23 - hmi - page 1 sdo pre-ship review part 1 - january 21-22, 2009 –v_20090116 hmi status at sdo...

23 - HMI - SDO Pre-Ship Review Part 1 - January 21-22, 2009 –V_20090116

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

GSFC

– 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


HMI Instrument on SDO

• 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

X

Z

Y

EVE

AIA

X

Y

Z

HOP HEB

HMI

SDO


HMI Integration

HOPHOP

HarnessHarness

HEBHEB

AIAAIAEVEEVE

HMIHMI


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


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


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

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 Initial on-orbit bake-out/warm-up expected to eliminate this effect

o 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


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


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 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


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


Mechanism Trending Summary

1.02

1.03

1.04

1.05

1.06

1.07

Cal/F

ocu

s W

heel

Sp

in P

eri

od

(s)

CF1

CF2

Lockheed Martin GSFC

0.104

0.106

0.108

0.110

0.112

0.114

Sh

utt

er

Sp

in P

eri

od

(s)

SH1

SH2

0.600

0.800

1.000

1.200

1.400

Pre-V

cal

Pre-V

ibe

TB AT 1

TB AT 3

Post-V

ibe

TV AT 2

.1

TV CPT 2

TV FT 2

TV AT 4

TV FT 4

TV FT 6

TV AT 6

TV FT 8

TV CPT 3

TV AT 7

HEB Pre

-Vibe

HEB Pos

t-Vib

e

SC Inte

gratio

n

Stand

alone

Pre-E

MI

Pre-V

ibe

TV Hot

1

TV Hot

2

TV Hot

3

TV Cold

3

Post-E

nv

Ho

llow

Co

re M

oto

r S

pin

Per

iod

(s)

WT1

WT2

WT3

WT4

PS1

PS2

PS3

All mechanisms meet requirements, variations due to temperature

Cold

Hot


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:

CCR Type Title Status Comments

SDO-CCR-0982 WaiverHMI EMI/EMC Test Radiated Susceptibility Exceeded

ApprovedRS exceeded requirements in one preamp of one camera at 200 MHz by 3-4 DN

SDO-CCR-1002 Waiver Observatory Radiated Emissions Exceedance ApprovedThere is sufficient margin between emissions and susceptibilities

SDO-CCR-1003 WaiverHMI HSB Electrical Requirement - Inner Shield Length

ApprovedThe data rate is met with the 0.1 inch extra length

SDO-CCR-1020 Waiver HMI Performance during 1.0V Ripple Voltage In Review Freq. 1-29 Hz not tested in EMI/EMC

SDO-CCR-1022 WaiverHMI Electronics Box (HEB) Stress Analysis not Completed at the Instrument Level

In ReviewBridge board stress analysis performedLoads test performed successfully


Requirements Verification Status

Verification Activity No. Req. Verified Open Status

Comprehensive Performance Test 21 21 0 As Run Test procedure in closure

EMI/EMC/GND 28 27 1 GND shop order number to be linked

Science Performance Analysis 35 34 1 Camera Gain Stability Report in progress

Image Motion waiver in progress

Software Acceptance 138 138 0 Document update

Optical Requirements 10 10 0 STOP analysis complete

Report in release

Timing 3 3 0 Report being completed

Thermal 19 19 0 As Run Test procedure in closure

Electrical Design Inspection 43 42 1 Verify the single link data rate

TOTAL 297 294 3

• 169 Closed

• 294 Verified / 3 Open

• Verified = Analysis complete, Data certified, Reports in completion


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


PFR Status

PFR# Rating Test Description Disposition

SDO-442NSR set time

Yellow No Step Request

The NSR flag lead time is 300 - 500 ms (vs. the 400 to 600 ms requirement).

Correctable by starting the camera clear 100 ms earlier.

SDO-251LVDS

Yellow Integration LVDS resistance measurements off nominal

Remaining open until the flight spares are repaired at RAL

SDO-452LED camera ratio

Red TV The optical throughput using the HMI LED decreased during thermal vacuum testing

Under review; anticipate use of decontamination heater and HOP bake-out on orbit

SDO-380Odd image

Yellow CPT FSN 1198049 was not received as expected

Monitor for reoccurrence

PFR# Rating Test Description Disposition

SDO-260Processor reset

Risk Flag

Pre-ship B-Side processor occasionally resets when ISS is powered on

•ISS relay closes properly, •CPU autonomously performs soft reset•Operator continues on with startup procedure (use as-is)

•Red-flag PFRs:

•Open (Red, Orange, Yellow) PFRs:


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


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


Readiness to Ship

• HMI is good to go with the following liens:– Resolution of PFRs requiring follow-up work

– Verification Closures


Backup Charts

•


PER Waiver Summary

CCR Type Title Status

SDO-CCR-0372 Deviation In-Rush Current Requirements for HMI and AIA CEBs Approved

SDO-CCR-0811 Waiver HMI Shutter and Focus Wheel Static Imbalances Approved

SDO-CCR-0813 Waiver HMI Induced Jitter Requirements in PJAB Approved

SDO-CCR-0814 Waiver Surface Conductivity Requirement for Some HMI Parts Approved

SDO-CCR-0816 Waiver Floating Metal Requirement for Some HMI Parts Approved

SDO-CCR-0817 Waiver Thermal Cycling of Some HMI Component-level Parts Approved

SDO-CCR-0819 Waiver HMI Oven Controller Operational Transients Approved

SDO-CCR-0820 Waiver HMI EMI/EMC Decontamination Heater Operational Transient Approved

SDO-CCR-0821 Waiver HMI EMI Conducted Emissions (CE) Exceedances Approved

SDO-CCR-0822 Waiver HMI EMI Radiated Susceptibility (RS) Incomplete Exposure Approved

SDO-CCR-0823 Waiver HMI EMI Radiated Emissions (RE) Exceedances Approved

SDO-CCR-0824 Waiver HMI EMI Conducted Susceptibility (CS) Approved

SDO-CCR-0834 Waiver HMI Heater Sizing Margin (Operational and HOP Survival) Cancelled

SDO-CCR-0838 Waiver Reduction in the HMI Field of View Requirement Approved

SDO-CCR-0856 Waiver AIA and HMI Shock Tests Deferred to Observatory Level Approved

SDO-CCR-0883 Waiver HEB vibe under test due to notching of first mode resonance Approved

23 - hmi - page 1 sdo pre-ship review part 1 - january 21-22, 2009 –v_20090116 hmi status at sdo...

Documents

hmi status hmi

hmi page

hmi dais

environmental tests

final cpt hmi

procedures hmi test

sdo preship review

magnetic imager hmi