HMI Status at SDO PSR-1

1. HMI Status at SDO PSR-1 • 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 • January 21-22, 2009 • GSFC

2. Helioseismic and Magnetic Imager (HMI) studies the interior and magnetic activity of the Sun HMI Instrument HMI Optics Package (HOP) HMI Electronics Box (HEB) Intra Instrument Harness Flight Software SDO AIA EVE X Y Z HMI HOP HEB HMI Instrument on SDO

3. HEB HMI Integration HOP EVE AIA Harness HMI

4. HMI Status • 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

5. Changes Since SDO PER (March 2008) • 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

6. Environmental Tests • 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 • No instrument susceptibility detected during Observatory level self compatibility test. • 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) • 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

7. Blank Image Anomaly Resolution • 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

8. CPT Performance Status • 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 ImagesRuntime • 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

9. Trending • 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

10. Lockheed Martin GSFC Mechanism Trending Summary Cold Hot All mechanisms meet requirements, variations due to temperature

11. Test & Verification • 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:

12. Requirements Verification Status • 169 Closed • 294 Verified / 3 Open • Verified = Analysis complete, Data certified, Reports in completion

13. Verification Close-out • 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

14. PFR Status • Open (Red, Orange, Yellow) PFRs: • Red-flag PFRs:

15. LED Camera Ratio in Vacuum (PFR-452) • 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

16. HMI Remaining Work • No Step Request timing verification • Test plan developed. Test needed to verify solution • Single link performance verification • Test plan being developed. Test needed to verify performance • LED camera ratio issue resolution • Open Verification items and open documentation

17. Readiness to Ship • HMI is good to go with the following liens: • Resolution of PFRs requiring follow-up work • Verification Closures

18. Backup Charts

19. PER Waiver Summary