Transcript SDO Systems Retreat - Stanford University
HMI Status at SDO PSR-1
January 21-22, 2009 GSFC SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
– – – – – – – – – HMI Present Status Changes Since SDO PER • Hardware • Software Blank Image Resolution Results of Test Program • Environmental • • Functionals & CPTs Trend Data Test Verification & Waivers Verification Matrix PFR Status HMI Remaining Work Readiness to Ship 23 -
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HMI Instrument on SDO SDO
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Helioseismic and Magnetic Imager (HMI) studies the interior and magnetic activity of the Sun
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HMI Instrument
– – – – HMI Optics Package (HOP) HMI Electronics Box (HEB) Intra Instrument Harness Flight Software
EVE HMI AIA
Y Z X
Z Y X
HOP
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HEB
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Harness SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
HMI Integration
HOP EVE HEB AIA HMI
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HMI Status
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HMI is ready for the Observatory to be shipped
– Environmental tests successfully accomplished – CPTs successfully performed • • Optical performance is stable and meets requirements Alignments and co-alignments meet requirements – Present flight software will be flown • • Tested patch prevents blank images when HEB is hot; patch loaded at instrument turn on Minor constraints recognized and documented – Flight blankets have been installed • Minor blanket close out on primary alignment cube required after final CPT – HMI is currently in flight configuration with the following planned exceptions • • CCD & CEB Radiator covers Blanketing for spacewire cable
Mission simulations will fine tune the operational plans and procedures HMI test bed at LMSAL has been, and will continue to be, quite useful
– Test flight observing sequences – Develop and test flight operations procedures – Trouble shoot anomalies – Develop and qualify potential flight software patches or updates
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Changes Since SDO PER (March 2008)
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Hardware changes
– Minor thermal blanket adjustments to address solar entrapment concerns
HMI Software changes
– FSW was delivered with known issues and software update planned after observatory integration – Developed a list of software updates with SDO Project to address the following • Incorporate fixes to selected known discrepancies based on HMI DAIs • • Incorporate corrections based on IV&V findings Integrate high speed bus (HSB) resynchronization protocols – Software was updated prior to TVac and subsequent CPTs & Functionals • Kernel acceptance testing performed at LMSAL in May 2008 • • Kernel 2.34 and FSW 10.10 loaded on 8 June 2008 Final FSW acceptance testing performed 10-12 June 2008 on the flight instrument – Developed and Tested Onboard Scripts for responding to FDCs and INCs • • Camera Header Errors Recovery Camera gain and offset reset Recovery
Observatory Software changes
– TSM/RTS developed and tested • Decontamination Heater Operations • • • Camera Link Detection & Recovery Camera Header Errors Detection & Recovery Camera gain and offset reset Detection & Recovery
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Environmental Tests
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HMI passed all environmental tests as part of the Observatory test program
– EMI/EMC (April 2008) • Radiated susceptibility exceeded requirements in one preamp of one camera at 200-300 MHz o No instrument susceptibility detected during Observatory level self compatibility test.
o Large margin between observatory radiated emissions and instrument susceptibility • Radiated Emission exceedence as seen at instrument-level EMC (see Waivers) – Mechanical (acoustic, shock, vibration) (May/June 2008) • Baseline performance reconfirmed – Thermal Balance (July 2008) • • • Thermal control system, including survival heaters, meet requirements Thermal math model refined based on Thermal Balance data, and reviewed with project Blank Image Anomaly observed during the first hot plateau (see following chart) – Thermal Vacuum (July/August 2008) • Successful qualification of the flight hardware • • Instrument meets requirements at all temperatures Camera intensity ratio changed with time in vacuum (see later chart re PFR-452) o o Initial on-orbit bake-out/warm-up expected to eliminate this effect Full Level-1 science achievable with bake-outs/warm-ups every 6 months even if effect is experienced on-orbit
Instrument now qualified for flight
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Blank Image Anomaly Resolution
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Observed during HMI Instrument Thermal Vacuum testing at LMSAL
– – HEB hot operations caused some images to have values of all “0”s Presumed caused identified as CIF memory Mode Register Set (MRS) command – Updated flight software was developed but was not thoroughly tested before delivery
Blank images were observed again during the first hot plateau in the Observatory level thermal balance test.
– – Troubleshooting identified a means for clearing the blank image anomaly A software patch was developed to remove the mode reset command
The MRS patch was extensively exercised during observatory thermal vacuum testing Testing on the HMI test bed and subsequent FPGA analysis was able to identify the root cause.
– Root cause has been determined as incorrect SDRAM address bits due to the FPGA timing skew across two clock domains
Hardware will be used as is with software patch that removes the MRS command
– FSW patch used as part of every instrument turn on since Mid-August 2008
Patch disables the built-in SEFI recovery function in the CIF
– SEFI ground recovery procedure developed and tested – – SEFI Rate – once per SDRAM every eight years in background environment, once per 30 days in flare Three way voting logic requires two SEFIs to occur in the same bank without ground intervention before impacting science
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CPT Performance Status
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Instrument performance fully characterized HMI has performed 7 CPTs to date (three at observatory level) Post Environmental CPT results
– Analysis has been completed and is consistent with the established baseline
All CPT PFRs successfully resolved Instrument Sequencer Operational statistics # of Images Runtime
– Since delivery (Dec 2007 – Dec 2008): 876,276 486.8 hours – Since software update (June 2008 – Dec 2008): 660,020 366.7 hours – Since software patch (Sept 2008 – Dec 2008): 115,328 64.1 hours •
Longest uninterrupted sequencer run since software update: 48.5 hours
– All expected images received and were complete
Level 1 science performance requirements met
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Trending
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Instrument performance trended, examples below Mechanical/Non Optical Performance (All meet requirements)
– Spin times for Cal/Focus wheels, shutters, and Hollow Core Motors – Mechanism delay time ranges (an internal parameter) – Voltages (primary and secondary) and currents – Boresight Alignment
Optical Performance (All meet requirements)
• • • • • • • • Best focus Field curvature Distortion MTF CCD alignment Flat Field stability Particulate contamination Scattered light performance
All trends nominal; will continue trending through I&T and on orbit SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
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Mechanism Trending Summary
1.07
1.06
1.05
Cold
Lockheed Martin GSFC
1.04
1.03
Hot
1.02
0.114
P re -V 0.110
P ca re l -V ib TB e
All mechanisms meet requirements, variations due to temperature
A T TB 1 A P T ost 3 -V TV ib e A T TV 2.
1 C P T TV 2 F T TV 2 A T TV 4 F T TV 4 F T TV 6 A T TV 6 F TV T 8 C P H T TV E 3 A B H P T E re 7 B -V P S ib ost C e -V In ib te e gr S at ta io nd n al on P re e -E P M re I -V ib TV e H ot TV 1 H ot TV 2 H ot TV 3 C ol P d 3 ost -E nv 0.108
CF1 CF2 SH1 SH2 0.106
1.400
0.104
1.200
Vca 1.000
0.800
Pr e l Vi be TB A T TB 1 A T Po 3 st -V TV ib A e T TV 2.
1 C PT 2 TV F T TV 2 A T TV 4 F T TV 4 F T TV 6 A T TV 6 F TV T 8 C PT H 3 TV EB A H P T re EB 7 -V P ib ost SC e -V In ib te e gr St at io an n da lo Pr ne e EM Pr e I Vi be TV H ot TV 1 H ot TV 2 H ot TV 3 C ol d Po 3 st -E nv 0.600
P re -V P ca re l -V ib TB e A T TB 1 A P T ost 3 -V TV ib e A T TV 2.
1 C P T 2 TV F T TV 2 A T TV 4 F T TV 4 F T TV 6 A T TV 6 F TV T 8 C P H T TV E 3 A B H T P E re 7 B -V P S ib ost C e -V In ib te e gr S at ta io nd n al on P re e -E P M re I -V ib TV e H ot TV 1 H ot TV 2 H ot TV 3 C ol P d 3 ost -E nv
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WT1 WT2 WT3 WT4 PS1 PS2 PS3 23 -
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Test & Verification
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Testing since Observatory PER
– EMI/EMC – Waiver SDO-CCR-0982, SDO-CCR-1002 – Vibe/Acoustics/shock – No issues – CPT #2 – No issues – Post-environmental Instrument CPT and Observatory Functional –No Issues
HMI Verification Matrix status
– All functional and performance requirements are met, with the exception of Waivers listed below and items shown on the following verification matrix slides
Waivers since PER: CCR
SDO-CCR-0982 SDO-CCR-1002 SDO-CCR-1003 SDO-CCR-1020 SDO-CCR-1022
Type
Waiver Waiver Waiver Waiver Waiver
Title
HMI EMI/EMC Test Radiated Susceptibility Exceeded Observatory Radiated Emissions Exceedance HMI HSB Electrical Requirement - Inner Shield Length HMI Performance during 1.0V Ripple Voltage HMI Electronics Box (HEB) Stress Analysis not Completed at the Instrument Level Status Approved Approved Approved In Review In Review
Comments
RS exceeded requirements in one preamp of one camera at 200 MHz by 3-4 DN There is sufficient margin between emissions and susceptibilities The data rate is met with the 0.1 inch extra length Freq. 1-29 Hz not tested in EMI/EMC Bridge board stress analysis performed Loads test performed successfully
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Requirements Verification Status
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169 Closed 294 Verified / 3 Open Verified = Analysis complete, Data certified, Reports in completion Verification Activity Comprehensive Performance Test EMI/EMC/GND Science Performance Analysis Software Acceptance Optical Requirements Timing Thermal Electrical Design Inspection TOTAL No. Req.
21 28 35 Verified 21 27 34 138 10 3 19 43 297 138 10 3 19 42 294 Open 0 1 1 0 0 0 0 1 3 Status As Run Test procedure in closure GND shop order number to be linked Camera Gain Stability Report in progress Image Motion waiver in progress Document update STOP analysis complete Report in release Report being completed As Run Test procedure in closure Verify the single link data rate SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
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Verification Close-out
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Single Link Data Rate Verification
– Level 1 science data rate has not been demonstrated with a single HSB data link – A test has been defined to measure the date rate threshold – Maximum data rate with a single link will be determined during instrument testing, scheduled for the last week of January
Image Motion Waiver
– Image motion resulting from tuning waveplate rotation exceeds a requirement detailed in the Instrument Performance Document – Review of the verification status discovered that the image motion requirement had not been completely addressed – This image motion requirement will be waived based on a better understanding of the observables calculation method
Camera Gain Stability Analysis
– Camera Gain Stability is the end to end performance of the CCD and CEB system – Analysis of images taken during observatory thermal vacuum testing indicates that the gain stability requirement is being met – The formal verification report is in process of being completed
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PFR Status
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Open (Red, Orange, Yellow) PFRs: PFR#
SDO-442 NSR set time
Rating
Yellow
Test
No Step Request SDO-251 LVDS SDO-452 LED camera ratio SDO-380 Odd image Yellow Red Yellow Integration TV CPT
Description
The NSR flag lead time is 300 - 500 ms (vs. the 400 to 600 ms requirement). LVDS resistance measurements off nominal The optical throughput using the HMI LED decreased during thermal vacuum testing FSN 1198049 was not received as expected
Disposition
Correctable by starting the camera clear 100 ms earlier.
Remaining open until the flight spares are repaired at RAL Under review; anticipate use of decontamination heater and HOP bake-out on orbit Monitor for reoccurrence •
Red-flag PFRs: PFR#
SDO-260 Processor reset
Rating
Risk Flag
Test
Pre-ship
Description
B-Side processor occasionally resets when ISS is powered on
Disposition
•ISS relay closes properly, •CPU autonomously performs soft reset •Operator continues on with startup procedure (use as-is)
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LED Camera Ratio in Vacuum (PFR-452)
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Under vacuum aliveness testing, the ratio of the LED intensity as observed with the two cameras changes with time The ratio recovers when brought back to room ambient temperature and pressure These data and closer study of-LED based images show a reversible effect on the CCD (and perhaps the fold mirror); such as contamination Magnitude of the effect seen during TVac would not impact Level 1 Science Since effect is reversible there are operational workarounds
– The initial 25-day on-orbit decontamination period will dramatically improve effective venting of any contaminants – Any lingering/other effects can be managed by periodic warm-up of the CCD and fold mirror; approximately every 6 months (likely during eclipse season).
Will continue to investigate root cause possibilities, using a Fishbone Analysis to guide and document the investigation SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
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HMI Remaining Work
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No Step Request timing verification
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Test plan developed. Test needed to verify solution
Single link performance verification
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Test plan being developed. Test needed to verify performance LED camera ratio issue resolution Open Verification items and open documentation SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116
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Readiness to Ship
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HMI is good to go with the following liens:
– Resolution of PFRs requiring follow-up work – Verification Closures
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Backup Charts
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PER Waiver Summary
CCR
SDO-CCR-0372 SDO-CCR-0811 SDO-CCR-0813 SDO-CCR-0814 SDO-CCR-0816 SDO-CCR-0817 SDO-CCR-0819 SDO-CCR-0820 SDO-CCR-0821 SDO-CCR-0822 SDO-CCR-0823 SDO-CCR-0824 SDO-CCR-0834 SDO-CCR-0838 SDO-CCR-0856 SDO-CCR-0883
Type
Deviation Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver Waiver
Title
In-Rush Current Requirements for HMI and AIA CEBs HMI Shutter and Focus Wheel Static Imbalances HMI Induced Jitter Requirements in PJAB Surface Conductivity Requirement for Some HMI Parts Floating Metal Requirement for Some HMI Parts Thermal Cycling of Some HMI Component-level Parts HMI Oven Controller Operational Transients HMI EMI/EMC Decontamination Heater Operational Transient HMI EMI Conducted Emissions (CE) Exceedances HMI EMI Radiated Susceptibility (RS) Incomplete Exposure HMI EMI Radiated Emissions (RE) Exceedances HMI EMI Conducted Susceptibility (CS) HMI Heater Sizing Margin (Operational and HOP Survival) Reduction in the HMI Field of View Requirement AIA and HMI Shock Tests Deferred to Observatory Level HEB vibe under test due to notching of first mode resonance
SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116 Status
Approved Approved Approved Approved Approved Approved Approved Approved Approved Approved Approved Approved Cancelled Approved Approved Approved 23 -
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