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EUV Variability Experiment (EVE). Rick Kohnert EVE Systems Engineer [email protected]. EVE Instrument Overview. OUTLINE. Science Overview Requirements Summary Overview Design Implementation Mitigation Efforts Development Flow - PowerPoint PPT Presentation
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EVE Overview Page 1SDO Preliminary Design Review (PDR) – March 9-12, 2004
EUV Variability Experiment(EVE)
Rick KohnertEVE Systems Engineer
EVE Instrument Overview
EVE Overview Page 2SDO Preliminary Design Review (PDR) – March 9-12, 2004
OUTLINE
• Science Overview• Requirements• Summary Overview• Design Implementation• Mitigation Efforts• Development Flow• Schedule
• Risk Assessment
EVE Overview Page 3SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Science Goal/SDO Role• Specify and understand the highly variable solar extreme ultraviolet (EUV)
electromagnetic radiation and its impacts on the geospace environment and the societal consequences
SDO Connects the Sun to the Earth
Space Weather Operations(NOAA, Air Force)
Solar Dynamics Observatory(NASA-GSFC)
Solar Images -> Flares, CMEs
Solar Irradiance -> Energy Input
Thermosphere Models -> Satellite Tracking
Ionosphere Models -> Communications
HMI
EVE
AIA
EUV Spectrum
EVE Overview Page 4SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Science Questions/Objectives
What questions will EVE answer?
EVE Objective The EVE Plan
1 What is the solar EUV spectral irradiance and how much does it vary?
Specify the solar EUV spectral irradiance and its variability on multiple time scales
Measure the EUV: 0-105 nm with 0.1 nm resolution + H I Lyman-at 121.6 nmMeasurement Time Scales: ≤ 20sec cadence, continuous sequence
2 Why does the solar EUV spectral irradiance vary?
Advance current understanding of how and why the solar EUV spectral irradiance varies
Use AIA and HMI solar images to understand the interactions of the solar magnetic fields and the evolution of the solar features (e.g., plage, active network) and how these affect the solar variations
3 How well can we predict the absolute value and variability of the solar EUV spectral irradiance?
Improve the capability to predict the EUV spectral irradiance variability
Develop new forecast and nowcast models of the solar EUV irradiance for use in the NOAA space weather operations
4 How does the geospace environment respond to variations in the solar EUV spectral irradiance and what are the societal impacts?
Understand the response of the geospace environment to variations in the solar EUV spectral irradiance and the impact on human endeavors
Use solar EUV irradiances with thermosphere and ionosphere models to better define the solar influences on Earth’s atmosphereInput EVE solar data near real-time into NOAA operational atmospheric models to improve accuracy of solar storm warnings and satellite drag calculations and to predict communications disruptions
EVE Overview Page 5SDO Preliminary Design Review (PDR) – March 9-12, 2004
Why EUV Measurements?
• The solar extreme ultraviolet (EUV: < 120 nm) radiation is the primary energy input for the thermosphere (where satellites reside) and the ionosphere (what affects communications)
Plot shows where the solar radiation is deposited in the atmosphere
Primary atmospheric absorbers are N2, O, O2, and O3Ionosphere
EVE Overview Page 6SDO Preliminary Design Review (PDR) – March 9-12, 2004
What is the solar EUV ?• The solar EUV radiation consists
of emissions from the solar chromosphere, transition region, and corona
– EUV is < 0.01% of the total solar irradiance (TSI: >99% from photosphere)
– But EUV variations are a factor of 2 - 100 (wavelength dependent), whereas TSI has only 0.1% variations
– And EUV is completely absorbed in Earth’s atmosphere
– And EUV photons are energetic enough to ionize the atmosphere (creates the ionosphere)
EVE Overview Page 7SDO Preliminary Design Review (PDR) – March 9-12, 2004
How does EVE measure the EUV?
• Multiple EUV Grating Spectrograph (MEGS)
– At 0.1 nm resolution• MEGS-A: 5-36 nm• MEGS-B: 35-105 nm
– At 1 nm resolution• MEGS-SAM: 0-7 nm
– At 20 nm resolution• MEGS-Photometers: @ 15,
25, 40, 60, 121.6 nm– Ly- Proxy for other H I emissions
at 80-102 nm
• EUV Spectrophotometer (ESP)– At 4 nm resolution
• 18.4, 25.6, 30.4, 36.8, 58.4 nm
– At 7 nm resolution• 0-7 nm (zeroth order)
0.114720
nm
EVE Overview Page 8SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Success Criteria (Level 1)
Level 1 Reference
PERFORMANCE REQUIREMENTS FOR FULL SUCCESS
Measurement Objectives
A-2.1.1.1.1.1 The EVE shall perform solar spectral irradiance measurements in the range of 0.1 to 105 nanometers with a time period of no longer than 20 seconds between successive measurements
0.1 to 105 nm with a 10 second cadence
A-2.1.1.1.1.2 The EVE shall measure at least 18 emission lines at a spectral resolution of 0.1 nanometers with a minimum absolute accuracy of 25 percent for each emission line
18 or more emission lines at Δ ≤ 0.1 nm, 20% accuracy (brighter lines)
PERFORMANCE REQUIREMENTS FOR MINIMUM SUCCESS
A-2.1.1.1.2.1 The EVE shall perform hourly solar spectral irradiance measurements in n less than six emission lines at a spectral resolution of 0.2 nanometers and an absolute accuracy of 40 percent to specify the chromosphere, transition region, and corona
A-2.1.1.1.2.2 The EVE shall perform a measurement of the Helium-II emission line at 30.4 nanometers at a spectral resolution of at least 5 nanometers and an absolute accuracy of 40 percent
EVE Overview Page 9SDO Preliminary Design Review (PDR) – March 9-12, 2004
Driving Requirements
Parameter Requirement Range 0.1-105.0 nm
Resolution 0.1 nm for 18 or more emissions
Time Cadence ≤20 seconds
Accuracy 25% over mission life
Signal to Noise Ratio 15 over mission life
Pointing Accuracy <15 arc-minutes
Visible Light Rejection > 1010
Contamination < 400 Angstroms NVR distributed over the optical path
CCD Gain 2e-/dn
CCD Operating Temperature -100 °C
EVE Overview Page 10SDO Preliminary Design Review (PDR) – March 9-12, 2004
The EVE TeamGSFC SDO Program Office
EVE Science Team
EVE PITom Woods
Project ManagerMike Anfinson
Quality AssuranceDoug Vincent
System EngineeringGreg Ucker, Lead
Rick KohnertGail Tate, SW
Project ScientistFrank Eparvier
EVE MESteve Steg, Lead
EVE ContractsSteve Erickson
Zach CastlemanCCD/Filter Mech
TBD Students
Bret LamprechtThermal
EVE EENeil White, Lead
Bryce BoltonIM/MEGS/EEBKip DenhalterEEB Pwr/GSE
Roger GundersonEEB
EVE SWGail Tate, Lead
Greg AllisonFlt SW
Karen TurkGnd SW
Don WoodraskaOps/DA
EVE SpTest/CalGinger Drake, Lead
Dave CrotserMEGs Optics/CCDs
Matt TripletMEGS Filters/CCDs
USC/Swales/SIRick Kohnert,
Engineering Liaison
MIT-LL/SIGreg Ucker
Engineering Liaison
I & TRick Kohnert, Test Mgr
Gail Tate, SOC Mgr
Karen TurkGnd Stwr
Don WoodraskaOps/DA
Neil WhiteEE
Steve StegME
Mission OperationsRandy Davis, MO DirGail Tate, SOC Mgr
Karen TurkGnd Stwr
Don WoodraskaOps/DA
QA Purchasing ExpeditorTom Lowensohn
TBD Students
Dave CrotserOptical
Susan TowerEEB/Door
James MacAnalysis MIT-LL/SI
Greg BerthiaumeUSC/Swales/SIAndrew Jones
TBD Students
Jennifer YoungThermal
Structure/Harness
MEGS ASAM
EEB MEGS BESP
Flt/GndSoftware CCDs
CCDElectronics
EVE Instrument
• The Components of EVE– Subsystems built at LASP
• MEGS – Multiple EUV Grating Spectrograph (2 channels, CCD and photodiode detectors)
• EEB – EVE Electronics Box (flgiht computer)
• Software (flight and ground)– Subsystems built at USC
• ESP – EUV Spectrophotometer (single channel, photodiode detectors) – Swales (mechanical design); SI (electrical design)
– Subsystems built at MIT-LL• CCD camera and logic for MEGS
– Subsystems built at SI• Power Supplies for CCD camera
systems
EVE Overview Page 11SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Summary Overview• EVE is currently on budget and on schedule• Developed detailed schedules
– schedule slack remains intact and incorporates 2 months in subsystem development and 2 months in EVE I&T
• EVE has successfully completed all major reviews to date– SDO SRR/SCR (April 8-11, 2003)
• 9 EVE RFAs total, responses submitted, 3 remain open, all can be closed• All critical actions are closed
– EVE PDR (December 17-18, 2003)• “The material presented provided a very good demonstration that
the EVE team has, in general, met the design and analyses status requirements for a PDR and is prepared to move into more detailed design activity” - Thomas Cygnarowicz, Chair, Systems Review Office
• 33 RFAs total, received March 1, 2004, no critical actions identified
• EVE Review & Working Group Participation– Participated in 2 Project peer reviews to date– Held 18 instrument peer reviews to date (includes independent external reviewers)– Participated in 13 working group and technical interchange meetings to date
• Includes 3 meetings with the project in the development of the ICDs
EVE Overview Page 12SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Summary Overview Continued
Program Management Plan √ Safety and Handling Plan √
Configuration Management Plan √ Risk Assessment and Management Plan √
Instrument Calibration Plan √ Software Development Plan √
Descope Plan √ Performance Verification Plan χ
• Detailed Schedules are in place– Tracked, updated and reported monthly
• Flowed Requirements– Delivered EVE Product Assurance Implementation Plan (PAIP)– Flowed Program & LASP requirements to subcontractors– ICDs in formal review– Assembled system level requirements– Have written and are writing subsystem requirements
• Implemented Performance Assurance– Performing FMEAs (draft in review at LASP)– Single point failure trade study completed December 2004– Preliminary parts list submitted
Program Plans
EVE Overview Page 13SDO Preliminary Design Review (PDR) – March 9-12, 2004
Changes Since SCR
SCR Now Effects CommentsOFS – Single Channel (2 gases)
OFS
Descoped (10/2003)
*Loss of spectral resolution & direct coverage at long wavelengths*Risk reduction descope (considered high risk to cost and schedule)
Replaced by enhanced ESP, MEGS-P photometer channels, 5 additional rocket underflightsOFS - new technology development, insufficient technical maturity, continued development did not fit with available resources
ESP – Single Channel
ESP - Single Channel Enhanced
*Extend ESP spectral coverage*Reduced risk approach to retaining inflight cal capabilities
Rescope and enhance to cover loss of OFS measurementsCustom diodes allow for respread of coverage to new desired range
MEGS – 2 Channels
MEGS - 2 Channels Enhanced
*Change MEGS zero order light traps to Si diode traps that provide 8 channels w/filter wheel utilization*Reduced risk approach to retaining inflight cal capabilities
Rescope and enhance to cover loss of OFS measurementsTIMED SEE & SOURCE XPS photometer heritage
Aperture Doors (1-Shot) Addition
*Slight increase in mass*Address potential contamination concerns (reduce risk)
Heritage from Messenger/MASCS designIn Review/Approval process w/Project
5 Rocket Underflights
* 5 underflights required to meet 25% absolute accuracy requirement with descope of OFS
Fabricate rocket instruments (MEGS/ESP prototypes) in Phase C instead of Phase E
Note: New configuration meets all SDO EVE science requirements
EVE Overview Page 14SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Instrument
ESP Electronics
Daughterboards
Motherboard
I/O Boards
Flexure mount (3)
Card guides
CCD Power Supply Electronics
EEB(EVE Electronics Box)
CCD Radiator with isolationmounts
MEGS Instrument
MEGS B
MEGS A
SAM
Support Structure
ESP Instrument
CCDÕs
CCD ElectronicsRadiator
EVEOptical package
EVEon Instrument Module
EVE Overview Page 15SDO Preliminary Design Review (PDR) – March 9-12, 2004
MEGS Optical Overview
MEGS Cross Section
CCD Electronics
CCD
Grating 1
Grating
Grating
FilterMech Slit + 0th order trap
MEGS P0th order traps
MEGS A
MEGS B
SAM
Aperture DoorMechanisms
FilterMech
FilterMech
ESP Mount Surface
EVE Overview Page 16SDO Preliminary Design Review (PDR) – March 9-12, 2004
ZX
YGrating
Entrance Slit Baffles
Aluminum Filter
C/Ti/C Filter
58-64nm30.4nm
33-38nm24-27nm
17-22nm
0.1-5nm
Baffles/Shielding
ESP Optical/Mechanical Layout
EVE Overview Page 17SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Electrical Block Diagram
12MHz Clock
PROM64KB
EEPROM2MB
SRAM2MB
1553
PCI Bridge
ColdFireProcessor
AnalogServices
Local Bus
Subsystem Data Node
EVE Electronics Box (EEB)EVE Optics Package (EOP)
EUV SpectroPhotometer
HSB
Instrument Controller Electronics
SpaceWire
Ping-Pong SRAM
2X 2.5Mx32
Science Processing I/F
(SPI/F)RT54SX72S
PCIDIFPGA
SpaceWire I/F (SPI/F)
RT54SX72S
40MHz
PCI
Brid
ge
20MHz System Clock
Power Services
PSFPGA
DAC
PCI
Brid
ge
Optos
Propor.Heater
H-Bridge Control
Power & LPT
H-Bridge Drivers
Resolver
Cover Switches
Filter Windings
Operational Heaters
Filter Positions
Contam. Covers
Filtered +28V
MEGS A & B Power ControlESP Power Control
Low Voltage Power Converter
Diode Isolation
4-bit DACs
Inrush Limiter
Current Sources
Filters
Opto
Turn-on DelayFilters
Opto
±15V+5V
+3.3V
DC-DC EMI
EMI
DC-DC
MOSFET Switches
MOSFET Switch
MEGS A
ESP
FF-Lamps
MEGS B
+28V S/C
Filtered +28V
ADC
ADC
Clocks
+
+
-
-
MuxTemps
Sync
VoltagesCurrents
ActelRT54SX72S
FPGA
MEGS A
CCD Radiator
Filter Mechanism(s)
Covers
MEGS A CCD Electronics
+24V Filter
+18V
+8V
-18V
+15V Filter
+2.5V Filter
+5V Filter
-15V Filter
+15V Reg.
+2.5V Reg.
+5V Reg.
-15V Reg.
MEGS A Digital Electrometers
MEGS A CCD Power Board
MEGS B
(9X)
Dig
ital
Elec
trom
eter
s
ESP Counters * I/F Logic
A1020 FPGA
ESP Control Electronics
SAM
cPC
I Bac
kpla
ne
Grid Bias
HVPS
DC-DC
In-Rush & EMI Filters
Temps & Voltage Mon’s.
ESP Power Board
+15V+5V
-15V
Custom DC-DC
In-Rush & EMI Filters
Temps & Voltage Mon’s.
MEGS A CCD Power
Sync
+24V+18V
+8V-18V
TT T
Op. Htr. Decont. Htr. Supp. Htr.
Multiple EUV Grating Spectrograph
•Redundant Spacecraft Interfaces–1355 (High Speed Bus)–1553 (Command and HK Telemetry)– Instrument power– Survival heater power– Decontamination heater power – Temperature monitors (5)
EVE Overview Page 18SDO Preliminary Design Review (PDR) – March 9-12, 2004
Mitigation of Technical Challenges• CCD Technical Mitigation
– Mechanical/Thermal Breadboard – vibration test completed, FEM correlated, and design refinements in process
– Power Supply Breadboard – revealed that ripple requirements for CCD power cannot be met with DC/DC converters from the Project’s common buy
•The subsequent trade study led to the incorporation of custom power supplies from Space Instruments for the CCD electronics
– CCD Power and Grounding TIM – established ground and isolation requirements for the CCD subsystem (LASP, SI, MIT/LL, Ball)
•Resulted in the change from chassis to analog grounds at the CCD header assembly
– CCD Life Testing – planned life tests will verify in band sensitivity (QE) and total EUV fluence over mission life prior to the CDR
– Engineering Models – engineering model CCD subsystems will verify noise performance prior to CDR
CCD Power Supply Breadboard Results(with filtering)
CCD Mechanical System Vibration
EVE Overview Page 19SDO Preliminary Design Review (PDR) – March 9-12, 2004
Mitigation Continued• The Filter Wheel breadboard has
successfully demonstrated a sound design– Vibration (random) – tests have
successfully demonstrated the integrity of filters and mounting scheme (and resulted in the identification of materials not suitable for use in unsupported filters: Sn)
– Thermal Cycle – tests have successfully demonstrated filter wheel integrity over the survival temperature range
– Filter Attenuation and Scatter – initial testing has verified that filters exceed the visible extinction requirement and the visible rejection requirements (light leaks/scatter)
– Life Cycle and Acoustic are planned prior to CDR (no current concerns)
• Prototype filter transmissions are in measurement at SURF
350x10-12
300
250
200
150
100
50
Am
ps300250200150100500
Step # (50 micron step)
300 250 200 150 100 50 0
1 X 7 mm Foil Filter
Filter Wheel Vibration @ Ball Aerospace
Red = After Env.Blue = Before Env.
(=638.0nm)
10-6 req. 10-7 extinction
EVE Overview Page 20SDO Preliminary Design Review (PDR) – March 9-12, 2004
Mitigation Continued• EVE prototype structural mounts are
complete – Testing planned for May 2004– Vibration and thermal cycle– Use optic cube to verify alignments
before and after tests
• Grating Specification TIM – Reviewed the established grating
specifications for scatter, optical parameters, and manufacturability
– Gratings are on order • Swales under contract to perform
Contamination Control engineering efforts
– Contamination Control Plan – Mass transport models– Participate in SDO contamination control
efforts
EVE Overview Page 21SDO Preliminary Design Review (PDR) – March 9-12, 2004
Technical Mitigation Timeline2003 2004
2 3 4 1 2 3 4 1EVE Breadboard Schedule
EVE Major Milestones
Breadboard/ETU Development
Filter Wheel Mechanism
Aperture Doors
CCD Mech-Therm Breadboard
CCD Life Test Unit
ETU CCD Sys Elect Verification
SDN Breadboard
EEB ETU
SRR/SCR CSR IPDR ICDR
5/13/15 8/2 9/1
9/15
3/15 9/15
5/110/10
Vib#1
11/10
Vib#2
2/19
Pw r & Gnd TIM
4/30
DesignRefinements Complete
8/2
Vib
9/1
Thermal9/15
5/56/24
Unit Del
9/3
Passivation Decision9/15
1/17/2
ETU PSComplete
9/30
CCD Del
11/15
Verif ication Complete
12/1
3/31SDN BB
4/15SSIM
6/25/14
BP
6/3
LVPC
7/22
Box
8/27
SDN
10/8
PS/ICE12/1
Vib Test 9/16
Scattered Light 10/1
Thermal 9/23
Filter Trans/SURF 50% Complete Life Test Acoustics
8/3 Actuator Del
8/13 Vib
8/20 Thermal
EVE Overview Page 22SDO Preliminary Design Review (PDR) – March 9-12, 2004
ESP (@ LASP) Performance TestsVibration, Thermal Vac
EVE Instrument Development &Test
EEBBoard level testingFlight code development
MEGSIntegrationPerformance TestsVibrationThermal/Vacuum Tests
EVE
EEB IntegrationPerformance TestsAlignmentsPre-Environmental CalVibration TestAcousticEMI/EMC TestThermal/Vacuum TestPost-Env Cal
CCD Detector & LogicManufacturePerformance Tests
ESP Mechanism Life-CyclePhotodiode CalibrationSlit Area MeasurementGrating CharacterizationElectronics Test
MEGSMechanism Life-CycleFilter TransmissionSlit Area MeasurementGrating CharacterizationDetector CharacterizationElectronics Test
EEBFunctional testing w/Instrument simulators
ESP IntegrationPerformance Tests
SDOS/C integrationPerformance TestsVibration TestAcoustic TestEMI/EMC TestThermal/Vacuum Test
Component Level Testing Instrument Level Testing Observatory Testing
MIT LL
USC
GSFC
LASP
Site Key:CCD System Assembly IntegrationPerformance Tests
EVE Overview Page 23SDO Preliminary Design Review (PDR) – March 9-12, 2004
Mass & Power Summary
MASS
Component Mass (kg)MEGS 23.61
ESP 3.27
EEB 14.96
Structure 2.82
Harness 2.35
Miscellaneous 1.43
Total 48.44
EVE Allocation 52.00
EVE Allocation Margin 6.8%
POWER
Component Sunlit Ave (W)
Eclipse Ave (W)
Peak (W)
MEGS (+ OP heaters) 36.3 37.3 67.0
ESP 1.5 1.5 1.5
EEB 29.7 29.7 31.4
Total 67.5 68.5 99.9
EVE Allocation 76.0 76.0 -
EVE Allocation Margin 11.2% 9.9% -
Additional Services
Survival Heater 35.6 36.6 98.5
CCD Decontam Heater 63.0 - 98.4
Note: project holds additional 20%above allocation margin
EVE OpticalPackage
EEB
EVE Overview Page 24SDO Preliminary Design Review (PDR) – March 9-12, 2004
Power & Mass Trends
EVE Mass Trend
0.0
10.0
20.0
30.0
40.0
50.0
60.0
Date
Kg
Mass Trend
EVE Power Trend
50.055.060.065.070.075.080.085.090.095.0
100.0
Date
Wat
ts
EVE Normal Mode Power
EVE Overview Page 25SDO Preliminary Design Review (PDR) – March 9-12, 2004
2002 2003 2004 2005 2006 2007 20083 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1
EVE Summary Schedule
Mission Milestones
EVE Milestones
Instrument Development
EEB
Harness
CCD
MEGS
ESP
Flight Software
Ground Software
I & T
Delivery to SI
SRR/SCR ICR PDR CDR PER PSR LAUNCH
SRR/SCR CSR IPDR ICDR IPER IPSR Inst. Del. to SI
6/2
3/31
SDN BBDelivery
ETU InitialI&T Complete 1/5
11/2
11/3
12/17
ETUComplete
7/22
11/3
6/28
Test UnitDelivered 10/5
ETUDelivered
3/18
5/1
10/25
5/1 1/11
9/3
4/15
Interfacew/SDN BB
1/5
EEB ETU toFSW Test Bed
2/9
5/26
3/23
OASIS CC Release
12/28
Ground OPS Release
9/8
1/3 11/20
11/21 Instrument Delivery to Spacecraft I&T
Slack (40 days)
Slack (40 days)
ETU
ETU
Final Pre-EVE I&TProcessing/Test @LASP
FU Delivery
FUComplete
FU Delivered to EVE I&T
Slack (20 days) Slack (20 days)
FU
FU
Critical Path
EVE Summary Schedule
EVE Overview Page 26SDO Preliminary Design Review (PDR) – March 9-12, 2004
Current Risks Status• Current concerns that require further analysis/resolution
Concern Mitigation StatusMEGS CCD detector system susceptibility noise sources (e.g., Ka band and S-band antenna emissions, other); late delivery of CCD ETU to support design verification
Analysis by MIT, LASP, and SDO spacecraft team; perform test verification with EVE breadboard CCD assembly
1) General noise susceptibility evaluation currently in progress2) Test verification November 2004 (delivery of CCD ETU is the schedule driver)
Filter Mechanism motor lubrication potential migration issues
Analysis of current design implementation (LASP/Swales); study issues observed by Chandra
Evaluation currently in progress - anticipated resolution May 2004
MEGS CCD cooling system functionality
Early breadboard/ functional characterization testing
Thermal testing with breadboard CCD mechanical assembly planned for June 2004
SDN Hardware and Software Delivery Schedules
Develop optimum EVE schedule need dates
1) Submitted to GSFC development teams for review/feedback2) Early deliveries on track
Low Concern Moderate Concern High Concern
EVE Overview Page 27SDO Preliminary Design Review (PDR) – March 9-12, 2004
Current Risks Status (Continued)
• Current concerns that require further analysis/resolution
Concern Mitigation StatusMEGS CCD passivation process selection
Evaluate test unit that has passivation process applied
1) Test unit delivery from MIT in early May 20042) EUV sensitivity evaluation performed by LASP
ESP signal-to-noise level characterization for the long wavelength channels
Analysis by USC/LASP Analysis currently in progress - anticipated conclusion March 2004
Filter mechanism filter robustness
Build breadboard and perform environmental testing (vibration, thermal, acoustics)
1) Vibration and thermal testing have been completed 2) Perform acoustics testing May 2004
Low Concern Moderate Concern High Concern
EVE Overview Page 28SDO Preliminary Design Review (PDR) – March 9-12, 2004
Conclusion
• The EVE Preliminary Design Review was successfully completed December 17-18, 2003
• Design requirements are met• Power and mass are within allocations• EVE is currently in the detailed design phase• Risks are identified, tracked, and mitigation strategies are in
place (currently carrying only low to moderate risks)
EVE Overview Page 29SDO Preliminary Design Review (PDR) – March 9-12, 2004
Supplemental Information
EVE Overview Page 30SDO Preliminary Design Review (PDR) – March 9-12, 2004
Summary of EVE Reviews & Meetings
Review / Meeting Date LocationEVE Science Requirements Workshop October 29-30, 2002 LASPUSC Technical Interchange Meeting January 8-9, 2003 USCMEGS B Optical Conceptual Design Peer Review January 27, 1999 LASPIEM Microprocessor Conceptual Design Peer Review February 26, 1999 LASPEVE System Requirements Review / Retreat March 10, 1999 LASPMEGS CCD Mechanical Thermal Conceptual Design Peer Review March 23, 1999 LASPEVE Filter Mechanism Design Peer Review April 2, 1999 LASPMEGS A Optical Conceptual Design Peer Review April 15, 1999 LASPMEGS Opto-Mechanical Conceptual Design Peer Review April 15, 1999 LASPUSC Interface Review / TIM April 22-23, 2003 LASPMEGS Solar Aspect Monitor Conceptual Design Peer Review April 22, 1999 LASPSDO SRR / SCR April 8-10, 2003 GSFCMIT-LL Technical Interchange Meeting April 10, 1999 MITIEM Low Voltage Power Supply Card Conceptual Design Peer Review April 29, 1999 LASPEVE Thermal System Conceptual Design Peer Review April 30, 1999 LASPMEGS Electrical Conceptual Design Peer Review May 7, 1999 LASPEVE System Mechanical Conceptual Design Peer Review May 7, 1999 LASPEVE System Electrical Conceptual Design Peer Review May 12, 1999 LASPEVE Flight Software Conceptual Design Peer Review May 19, 1999 LASPEVE Ground Operations & Science Data Processing Conceptual Design Peer Review May 19, 1999 LASPEVE Concept Study Report Review May 22-23, 2003 LASPEVE USC-LASP Technical Interchange Meeting, Mechanical Thermal July 7, 1999 LASPSDO EVE ICD Meeting #1 August 19-20, 2003 LASPEVE Detector-to-Downlink Preliminary Design Peer Review September 11, 1999 LASPUSC Technical Interchange Meeting October 8-9, 2003 USCEVE Flight Software Preliminary Design Peer Review October 14, 1999 LASPEVE Ground Operations Preliminary Design Peer Review October 15, 1999 LASPEVE Science Data Processing Preliminary Design Peer Review October 16, 1999 LASPSDO EVE ICD Meeting #2 October 21-22, 2003 GSFCMIT-LL Technical Interchange Meeting October 23, 1999 MIT
EVE Overview Page 31SDO Preliminary Design Review (PDR) – March 9-12, 2004
EVE Reviews & Meetings Continued
EVE PDR December 17-18, 2003 LASPMEGS-Photometer Working Group January 15, 2004 LASPMEGS Grating Specification Peer Review January 22, 2004 LASPSDO Risk Management TIM January 29,2004 LASPSDO EVE ICD Meeting #3 February 3-4, 2003 LASPSDO Grounding, Shielding and Bonding Workshop February 5, 2004 LASPCCD Power and Gounding Working Group February 19,2004 LASP