orbit at +V3 sunpoint
during NCC startup).
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2) Start the NCC circulator.
3) Start the NCC compressor.
4) With the NCC compressor max speed at its default value (7300
rps.), set the NCC PID control set point to 60 K, controlling off
of the weighted average of the neon temperatures.
This will
result in the fastest cool-down.
5) 24 hours after the NCC cool-down is begun, begin taking NICMOS
detector internal temperature monitoring observations (30-minute
dark, 0-sec bias exposures, FPA temperature, mounting cup
temperature) once per orbit until the conclusion of the test [148
hr after start of cooldown (TBR)].
6) 76 hours (TBR) after the NCC cool-down is begun, slew HST to
the sun angle and roll (consistent with the BEA constraints) that
produce the warmest mean NCS radiator temperature.
Maintain this
attitude for 72 hours (TBR).
7) 90 hours after the NCC cool-down is begun, set the NCC
compressor max speed to 7250 rps (normal max speed is 7300 rps)
and keep the NCC PID control set point at 60 K.
This will cause
the compressor to run at a fixed speed of 7250 rps. and will
result in an asymptotic cool-down to the lowest temperature that
can be reached at this speed and under these thermal conditions.
No HST attitude requirements pertain to steps 8-15.
8) 148 hours (TBR) after the NCC cool-down is begun, set the NCC
PID control set point to 3.0 K warmer than the temperature
reached and the NCC compressor max speed to 7300 rps.
This will
put the NCC under active PID control at a controlled operating
temperature.
Maintain this set point for 48 hours (TBR). (Note:
This configuration is a normal operational configuration and can
be maintained indefinitely.)
Steps 9-11 verify the repeatability of the NICMOS detector
temperature:
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9) Increase NCC PID control set point by an amount that
corresponds to 0.5 K at the NICMOS detector and maintain this
temperature for 48 hours (TBR).
10) Decrease NCC PID control set point by an amount that
corresponds to 1.0 K at the NICMOS detector and maintain this
temperature for 48 hours (TBR).
11) Increase NCC PID control set point by an amount that
corresponds to 0.5 K at the NICMOS detector and maintain this
temperature for 48 hours (TBR).
Execute step 4 of VDT (at least 5 full orbits a +V3 sunpoint
while NCC is operating at steady state).
Execute step 5 of VDT (at least 5 full orbits at –V1 sunpoint
while NCC is operating at steady-state).
Two weeks after the end of the BEA period:
12) Set the NCC PID control set point to the temperature that
corresponds to the NICMOS detector optimal science operating
temperature as determined from analysis of the data taken in step
7.
This temperature will depend on NCS and NICMOS detector
performance.
Maintain this set point for 48 hours (TBR).
13) Concurrent with steps 8-12, take NICMOS detector internal
temperature monitoring observations once per orbit.
14) At the end of the 48-hr stabilization interval, take
continuous NICMOS detector internal temperature monitoring
observations for 1 orbit to demonstrate +/-0.1K stability at the
science operating temperature (known as rapid monitor data
takes).
15) Continue NICMOS detector internal temperature monitoring
observations once every three orbits for 1 month (150 samples) to
demonstrate +/-0.5K stability at the science operating
temperature.
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IMPLEMENTATION METHOD: Real-time commanding for NCS operations.
Proposal for NICMOS measurements.
DEPENDENCIES:
1) Fill NCS circulator neon loop (done in servicing mission command
plan)
2) Perform STIS baseline measurements.
3) A Vehicle Disturbance Test (VDT) is planned in regards to NCC
startup. The following are the requirements in conjunction with
NCC startup:
a) at least 1 full orbit at +V3 sunpoint prior to NCC
operation while moving the ACS Filter Wheel
b) at least 5 full orbits at +V3 sunpoint prior to NCC
operation with no filter wheel motion
c) at least 1 full orbit at +V3 sunpoint during NCC startup
d) at least 5 full orbits at +V3 sunpoint while NCC is
operating at steady-state
e) at least 5 full orbits at -V1 sunpoint while NCC is
operating at steady-state
4) ACS CCD Functional
5) FGS Jitter Baseline
DURATION:
Starting the NCS CPL requires approximately 3 hours of sparse
real-time commanding. Starting the NCC circulator and compressor
requires approximately 1 hour of real-time commanding. The NCC
cool-down during the BEA requires approximately 148 hours.
The
final 76 hours of this is at a specified attitude.
The NCS stability and repeatability steps require approximately
15 days.
There are no related HST attitude requirements and
these steps can be done in parallel with other activities.
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DATA REQUIREMENTS:
Several NCS history buffer dumps for NCS start-up (8 Kbytes/dump)
NICMOS detector data:
Once-per-orbit internal temperature monitor: DARK = 30-min dark, 3
detectors = 12.5 MB. BIAS = 2 x 100 0-sec exposures, 1 detector =
32 MB. There is no additional data volume for FPA and mounting cup
temperature.
Daily data volume = 15 orbits of 3-detector DARK + 15 orbits of 1detector BIAS + 1 orbit of 2-detector BIAS = 15*12.5 + 15*32 + 2*32 =
731.5 MB.
One orbit rapid monitor: 88 MB.
ANALYSES & RESULTS:
The CHAMP Thermal group will analyze NCS thermal performance.
The BEA
NCS cool-down and steady state data will be used to determine the
coldest NCC Cold Load Interface temperature that the NCS can maintain
under active PID control in all expected thermal environments.
Analysis is expected to require two weeks.
Results of this analysis
are required for the stability and repeatability parts of this
activity, which begin after the BEA period.
The STScI NICMOS team will analyze NICMOS detector performance.
NICMOS detector data from the BEA cool-down period will be used to
determine the detector temperature that will provide the optimal
science data by trading detector quantum efficiency and dark current
and considering the minimum sustainable NICMOS temperature.
is expected to require two weeks.
Analysis
Results of this analysis are
required for the stability and repeatability parts of this activity,
which begin after the BEA period.
NICMOS detector data from the post-BEA period will be used to
determine detector temperature stability and repeatability.
is expected to require one week.
Analysis
Results of this analysis are
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required prior to beginning NICMOS calibration and science
observations.
COMMENTS:
The TBRs associated with the various event times in
the “Methodology” section will be resolved by 05/31/01 when the
MOSES Thermal Group has finished their analysis.
AUTHOR/telephone/email: Ken Pulkkinen, (301) 901-6152,
kpulkkinen@hst.nasa.gov
DATE: March 29, 2001
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2.15
WIDE FIELD/PLANETARY CAMERA 2
Table 2-9 shows the verification activities that must be accomplished
during SMOV to verify the performance of the Wide Field/Planetary
Camera 2 (WFPC2) to support normal science operations.
Table 2-9
WF/PC-2 SMOV Activities
Activity
Summary #
WFPC2-01
Execution Duration
Observatory Verification Activity
WFPC2 Transition From Protect Safe
Phase
Hr:min
SMS
20:00
SMS
31:30
Mode to Hold Mode to Protect
Decontamination Mode
WFPC2-03
WFPC2 Contamination Monitor, Cool
Down, and Focus Check
WFPC2-04
WFPC2 Lyman Alpha Check
SMS
03:00
WFPC2-05
WFPC2 Flat Field Calibration
SMS
10:00
WFPC2-06
WFPC2 Relative Photometry Calibration
SMS
06:00
WFPC2-07
WFPC2 Point Spread Function
SMS
04:30
SMS
24:00
Verification
WFPC2-08
WFPC2 Internal Monitor
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WFPC2 Transition from Protect Safe Mode to Hold Mode, to
Protect Decontamination Mode
ID:
WFPC2-01
APPLICABLE SMOV REQUIREMENT: J.10.4.1.1.1
DESCRIPTION: Recover WFPC2 from Protect Safe to Hold. Configure
power relays, clear and reset safing status bits, enable and
execute application processor limit checking, turn LVPS on,
initialize microprocessor, select SDF I/F, enable microprocessor
idle checking and bay 1 temperature control. After transitioning
to Hold, begin real-time microprocessor memory collection for
PROM and RAM.
SMS has an appropriate wait time for RAM dump and
verification.
After RAM validation and while WFPC2 is in Hold
mode, initiate Protect decontamination transition. Enable CCD
heaters on, position filter F785LP in optical path, close shutter
blade A, enable radiator heat pipe heaters on.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: Completion of SM3B activities
DURATION: 20 Hours
DATA REQUIREMENTS: Availability of serial telemetry data, and RAM
and PROM memory dumps.
ANALYSIS: 1. Perform engineering matrix verification (commanding,
application processors, microprocessor, mechanism, and error
messages), 2. Perform dump and miscompares on RAM and PROM data,
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3. Monitor thermal and power performances, 4. Monitor camera
decontamination thermal profile.
RESULTS: 1. Verify nominal operation of WFPC2, 2. Place WFPC2 in
protective decontamination state with CCD camera temperatures at +22
C.
COMMENTS: N/A
AUTHOR/TELEPHONE/EMAIL: Sito Balleza, STSCI ESS,
Balleza@stsci.edu 410-338-4532
DATE: January 16, 2001
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2.15.2
ID:
WFPC2 Cool Down, Contamination Monitor, and Focus Check
WFPC2-03
APPLICABLE SMOV REQUIREMENT: J.10.4.1.1.2, J.10.4.1.1.3
DESCRIPTION: After 24 hours in Protect Decon mode (Activity
WFPC2-01), the camera is cooled down to the standard operating
temperature of -88C. The cool down is timed to end shortly after
the end of the BEA restrictions.
The expected growth of UV contamination is monitored with
observations of a standard star, initially very frequent, then
progressively less frequent as better information on the
contamination monitor is obtained.
UV monitoring observations
will be taken at 0, 3, 6, 12, 18, 24, 36, and 48 hours, 3, 4, 5
and 6 days from the end of cool down.
The camera will undergo
planned decontamination procedures (PROTECT DECONs) 7, 14, and 28
days after cool down.
Observations include a set of internals
(darks, biases, INTFLATs, KSPOTs) after the initial cooldown and
after each decontamination.
The focus check consists of three separate sets of F555W
observations of the standard star, starting shortly after
cooldown and spaced by about 24 hours.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2-01; End of BEA
DURATION: Total of 21 external orbits, as follows:
- 12 orbits for UV contamination monitoring
- 3 orbits for focus check
- 6 orbits for pre- and post-decon photometry verification
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Total of 50 hours of internals, as follows:
- 36 hours for the three decons
- 10 hours for darks (4 sets of 5 darks each)
- 4 hours for other internals (4 sets)
DATA REQUIREMENTS: Estimated total of 260 images
ANALYSES & RESULTS:
- Trend UV throughput (expected accuracy better than 1% per
epoch)
- Verify photometry before and after each decon
- Determine contamination rates
- Measure focus position using phase retrieval
COMMENTS:
WFPC2 is enabled for science observations after the
first 24 hours of UV monitoring.
IMPORTANT: UV monitoring data within the first 24 hours after
cooldown are QUICKLOOK - must be made available to
Instrument Scientist within 6 hours of observation,
and analyzed within an additional 6 hours.
IMPORTANT: UV monitoring data within the first week, focus data
Must be delivered within 12 hours
IMPORTANT: If contamination is detected that would result in
loss of 30% of the UV throughput at F170W, the camera
will be safed via real-time commands, as in the WFPC2
contingency plan.
AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE: January 16, 2001
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2.15.3
ID:
WFPC2 Lyman Alpha Check
WFPC2-04
APPLICABLE SMOV REQUIREMENT: J.10.4.1.2.2
DESCRIPTION: The WFPC2 primary standard GRW+70d5824 is observed
in the far UV with filters F160BW, F122M by themselves and
crossed with F130LP to assess Lyman alpha contamination, with an
expected measurements error of about 5%.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2 enabled for science observations (WFPC2-03,
Cooldown plus 24 hours UV monitoring)
DURATION: 1 external orbit
DATA REQUIREMENTS: 17 images
ANALYSES & RESULTS: The UV photometry is compared with pre-SMOV
measurements, both for the UV filters and for the UV filters
crossed with F130LP.
Flux decrease in the UV observations, but
not in the UV crossed with F130LP, is indicative of Lyman alpha
contamination.
COMMENTS: Because of the small impact of Lyman alpha observations
on WFPC2 science, we do not plan a return to BEA if
low-level contamination (5-10%) is detected.
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AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE:
January 16, 2001
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2.15.4
ID:
WFPC2 Flat Field Calibration
WFPC2-05
APPLICABLE SMOV REQUIREMENT: J.10.4.1.2.3
DESCRIPTION: External (Earth) flat fields will be obtained for
the four narrow-band filters F375N, F502N, F656N, and F935N (20
images each) after the end of the BEA phase.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2 enabled for science observations (WFPC2-03,
Cooldown plus 24 hours UV monitoring)
DURATION: 10 hours, non-contiguous
DATA REQUIREMENTS: 80 images
ANALYSES & RESULTS: Flat fields in each filter will be combined
to remove cosmic rays and streaks.
Images will be compared with
pre-SM3 images to quantify stability and measure any changes that
may have occurred.
Check for changes in flat field.
Update
pipeline flat field calibration (not a prerequisite for further
SMOV activities).
COMMENTS: N/A
AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE: January 16, 2001
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2.15.5
ID:
WFPC2 Relative Photometry Calibration
WFPC2-06
APPLICABLE SMOV REQUIREMENT: J.10.4.1.2.2
DESCRIPTION: The WFPC2 primary standard GRW+70d5824 is observed
through F160BW, F170W, F185W, F218W, F255W, F300W, F336W, F555W,
F675W, and F814W in all four cameras.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2 enabled for science observations
DURATION: 4 orbits
DATA REQUIREMENTS: 44 images
ANALYSES & RESULTS: Aperture photometry will be performed on each
image to measure instrument response and throughput.
Results
will be compared with historic pre-SMOV photometry results.
Update pipeline and database photometric tables if required; this
is not a prerequisite for further SMOV activities.
COMMENTS: Must execute shortly (1-2 days) after a
decontamination.
AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE: January 16, 2001
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2.15.6
ID:
WFPC2 Point Spread Function Verification
WFPC2-07
APPLICABLE SMOV REQUIREMENT: J.10.4.1.2.1, J.10.4.1.2.4
DESCRIPTION: Exposures over a wide dynamic range of a bright star
through a wide-band filter (F555W) will be obtained in order to
characterize the extended wings of the PSF.
Exposures will also
be made of a crowded stellar field with sub-pixel stepping to
provide a critically sampled PSF.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2 enabled for science observations
DURATION: 3 orbits
DATA REQUIREMENTS: 33 images
ANALYSES & RESULTS: The PSF will be reconstructed by DRIZZLE and
checked against both theoretical models (TinyTim) and pre-SMOV
observations. Linearity will be checked by comparing PSFs taken
at different count levels.
COMMENTS: N/A
AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE: January 16, 2001
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2.15.7
ID:
WFPC2 Internal Monitors
WFPC2-08
APPLICABLE SMOV REQUIREMENT: J.10.4.1.2.3
DESCRIPTION: Routine internal observations will be obtained to
monitor the basic instrument health and its optical alignment via
K-spot observations, to verify the stability of the calibration
and INTFLAT channels, and to check for contamination.
Initial
execution will include bias frames, darks, K-spot images,
INTFLATS and VISFLATS in F555W.
Once the prerequisites for UV
operation have been met, two F170W UV flat fields will be
obtained.
These data will be obtained weekly, compatibly with
SMOV activity levels, with the exception of VISFLATS and UV flats
which will only be obtained once because they use limited
lifetime items.
IMPLEMENTATION METHOD: Proposal
DEPENDENCIES: WFPC2 enabled for science observations
DURATION: 24 hours of internal observations; 2 external orbits
(used for UVFLAT scheduling)
DATA REQUIREMENTS: 49 images
ANALYSES & RESULTS: Compare each set of observations (bias, dark,
K-spot, intflat, visflat, UV flat) with pre-SMOV data to check
for changes in instrument performance.
Weekly images throughout
SMOV will be compared to identify and trend any changes.
2-179
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COMMENTS: This proposal covers normal internals (DARKs, BIASes,
INTFLATs, KSPOTs) during non-decon weeks, as well as the INTFLATs
and UVFLATs which are executed only once during SMOV.
Both
INTFLATs and UVFLATs require the use of limited lifetime items.
UVFLATs must not be scheduled within 12 hours of a
decontamination.
UVFLAT observations require contiguous darks,
therefore blocking an opportunity for external observations, and
thus are counted as 2 external orbits.
AUTHOR/telephone/email:
Stefano Casertano / (410) 338-4752 /
stefano@stsci.edu
DATE: January 16, 2001
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2.16
EARLY RELEASE OBSERVATIONS
The Early Release Observations (ERO) program will be conducted to
demonstrate that after SMOV, HST is still capable of producing the
superb images and premier science for which it has become celebrated.
The ERO activities list is shown in Table 2-10.
Table 2-10
ERO Activities
Activity
Observatory
Summary #
Verification Activity
ERO-01
Early Release Observations
2-181
Execution Duration
Phase
SMS
Hr:min
TBD
SMR-3029
Draft
March 30, 2001
2.16.1
ID:
Early Release Observations
ERO-01
APPLICABLE REQUIREMENTS: J.10.4.6
DESCRIPTION: The Early Release Observations (EROs) are intended to
demonstrate that after SMOV, HST is still capable of producing the
superb images and premier science for which it has become celebrated.
BEST IMPLEMENTED AS: SMS Proposal
DEPENDENCIES: The EROs will be performed with ACS and NICMOS;
therefore, they should be done after requirement ACS-11 is completed
and NICMOS requirements NICMOS-21 and NICMOS-34 are completed and
operating nominally.
DURATION: TBD
RESULTS: Images of astronomical objects, and a description of the
contents of the images; the latter will discuss how the images show
the continued ability of HST to advance our knowledge of the universe.
ANALYSIS: ACS and NICMOS images will be obtained and released through
the coordination of the STScI/GSFC, NASA Headquarters, and the science
teams.
AUTHOR/ORG/TEL: Andrew Fruchter, STScI, fruchter@stsci.edu, 410-3385018
DATE:
January 18, 2001
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3.
SMOV NOMINAL TIMELINE
This section presents the milestone schedule and the nominal
high level timeline for conducting the planned SMOV activities.
Figure 3-1 presents the SMOV Timeline Summary, while Table 3-1
presents the SMOV Milestone.
The SMOV timeline is presented in a set of tables containing
the SMOV activities and the planned order of execution during
the Real-time, Health and Safety, and SMS Phases of SMOV.
Figure 3-2 is a SMOV Activity Dependency Network that
graphically presents the dependencies for the SMOV key
activities listed in the Section 3 tables.
The network chart
allows the SMOV Management Team to continually measure the
progress of SMOV, and also react to contingency situations,
since the activity dependencies are already known.
The
schedule provides some contingency time for completing SMOV
operations.
The ST ScI will schedule appropriate non-SMOV
science observations to utilize available time each week.
3-1
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March 30, 2001
Table 3-1
SMOV Milestone Schedule
WFPC2 Milestones
WFPC2 Science Enable
Launch + 27 days
STIS Milestones
STIS CCD Science Enabled
STIS MAMA Science Enabled
Launch + 23 days
Launch + 30 days 8 hours
PCS Milestones
PCS/OTA Configured
Launch + 22 days
NCS Milestones
NCS Set Point Determined
Launch + 33 days
NICMOS Milestones
NICMOS ERO Enable
NICMOS GO Science Enable
Launch + 42 days
48 days
ACS Milestones
ACS ERO Enable
ACS PRD Aperture Location
Updates
ACS SBC Science Enable
ACS CCD Science Enable
Launch + 39 days
Launch + 68 days
Launch + 69 days
Launch + 69 days
3-2
SMR-3029
Draft
March 30, 2001
HST RELEASE
12
BEA
20
WFPC2
WFPC2 SCIENCE
DECON, C/O, CALIBRATION
16
STIS
ALIGNMENT, FOCUS, C/O, CALIBRATION
STIS CCD SCIENCE
23
STIS
ALIGNMENT, FOCUS, C/O, CALIBRATION
STIS MAMA SCIENCE
26
NCS
SET POINT DETERMINED
41
NICMOS
NICMOS SCIENCE
GO SCIENCE ENABLED
61
ACS
APERTURE LOCATION UPDATES
62
ACS
ALIGNMENT, FOCUS, C/O, CALIBRATION
ACS SBC SCIENCE
62
ACS
ALIGNMENT, FOCUS, C/O, CALIBRATION
ACS CCD SCIENCE
LEGEND:
# DAYS:HOURS SINCE HST RELEASE
Figure 3-1 SMOV Timeline Summary
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-
SMR-3029
Draft
March 30, 2001
Table 3-2
Sample Activity Table
Activity Name and
Duration
Identification Number
(Days)
HST Release from
Type of
Dependent On
Dependency
3
FS
Orbiter
Transition to Software
2
HST Release from
Sunpoint Mode (D028)
•
FS
Orbiter
Activity Name and Identification Number - Title of the
basic function to be performed, with its assigned unique
identification number.
•
Duration - Expected time to complete the activity, shown
in either days or hours.
•
Dependency - Provides the title of the activity upon
which that function is dependent.
In many cases, there
are multiple activities, which must be completed prior to
initiating a specific task.
•
Dependency Type - Two types of dependencies were used in
preparing this plan, Finish-to-Start and Start-to-Start.
A Finish-to-Start dependency requires a preceding
activity to be completed prior to initiating its
dependent activity.
A Start-to-Start dependency means
that the dependent activity may be started any time after
the preceding task is started.
3-5
SMR-3029
Draft
March 30, 2001
3.1
REAL-TIME COMMAND PHASE
The Real-time Command Phase is the shortest phase of the SMOV
program and covers from HST release from the Orbiter RMS, to
activation of the Health and Safety SPC Load.
It primarily
consists of the basic operations that are normally used to
recover the HST from a PSEA safing.
The majority of activities
during this phase require relatively short execution periods, so
durations in the activity tables are expressed in minutes.
The
Real-time Command Phase is planned to be completed within
approximately 36 hours, to alleviate any unnecessary pressure
caused by keeping to a specific schedule.
If no anomalies are
encountered, Real-time activities can be performed within
reasonable time limits after due consideration of safety issues.
3.1.1
Real-Time Command Phase Activity Table
The activities in the Real-time Command Phase following HST
release are shown in Table 3-3.
3.2
HEALTH AND SAFETY SPC PHASE
The Health and Safety SPC Phase begins once the uplinked Health
and Safety Load is activated and HGA tracking is initiated, and
terminates when the HST is configured to fully support normal
operations via an SMS generated SPC load.
The Health and Safety
SPC Phase is planned to take approximately one day to complete,
and allows for a low pressure schedule to complete both on orbit
activities as well as processing of data by the ground system to
prepare for science operations.
As with the Real-time Command
Phase, if no anomalies are encountered, successive tasks may be
performed ahead of schedule after due consideration of safety
3-6
SMR-3029
Draft
March 30, 2001
issues.
The Health and Safety SPC Phase Activity are shown in
Table 3-4.
3-7
SMR-3029
Draft
March 30, 2001
Table 3-3
Real-Time Command Phase Activity Table
Activity Name
Duration
(Minutes)
HST Release from orbiter
Transition to Normal
Mode
3
9
Reconfigure HST LGA
Direct TDRSS
Maneuver to Bright Earth
Avoidance Attitude
19
16
Configure MCU and
RETR/DEPL HTRS for
Normal Ops
8
Turn On FGEs After
Deploy
FHST FOV Check
7
Enable Battery SOC SM
Tests
Attitude Determination
for First HLGBU
Dependent On
HST in Software
Sunpoint.
Vehicle Body
Rates < 30
arcsec/sec.
HST in Software
Sunpoint.
Transition to
Normal Mode and
Coarse Attitude
Determination
Complete
Aperture Door
Open, HST in
Software
Sunpoint
Type of
Dependency
FS
FS
FS
FS
FS
20
I & Q Channels
Uncombined
3
FS
FS
120
Re-Center HGA Gimbals
9
First LGBU/HGBU
10
Attitude Determination
2nd ARU
100
3-8
FHSTs are
Operational and
sufficient FHST
Visibility to
Determine Drift
HGAs Deployed,
HGA CTRL Laws
Enabled, GEAs On
R/T FHST Maps
for HGBU and
LGBU Completed
and PASS
Generated Table
Load Available
FHSTs are
Operational
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-3
Real-Time Command Phase Activity Table (Continued)
Activity Name
Load Ephemeris
Duration
(Minutes)
Dependent On
5
Current On-Board
Ephemeris Tables
Have Been
Previously
Loaded with an
Epoch Time Less
Than 6 Days From
New Epoch Time.
Fine Attitude
Determination is
Complete
PCS/FSW
Configured for
Normal Ops.
STIS TEC Set
Point to –67 deg
updated and the
Detector has
Stabilized
None
Transition to Normal Ops
Uplink 2nd ARU
20
Enable B.O.P. Test
4
STIS/NCS Noise Test
(Post Baseline)
200
Safe SIs Before NCC
Fill-Operations
Fill NCC Circulator Loop
12
30
Load Health and Safety
SPCs
(First Opportunity)
7
Attitude Determination
For 2nd HLGBU & 3RD ARU
10
3-9
ESM In Operate
Mode
SSAR Service
Available with 4
KBPS AN Format
Active on Q
Channel
Available for 4
KBPS Memory
Dump. I & Q
Channel
Uncombined
None
Type of
Dependency
FS
FS
FS
FS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-3
Real-Time Command Phase Activity Table (Continued)
Duration
(Minutes)
Dependent On
Activity Name
Second LGBU/HGBU and ARU
10
Configure HST HGA Direct
TDRSS
-Initiate HGA Pointing
Mgmt HGA/TDRS
-Configure SSA TX 1 & 2
for SN Ops
9
R/T FHST Maps
for HGBU and
LGBU Completed
and PASS
Generated Table
Load Available
TDRSS Service
Scheduled SSAF
(H04) /SSAR
(L23), HST H&S
Load has been
uplinked and
started, HGAs
have been
splined to
TDRSS-Intercept
Angles, HGA
Gimbal Angles,
verified correct
per PASS .RGM
Report
3-10
Type of
Dependency
FS
FS
SMR-3029
Draft
March 30, 2001
3.2.1
Health and Safety SPC Phase Activity Table
The activities in the Health and Safety SPC Phase are shown in
Table 3-4.
Please note that some activities in the far left
column have multiple dependent tasks.
The key activities in this
phase are activation of the Health and Safety SPC load, which
provides for HGA tracking of TDRS and completing the flight
software transition to support science operations.
3.3
SCIENCE MISSION SPECIFICATION COMMAND PHASE
The Science Mission Specification Command Phase begins once the
first SPC loads generated from the first ST ScI SMS begins to
execute, and terminates upon transition to normal science
operations.
The majority of activities during the SMOV program
are executed during the SMS phase, and the activities are
generally of much longer duration than the previous two phases,
the time unit used to show activity duration is days or hours.
Tables 3-5 lists the activities planned for the SMS phase of
SMOV.
3.3.1
SMS Command Phase Activity Table
The SMOV activities for the SMS Command Phase are shown in Table
3-5.
3-11
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March 30, 2001
Table 3-4
Health and Safety SPC Phase Activity Table
Activity Name
Health and Safety
Load Activated
Configure SSA
Transmitters
Configure HST HGA
Direct TDRSS
Load NSSC-1 5 SI S/W
Verify 486 TLM
Formats
FHST/FHST Alignment
(Data Processing)
Normal Ops via STScI
SMS Generated SPC
Loads
Duration
Dependent On
(Minutes)
0
Load Health and
Safety
SPCs/Initialize
Attitude
2
Health and Safety
Load Activated
6
Type of
Dependency
FS
FS
FS
2
60
FS
FS
1440
FS
0
Verify TLM Formats
Star Trackers
Aligned
Health and Safety
Load Activated
Polarity Slews
Configure HST HGA
Direct TDRSS
SSR1 Sci & Eng
Recording
3-12
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March 30, 2001
Table 3-5
SMS Command Phase Activity Table
Activity Name
HST Release
Bright Earth Avoidance
NOBL Monitoring
FHST FOV Test
NCS Fill Procedure
Gyro Bias
Determination
Attitude
Initialization
FHST/FHST Alignment
ACS CCD Temp Set Point
Determination
Guide Star Acquisition
(FGS 1&3)
Veh Disturbance Test
FGS Pre-NCS Jitter
Test
FGS Recommissioning
NICMOS FOM Optical
Operations Test
ACS Load & Dump Onboard Memory
ACS CCD Hot Pixel
Annealing
STIS CCD Functional
Astrometry Sci Enabled
ACS Science Data
Buffer Check
STIS Pre-NCS Image
Quality
CCD Dark & Bias Images
Duration
(Days*)
0
12
28
4 hrs
1
4 hrs
Dependent On
Type of
Dependency
HST Release
HST Release
HST Release
HST Release
FHST FOV Test
FS
FS
FS
FS
FS
FS
3 hrs
1
Gyro
Determination
Att. Determ.
HST Release
FS
FS
3 hrs
FHST/FHST Align.
SS
FS
FS
1
1
Guide Star Acq.
Guide Star
Acquisition
Guide Star Acq.
HST Release
1
HST Release
FS
1
ACS CCD Temp Set
Point Determ.
HST Release
FGS Recommission
ACS Memory Dump
FS
1
1
1
3 hrs
1
1 hr
1
10
STIS MAMA Turn-on
1
ACS CCD Pre-Flash Test
1
ACS Coarse Alignment
7
STIS MAMA Darks
19
CCD Functional &
Guide Star Acq.
Set Point
Determ. & Sci
Buffer Check
STIS CCD
Functional
ACS CCD
Functional
ACS CCD
Functional
STIS MAMA Turnon
3-13
FS
FS
SS
FS
FS
FS
FS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-5 (continued)
SMS Command Phase Activity Table
Activity Name
STIS End-BEA Test
STIS Pre-NCS Jitter
Test
NCS Activation
NSSC1 Patch (Enable
NICMOS FW)
NICMOS Cool-Down Darks
NCS Set Point
Determined
STIS MAMA Science
Enable
NICMOS Temp Stability
Duration
(Days*)
2
Type of
Dependency
FS
1
STIS MAMA Turnon
STIS MAMA Turnon
Fill Procedure,
Vehicle Disturb
Test, FGS PreJitter Test,
Pre-NCS Jitter
Test & pre-Image
Quality
NCS Activation
4
0
NCS Activation
NCS Activation
SS
FS
0
STIS MAMA Darks
SS
1
FS
1
NCS Set Point
Determined
NCS Set Point
Determined
NCS Set Point
Determined
NCS Set Point
Determined
NCS Set Point
Determined &
NSSC1 Patch(Enab
NIC SW)
NCS Activation
FS
1
NCS Activation
FS
1
0
NCS Activation
BEA, Guide Star
Acq (FGS 1,3)
FS
FS
1
4
NICMOS Det Noise & CRs
1
NICMOS Thermal
Background
NICMOS Transfer
Function Test
NICMOS Filter Wheel
Test
70
Vehicle Disturb. Test
(+V3)
Post-NCS Image Quality
Check
Post-NCS Jitter Test
PCS/OTA Configured
Dependent On
1
1
3-14
FS
FS
SS
SS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-5 (continued)
SMS Command Phase Activity Table
Activity Name
Duration
(Days*)
Dependent On
NIC 1&2 Fine OPT
Alignment
Vehicle Disturbance
Test (-V1)
FGS Post-NCS Jitter
Test
WFPC2 Protect Decon
10
1
NICMOS Temp
Stability
Veh Disturbance
Test (+V3)
NCS Activation
FS
1
PCS/OTA Config.
FS
STIS/FGS Alignment
1
FS
STIS CCD Science
Enable
0
WFPC2 UV Mon Cool-Down
4
WFPC2 PSF Verification
ACS Fine Alignment
WFPC2 Science Enable
WFPC2 Contam Monitor
WFPC2 Focus Check
STIS Contamination
Plan (UV MON)
35
7
0
2
1
42
WFPC2 Lyman Alpha
Check
WFPC2 Flat Field
Calibration
WFPC2 Rel Photometric
Calibration
WFPC2 Int Mon
WFPC2 ERO
STIS Sensitivity &
Geometry
1
PCS/OTA Config.,
STIS CCD Func.
STIS/FGS Align.,
CCD Dark/bias
Image
WFPC2 Protect
Decontamination
UV Mon Cool-Down
ACS Coarse Align
UV Mon Cool-Down
UV Mon Cool-Down
UV Mon Cool-Down
STIS MAMA Turnon, STIS/FGS
Align.
UV Mon Cool-Down
3
UV Mon Cool-Down
FS
1
UV Mon Cool-Down
FS
14
3
2
UV Mon Cool-Down
UV Mon Cool-Down
STIS MAMA Turnon STIS/FGS
Align.
NIC 1&2 Fine Opt
Alignment
NIC 1&2 Fine Opt
Alignment
FS
FS
FS
NIC3 Fine Opt
Alignment
MODE2 Target
Acquisition
1
10
1
3-15
Type of
Dependency
FS
FS
FS
FS
SS
FS
FS
FS
FS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-5 (continued)
SMS Command Phase Activity Table
Activity Name
Coronagraphic Focus
Coronagraphic
Performance
ACS/FGS Alignment
ACS Image Quality &
PSF Measurement
ACS Flat Field
Stability
HRC Flat Field
Stability
ACS Ramp Filter Test
ACS Grism/Prism
Performance
ACS Sensitivity
ACS CCD Geometric
Distortion
ACS Polarization
Capability Check
SBC Activation
ACS SMOV Contamination
Monitor
SBC Detector MiniFunction
SBC Dark Current
Measure
NICMOS GO Science
Enable
NICMOS EROs
Duration
(Days*)
1
Dependent On
Type of
Dependency
FS
1
NIC 1&2 Fine Opt
Alignment
MODE2 Target
Acquisition
ACS Fine
Alignment
ACS Fine
Alignment
ACS Fine
Alignment
ACS Fine
Alignment
ACS Fine
Alignment
ACS Fine
Alignment
ACS/FGS
Alignment
ACS Sensitivity
1
ACS Sensitivity
FS
FS
FS
1
HST Release
ACS Fine
Alignment
SBC Activation
1
SBC Activation
FS
0
NIC3 Fine
Alignment
NIC3 Fine
Alignment
NIC3 Fine
Alignment
NIC3 Fine
Alignment
NIC3 Fine
Alignment
Opt
FS
Opt
FS
Opt
FS
Opt
FS
Opt
FS
1
1
1
1
1
1
1
1
1
63
2
NICMOS Flat Fields
1
NICMOS Persistence
Measure
NICMOS Grism
Wavelength Calibration
1
1
3-16
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
Table 3-5 (continued)
SMS Command Phase Activity Table
Activity Name
NICMOS Photometry
Duration
(Days*)
1
Type of
Dependency
FS
1
NIC3 Fine Opt
Alignment
NIC3 Fine Opt
Alignment
NIC3 Fine Opt
Alignment
NIC3 Fine Opt
Alignment
ACS Fine Align.
& SBC MiniFunction
SBC MiniFunction
SBC Activation
1
SBC PSF Measure
FS
1
NIC 1&2 Fine Opt
Alignment
ACS/FGS
Alignment
SBC Geometric
Distortion, PRD
Aper Loc Updates
PRD Aperture
Location Update
PRD Aperture
Location Update
PRD Aperture
Location Update
PRD Aperture
Location Update
HRC
Coronagraphic
Acquisition
HRC
Coronagraphic
Acquisition
FS
NICMOS Grism
Sensitivity
NICMOS Aperture
Locations
NICMOS Plate Scale
1
SBC PSF Measurement
1
SBC Flat Field
Uniformity
SBC Fold Analysis &
Anomaly Received
SBC Geometric
Distortion
NICMOS Focus Monitor
1
ACS PRD Aperture
Location Updates
ACS SBC Science Enable
Dependent On
1
1
1
1
HRC Coronagraphic
Acquisition
ACS Pointing Stability
1
1
ACS CCD Science Enable
1
ACS EROs
2
HRC Coronagraphic
Scattered Light
1
HRC Coronagraphic
Repeatability
1
*Days unless otherwise noted
3-17
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
FS
SMR-3029
Draft
March 30, 2001
APPENDIX A
REQUIREMENTS TRACEABILITY MATRIX
A-1
SMR-3029
Draft
March 30, 2001
APPENDIX A
Appendix A contains tables that trace the Level III verification
requirements to activities identified in this plan.
These
requirements are found in Appendix J, Section 10.4 of the Mission
Operations Functional Requirements Document (SMO-1000C) and are
controlled by the HST Project, Code 440.
The following tables provide a list of the verification
requirements (following HST release from the Orbiter), that
correlates requirements to activity summaries.
Shown in each
table are:
•
Requirement Identification Number
•
Requirement Description
•
Activity Name and Identification Number
•
Execution Time (by execution phase and week)
A-2
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Draft
March 30, 2001
Table A-1
Verification Requirements Table
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
Execution
Time
J.10.4.1
WFPC II Verification
Requirements
J.10.4.1.1
Engineering Activation and
Check-Out Requirements
J.10.4.1.1.1
After release, the instrument
shall undergo an active
decontamination procedure
(Protect Decon) of at least 12
hours. In the interval
between release and the start
of the decontamination
procedure, the shutter shall
remain closed and the Thermal
Electric Coolers (TECs) shall
remain off.
WFPC2-01
SMS
J.10.4.1.1.2
Upon completion of the
decontamination procedure, the
instrument shall undergo a
contamination verification
phase of at least 48 hours
which shall be monitored by
the STScI. Upon the approval
of STScI, the instrument shall
be cooled to its nominal
operating temperature and the
AFMs shall be reset.
WFPC2-03
SMS
A-3
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
WFPC2-03
Execution
Time
SMS
J.10.4.1.1.3
Following TEC turn on, a
standard UV stellar monitor
shall be scheduled at least
trice during the first week &,
starting with the second week,
at a declining frequency for
the duration of SMOV. A
decontamination procedure
shall be executed no later
than 1 week after TEC turn-on,
and at declining frequency
thereafter. (The STScI will
use the UV monitor to
determine whether the planned
decontamination cycle is
executed or additional
decontaminations are
necessary.)
J.10.4.1.2
Science Verification
Requirements
J.10.4.1.2.1
An initial set of PSF
measurements shall be
performed.
WFPC2-07
SMS
J.10.4.1.2.2
A photometric calibration
shall be performed.
WFPC2-04/
06
SMS
J.10.4.1.2.3
Internal calibrations,
including dark frames, bias
frames, K-spot images, and
internal flat fields, shall be
performed.
WFPC2-05/
08
SMS
A-4
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.1.2.4
If the operational state of
the NCS changes with respect
to the first PSF measurement
(J.10.4.1.2.1), a second PSF
measurement shall be performed
to reflect normal HST
operations.
J.10.4.1.2.5
During the first 30 days after
TEC turn-on, no external WFPC2
pure parallels shall be
scheduled, except as required
to test its parallel
capabilities as provided in
J.10.4.16.3
J.10.4.2
COSTAR Verification
Requirements
Activity
Name and
Identifica
-tion
Number
WFPC2-07
Execution
Time
SMS
N/A
NORMALOPS
N/A
NORMALOPS
No applicable requirements
J.10.4.3
ACS Verification Requirements
j.10.4.3.1
Engineering Requirements
J.10.4.3.1.1
ACS entry into each of four
instrument states (Boot, Hold,
Operate, Observe) shall be
demonstrated. Operations shall
be commanded via stored
commands transmitted over the
Supervisory Bus.
A-5
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
N/A
Execution
Time
J.10.4.3.1.2
ACS entry into each of the
defined detector states shall
be demonstrated. Operations
shall be commanded via stored
commands transmitted over the
Supervisory Bus.
J.10.4.3.1.3
ACS command and engineering
data 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.
N/A
NORMALOPS
J.10.4.3.1.4
The ability to load and dump
on-board memory shall be
demonstrated.
ACS-02
R/T
J.10.4.3.1.5
The ability to read and write
data from and to the science
data buffer shall be
demonstrated.
ACS-03
R/T
A-6
NORMALOPS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.3.1.6
J.10.4.3.1.7
J.10.4.3.1.8
The performance of the cal/
Coronagraph Door, M3 Fold
Mechanism, Im1 and M1
Alignment and Focus Corrector
Mechanisms, WFC/HFC Filter
Wheels 1 and 2, SBC Filter
Wheel, and WFC and HRC CCD
shutters shall be verified.
The functionality of the ACS
Tungsten calibration Lamps and
Pre-Flash LEDs shall be
verified. Operation of the
deuterium lamp shall be
deferred for an initial
outgassing period following
release of the observatory, as
defined in the CARD.
Functionality of all three ACS
detectors shall be
demonstrated through normal
SMOV operations. This shall
include the proper
accumulation of signal over a
specified time internal and
data readout (including
compressed data), as well as,
for the CCDs, readout of a
single subarray and
commandability of gain
settings.
A-7
Activity
Name and
Identifica
-tion
Number
ACS 16/21
Execution
Time
SMS
ACS-05/32
SMS
ACS-05
ACS-08
SMS
R/T
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
ACS-06
Execution
Time
SMS
J.10.4.3.1.9
The ability of the TECs to
cool and stably control the
CCDs shall be tested at a
small number of temperature
set points, in order to
determine the coldest stable
operating point, which is the
final setting desired. The
requirement is that this point
be at least as cold as –80C.
J.10.4.3.1.10
ACS operations shall be
managed to 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. The ACS Cal
Door shall be used to provide
ACS contamination protection
while the OTA is viewing the
bright earth for the duration
of the SMOV program. A
contamination monitoring
program shall be initiated as
early as possible after the
SM.
ACS-10
SMS
J.10.4.3.1.11
High voltage operation of the
ACS SBC MAMA detector shall be
delayed for an initial
outgassing period following
release of the observatory, as
defined in the CARD.
ACS-10
SMS
A-8
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
Execution
Time
J.10.4.3.2
Target Acquisition
Requirements
J.10.4.3.2.1
The location of a reference
ACS HRC camera aperture shall
be determined with respect to
the FGS reference frames to an
accuracy of +/- 1 arcsecond in
V2-V3 coordinates and 10 arc
minutes in aperture rotation
angle.
ACS-11
SMS
J.10.4.3.2.2
The relative positions of the
ACS coronagraphic field masks
and Fastie finger, determined
during ground test, shall be
confirmed.
ACS-12
SMS
J.10.4.3.2.3
The ability of the FSW to
perform isolated point source
acquisition onto the
coronagraphic spots shall be
demonstrated with the ACS HRC
detector. Successful execution
of these acquisitions will
also demonstrate the ability
of the FSW to calculate the
centroid of target positions
and to perform automated
telescope pointing.
ACS-12
SMS
J.10.4.3.3
Optical Alignment Requirements
A-9
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.3.3.1
J.10.4.3.3.2
J.10.4.3.3.3
The encircled energy and image
diameter shall be measured
over a grid of focus and tilt
positions for both IM1 and M1
correctors. These measurements
shall be used to se the
nominal corrector positions.
The camera mode image quality
at the detectors over the full
field shall be measured via
broad and narrow band imaging
of stars. The requirement for
encircled energy in the WFC
and HRC is 75% within a
diameter of .25 arcseconds,
through the F502N filter. The
requirement for encircled
energy in the SBC is 30%
within a diameter of 0.10
arcseconds, for a star
observed through the Lyman
alpha filter.
The internal stability of ACS
from coronagraphic field stop
to HRC detector shall be
monitored. The image shifts
seen shall be compared to the
specified stability of 0.12
HRC pixels RMS over 1300 s and
+/- 0.20 HRC pixels over a
three hour period.
A-10
Activity
Name and
Identifica
-tion
Number
ACS-13/14
Execution
Time
SMS-R/T
ACS-15/23
SMS
ACS-16
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4 3.3.4
The pointing and throughput
stability of the OTA-ACS
combination shall be measured
over several orbits. The
purpose of these measurements
is twofold: 1. Confirm that
the typical
Thermal environment after SM3B
does not cause unacceptable
image drifts.
2. Determine ACS image quality
and pointing stability before
and after the start of NCS
operation.
J.10.4.3.3.5
The ACS Point Spread Function
(PSF) in normal imaging and
coronagraphic modes shall be
measured.
J.10.4.3.4
Calibration Requirements
J.10.4.3.4.1
The plate scale, orientation
and geometric distortion shall
be measured for each of the
ACS channels by imaging an
astrometric field. Relative
location of each aperture in
the FGS frame shall also be
determined with these
measurements.
A-11
Activity
Name and
Identifica
-tion
Number
ACS-17
Execution
Time
SMS
ACS-23/25
SMS
ACS-27
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.3.4.2
Dark rate and read noise and
CTE for each CCD detector
shall be measured, as well as
dark rate for the SBC MAMA
detector. The hot pixel
creation rate shall be
assessed and the efficacy of
the hot annealing cycle shall
be demonstrated.
J.10.4.3.4.3
Instrument sensitivity vs.
wavelength shall be measured
for a subset of ACS modes.
Sensitivity measurements shall
be performed using
astronomical standard stars.
As part of this process, UV
sensitivity measurements shall
be obtained as early as
possible, to enable early
trending of UV sensitivity.
J.10.4.3.4.4
The instrumental polarization
as function of wavelength
shall be measured for both WFC
and HRC channels.
A-12
Activity
Name and
Identifica
-tion
Number
ACS-05/22
ACS-31
Execution
Time
ACS-20/26
ACS-29
SMS
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.3.4.5
J.10.4.4
The flat field uniformity per
pixel & cosmetic defect
fraction shall be measured for
each of the 3 ACS detectors.
The ability to determine the
residual response variation
using the ACS 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.
NICMOS Verification
Requirements
J.10.4.4.1
Engineering Activation
Requirements
J.10.4.4.1.1
The ability to command NICMOS
via the RIU, science data
transmission via the SDF, and
the ability of NICMOS to
transition between its primary
operational states (Hold,
Boot, SAA-Oper, Operate, and
Observe) shall be verified.
A-13
Activity
Name and
Identifica
-tion
Number
ACS-18
Execution
Time
SMS
NICMOS-03
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.4.1.2
Operation of the NICMOS
mechanisms (PAM, FOM, and
filter wheels) shall be
tested. PAM motion over the
range needed to assure focus
in all three NICMOS cameras
(best achievable focus for
NIC3) and +/- 10 steps in X
tilt and +/- 12 steps in Y
tilt shall be demonstrated.
The ability to reposition the
field offset mirror (FOM) over
the range needed to remove
vignetting in NIC3 shall be
demonstrated. Internal lamp
exposures shall be obtained at
each filter wheel position.
J.10.4.4.2
Target Acquisition
Requirements
J.10.4.4.2.1
The location of each NICMOS
camera aperture shall be
determined with respect to the
FGS reference frames to an
accuracy of +/- 2 arcseconds
in V2-V3 coordinates and 7 arc
minutes in aperture rotation
angle for Camera 2 and 1
degree for cameras 1 and 3.
The performance of the
coronograph shall be
demonstrated by an observation
of an isolated point source
following an onboard
acquisition (Mode 2 acq) with
an autonomous location of the
coronographic hole.
J.10.4.4.2.2
A-14
Activity
Name and
Identifica
-tion
Number
NICMOS-01/
02/14
Execution
Time
NICMOS-10
SMS
NICMOS-12/
13
SMS
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
Execution
Time
J.10.4.4.3
Optical Requirements
J.10.4.4.3.1
The optical plate scales at
each of the detector focal
planes shall be measured to a
precision of 1/5 pixel in each
camera.
NICMOS-11
SMS
J.10.4.4.3.2
Optical alignment shall be
restored to the level of
performance achieved during
Cycle7. PAM focus setting
should be measured and trended
to establish and maintain
focus within +/- 1 mm of
nominal (best) focus for each
camera. The encircled energy
within a 100 mas (200 mas for
Camera 3) radius of an
unresolved pointsource shall
be measured. The goal is to
re-establish the performance
achieved in Cycle 7 when the
total wavefront error was λ/14
or better in all cameras
except for NIC3 in the J band
where it was λ/10.
NICMOS-06/
07/09
SMS
J.10.4.4.3.3
Root mean square image motion
shall be characterized.
J.10.4.4.4
Calibration Requirements
A-15
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
NICMOS-14
Execution
Time
J.10.4.4.4.1
The ability to determine
residual pixel-to pixel
variation using the internal
flat-field calibration source
shall be demonstrated. The
stability of the instrumental
flat-fields will be
characterized over timescales
of orbits, days, and one
month.
J.10.4.4.4.2
The ability to calibrate
spectral throughput shall be
demonstrated. The goal is the
calibration of the absolute
flux level to an accuracy of
approximately 10%. Total
instrument throughput shall be
determined and compared to
that measured previously
during Cycle 7.
NICMOS-05/
15
SMS
J.10.4.4.4.3
The ability to do differential
photometry with a residual
measurement error no greater
than 3%, and a temporal
stability of 3% over a month
shall be demonstrated. The
consequences of detector
temperature stability will be
assessed.
NICMOS-15
SMS
A-16
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.4.4.4
NICMOS geometric stability
will be characterized as a
function of orbital elements,
vehicle orientation, and dewar
temperatures by measuring the
lateral motion of the image in
the Camera 2 focal plane.
J.10.4.4.4.5
Detector read noise and dark
current shall be measured. The
minimum acceptable levels of
performance are a read noise
of </=40 electrons and a dark
current of </=2.5
electrons/second.
J.10.4.4.4.6
The cosmic ray background will
be measured and confirmed to
be comparable to the Cycle 7
levels.
J.10.4.4.4.7
HST + NICMOS thermal emission
will be characterized in a
subset of spectral elements
over the duration of SMOV.
A-17
Activity
Name and
Identifica
-tion
Number
Execution
Time
NICMOS-04
SMS
NICMOS-18
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
NICMOS-16/
17
Execution
Time
NICMOS-19/
20
SMS
J.10.4.4.4.8
The decay timescale for image
persistence will be determined
for both images from external
sources of light and from
cosmic rays.
J.10.4.4.4.9
The photometric and wavelength
solutions for the G096 and
G141 grisms will be
remeasured.
J.10.4.4.4.10
During the initial cooldown
phase, NICMOS detector dark
current and flat-field
performance in all three
cameras shall be measured in
3-degree steps starting at 100
degrees K.
J.10.4.4.5
NICMOS Cooling System (NCS)
Engineering Verification
Requirements
J.10.4.4.5.1
Configure the NCS to re-cool
NICMOS detectors. The goal
during SMOV is to verify the
capability to maintain the
NICMOS Cooling Coil
temperature less than or equal
to 69 +/- 0.1K.
NCS-01
R/T
J.10.4.4.5.2
Verify the capability of the
NCS to achieve a NICMOS Cold
Well temperature of 75 +/- 3
degrees Kelvin and maintain it
within 0.1K.
NCS-01
R/T
A-18
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
NCS-01
Execution
Time
R/T
J.10.4.4.5.3
Verify the NCS capability to
provide adequate level of
thermal stability and
repeatability for NICMOS
science operations. Minimum
acceptable levels of
performance are thermal
stability at the detector
baseplate of +/- 0.1K over one
hour and +/- 0.5K over one
month.
J.10.4.4.6
NICMOS/NCS Calibration and
Performance Requirements
J.10.4.4.6.1
The temperatures of each
NICMOS detector, along with
its range of variation and the
timescales for variation,
shall be determined. Detector
temperature stability shall be
characterized over periods of
60 sec, 2000 sec, 24 hours,
and 30 days.
NCS-01
SMS
J.10.4.4.6.2
The temperature of the VCS
(and hence the filter
elements), along with its
range of variation and the
timescales for variation,
shall be determined. The
thermal stability of the VCS
shall be determined to be
within +/- 5K of the nominal
operating temperature as
determined by models of NCS
performance.
NCS-01
SMS
A-19
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
Execution
Time
J.10.4.5
STIS Verification Requirements
J.10.4.5.1
Engineering Requirements
J.10.4.5.1.1
Minifunctional tests shall be
executed for all three STIS
detectors. The high voltage
for the STIS MAMA detectors
will not be activated until at
least four days after release,
as in SM3A.
STIS-01
SMS
J.10.4.5.1.2
The ability of the TEC to cool
and stably control the CCD at
the nominal CCD operating
temperature of –83 degrees C
shall be tested during the
course of normal operations,
including simultaneous
operation of other
instruments.
STIS-01
SMS
J.10.4.5.1.3
Contamination Plan:
1. The STIS Deuterium and
Krypton lamps will not be
operated until 3 weeks
after release as in SM3A.
2. STIS sensitivity will be
monitored periodically.
STIS-00/05
STIS-06
SMS
J.10.4.5.2
Target Acquisition
Requirements
A-20
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.5.2.1
The location of a reference
STIS camera aperture shall be
determined with respect to the
FGS reference frames to an
accuracy of 1 arcsecond in V2V3 coordinates and 10 arc
minutes in aperture rotation
angle.
J.10.4.5.3
Optical Alignment Requirements
J.10.4.5.3.1
The slit plane encircled
energy vs. wavelength and
image diameter shall be
measured for the nominal
corrector focus and tilt
positions. A standard aperture
throughput test shall be used
to assess STIS focus. If
throughput is down by more
than 3 sigma (7%), relative to
the pre-SM3B mean, further
tests and perhaps a STIS
corrector alignment shall be
done.
A-21
Activity
Name and
Identifica
-tion
Number
STIS-02/04
STIS-05
Execution
Time
STIS-02/20
SMS
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.5.3.2
For each supported combination
of optical element and
detector, the location on the
spectrum or slit image on the
detector shall be compared to
pre-SM3B values. Operationally
significant shifts shall be
corrected by updating on-board
mechanism calibration tables.
Updates shall be verified by
retesting the affected optical
element and detector
combination(s). Only one
orientation of each optical
element need be tested.
J.10.4.5.3.3
The slit-to- detector internal
stability of STIS shall be
monitored. The spectral shifts
seen shall be compared to the
specified stability of 0.2 low
resolution MAMA pixels over a
one-hour period. The purpose
of this measurement is
twofold:
1. Measure spectral shifts in
the typical post-SM3B
thermal environment to
check if the maximum time
between wavelength
calibration exposures need
to be reduced.
2. Measure STIS spectral image
quality with and without
NCS operating.
A-22
Activity
Name and
Identifica
-tion
Number
N/A
Execution
Time
STIS-04
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.5.3.4
The pointing and throughput
stability of the OTA-STIS
combination shall be measured
over several orbits. The
purpose of this measurement
is twofold:
1. Measure image drifts in the
typical post-SM3B thermal
environment.
2. Measure STIS image quality
with and without NCS
operating.
J.10.4.5.4
Calibration Requirements
J.10.4.5.4.1
Dark rate and read noise for
each detector shall be
measured at the nominal
operating temperatures, and
will be periodically
monitored to track variations
with time and temperature.
The goals are:
1. Measure the noise
properties of STIS
detectors with and without
NCS operating.
2. To calibrate NUVMAMA dark
rate vs. temperature and
time since SAA passage in
the post-SM3B operating
environment.
A-23
Activity
Name and
Identifica
-tion
Number
STIS-02/04
STIS-01/07
STIS-08/09
Execution
Time
SMS
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.5.4.2
Instrument sensitivity shall
be measured for the lowresolution spectroscopic
modes for contamination
monitoring. Sensitivity
measurements shall be
performed using astronomical
standard stars. Sensitivity
shall be measured at
different values of the MAMA
temperatures.
J.10.4.6
Early Release Observation
J.10.4.6.1
SMOV activities shall include
early release observations
with at least ACS and NICMOS
science instruments. The
resulting science data
products shall be released
into the public domain to
demonstrate the improved HST
capabilities.
J.10.4.7
Optical Telescope
Assembly/Fine Guidance Sensor
Verification Requirements
J.10.4.7.1
Optical Interfaces
J.10.4.7.1.1
HST‘s secondary mirror shall
only be moved to compensate
for desorption in the
graphite epoxy structure.
J.10.4.7.1.2
A check of the OTA focus
shall be made.
J.10.4.7.2
FGS Calibration
A-24
Activity
Name and
Identifica
-tion
Number
STIS-06
Execution
Time
SMS
ERO-01
SMS
FGS/OTA-06
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.7.2.1
The distortions, plate scale,
alignment, and S-curve
morphology and amplitude in
all three FGSs shall be
measured after the completion
of SM3B. These data are to be
compared to pre-SM3B
observations to verify the
validity of the operational
calibration database for each
FGS.
If necessary, as indicated by
the results of J.10.4.7.3.1,
the optical field angle
distortion (OFAD) will be recalibrated for a given FGS.
The appropriate onboard
flight software tables and
PDB shall be updated as
necessary.
J.10.4.7.2.2
J.10.4.7.2.3
If necessary, as indicated by
the results of J.10.4.7.2.1,
the FGS-to-FGS alignment
calibration shall be
performed and the appropriate
alignment matrices will be
computed. Onboard tables and
the PDB shall be updates with
the new calibration
parameters.
A-25
Activity
Name and
Identifica
-tion
Number
FGS/OTA-02
Execution
Time
SMS
FGS/OTA-03
SMS
FGS/OTA-04
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.7.2.4
If necessary, as indicated by
the results of J.10.4.7.2.1,
S-curves in a given FGS will
be obtained at 5 locations in
the FOV. These data will be
used to update the FGS
commanding database so that
appropriate K-factor values
used for the acquisition and
tracking of guide stars can
be computed.
J.10.4.7.2.5
The FGSs will be used to
measure the jitter
experienced by HST during the
operation of NCS.
J.10.4.7.3
FGS Astrometry Science ReCommissioning
J.10.4.7.3.1
The photometric response,
distortions, plate scale, and
S-curve morphology and
amplitude will be measured in
the Astrometer FGS. These
data will be used to
recertify the Astrometer for
scientific observations.
J.10.4.8
Pointing Control Subsystem
Verification Requirements
A-26
Activity
Name and
Identifica
-tion
Number
FGS/OTA-05
Execution
Time
SMS
FGS/OTA-06
SMS
FGS/OTA-07
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
PCS-01/03
J.10.4.8.1
The initial attitude shall be
determined to an accuracy
within .2 degrees using Fixed
Head Star Tracker (FHST)
data.
J.10.4.8.2
R/T
The gyro drift rate bias
shall be calibrated to within
0.05 arcseconds per second
prior to the first guide star
acquisition.
PCS-01/02
R/T
J.10.4.8.3
The FHST/FHST alignment
matrices shall be computed,
using FHST observations at
the initial attitude, to an
accuracy of 5 arcseconds
(1σ). The FHST/FHST alignment
matrices shall be updated if
the change in the pitch or
yaw alignment exceeds 20
arcseconds. The alignment
computations will be further
refined during normal
operations to achieve
accuracy comparable to the
pre-Servicing Mission level.
PCS-04
R/T
J.10.4.8.4
The gyro-to-FHST alignment
matrices shall be maintained
to an accuracy that reduces
the attitude error following
a vehicle maneuver to less
than one arcsecond per degree
of slew. If any gyros are
changed out, a full RGA
calibration will be
performed.
PCS-05/06
R/T-SMS
A-27
Execution
Time
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.8.5
The PCS shall acquire guide
stars in fine lock.
J.10.4.8.6
The vehicle jitter during
periods of fine lock shall be
measured.
A-28
Activity
Name and
Identifica
-tion
Number
PCS-07
Execution
Time
SMS
PCS-07
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number SMOV Requirement Description
J.10.4.8.7
Perform a Vehicle Disturbance
Test (VDT) to characterize the
disturbance environment of the
HST using a low-bandwidth
attitude control law during
gyro-hold with the gyros in
low-mode. The VDT is a passive
test (not a forced-response
test). Obtain signatures for
both externally induced (e.g.
SA-3) and internally induced
(e.g. NCC) disturbances for
comparison with past VDT
results and characterize
jitter induced by the SA-3,
NCS, and the ACS Filter Wheel.
The VDT shall consist of five
separate tests that need not
occur consecutively. The
overall duration of the VDT
tests are at least 17 orbits
of spacecraft time including
(1) at least 1 full orbit at
+V3 sunpoint prior to NCC
operation while performing ACS
Filter Wheel moves simulating
routine flight operations, (2)
at least 5 full orbits at +V3
sunpoint prior to NCC
operation, (3) at least 1 full
orbit at +V3 sunpoint during
NCC startup, (4) at least 5
full orbits at +V3 sunpoint
while NCC is operating at
steady-state, and (5) at least
5 full orbits at –V1 sunpoint
with the NCC operating at
steady-state.
A-29
Activity
Name and
Identifica
-tion
Number
PCS-08
Execution
Time
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.8.8
Contingent upon analysis of
PCS performance post-SM3B,
perform a Transfer Function
Test (TFT). The TFT is a
forced response test that
measures HST system modal
parameters (modal gains, modal
damping ratios and
frequencies) by applying a RWA
forcing function and measuring
RGA gyro response. This test
will be performed if PCS
analysis of post-SM3B HST
flight data (such as the VDT)
suggests that HST system modal
parameters significantly
differ from pre-SM3B
analytical models. On-orbit
modal parameters that differ
from pre-SM3B models can cause
degraded performance of the
HST attitude control system
because of reductions in
stability margins and/or
increased vehicle jitter.
J.10.4.9
Data Management Subsystem
Verification Requirements
No applicable requirements.
J.10.4.10
Instrumentation &
Communications Subsystem
Verification Requirements
No applicable requirements
J.10.4.11
SI C&DH Verification
Requirements
A-30
Activity
Name and
Identifica
-tion
Number
PCS-09
Execution
Time
SMS
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
Activity
Name and
Identifica
-tion
Number
Execution
Time
TCS-01
SMS
EPS-01
Analysis
Task
No applicable requirements
J.10.4.12
Structures and Mechanisms
Subsystem Verification
Requirements
No applicable requirements
J.10.4.13
Thermal Control Subsystem
Verification Requirements
J.10.4.13.1
Verify the predicted
temperature changes due to the
NOBL installation on SSM bays
5, 6, 7 and 8.
J.10.4.14
Electrical Power Subsystem
Verification Requirements
J.10.4.14.1
Solar Array III (SAIII)
Verification Requirements
J.10.4.14.1.1
SAIII drive system performance
shall be characterized during
the SMOV period and the
following requirements
verified. 1. The sensed
position is within +/- 3.5
degrees of the commanded
position when operating within
the range 0 to 130 degrees,
and +/- 5.0 degrees outside
this range, 2. The maximum
command profile error shall be
less than the safemode test
threshold (10 degrees for 3
seconds).
A-31
SMR-3029
Draft
March 30, 2001
Table A-1
Verification Requirements Table (Continued)
Req. ID Number
SMOV Requirement Description
J.10.4.14.1.2
SAIII power generation
performance shall be assessed
and compared to Beginning of
Life (BOL) predictions that
account for expected
degradation. To the extent
possible, measurements shall
be recorded when HST is at
orbit noon, when the Sun
vector is within +/- 10
degrees of the –V1 axis, when
the SA/Sun incidence angle is
less than 5 degrees, and when
all the available CCC K-relays
and SPA Trim Relays are
closed.
J.10.4.14.2
Power Control Unit
J.10.4.14.2.1
A software charge control
mode, Trim Relay SoftWare
Charge Control with the V/T
Front End (TRSWCC/VTFE), shall
perform charge control and
maintain battery thermal
stability. This shall be
verified for periods of high
suntime, low solar array
incidence angles, and at a
minimum HST load power for the
expected load range following
SM3B.
A-32
Activity
Name and
Identifica
-tion
Number
EPS-02
Execution
Time
EPS-03
Analysis
Task
Analysis
Task