euv variability experiment (eve)

EVE Overview SDO Preliminary Design Review (PDR) – March 9-12, 2004

EUV Variability Experiment(EVE)

Rick KohnertEVE Systems Engineer

[email protected]

EVE Instrument Overview


OUTLINE

• Science Overview• Requirements• Summary Overview• Design Implementation• Mitigation Efforts• Development Flow• Schedule

• Risk Assessment


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 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


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


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)


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 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


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


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 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 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


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 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


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


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 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)


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


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


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


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


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


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


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


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


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


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


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)


Supplemental Information


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 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

euv variability experiment (eve)

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