page 1cospar2006-a-01469 hmi hmi helioseismic and magnetic imager for the solar dynamics observatory...

COSPAR2006-A-01469 HMI

HMIHelioseismic and Magnetic Imager for the

Solar Dynamics Observatory

BAO – Beijing, July 2006

P.H. Scherrer, J. Todd Hoeksema

And the HMI Team

Stanford University

Stanford Lockeed Institute for Astrophysics and Space Research


Outline

• The SDO Mission

• Instrument Overview

• Calibration Activities

• HMI Science Goals

• Observations & Observables

• Joint Science Operations Center


The Science of SDO


SDO Science Requirements

•What mechanisms drive the quasi-periodic 11-year cycle of solar activity?

•How is active region magnetic flux synthesized, concentrated & dispersed across the solar surface?

•How does magnetic reconnection on small scales reorganize the large-scale field topology and current systems?

•How significant is it in heating the corona and accelerating the solar wind?

•Where do the observed variations in the Sun’s total & spectral irradiance arise, how do they relate to the magnetic activity cycle?

•What magnetic field configurations lead to CMEs, filament eruptions and flares which produce energetic particles and radiation?

•Can the structure & dynamics of the solar wind near Earth be determined from the magnetic field configuration & atmospheric structure near the solar surface?

•When will activity occur and is it possible to make accurate and reliable forecasts of space weather and climate?


Sensing the Sun from Space

• High-resolution Spectroscopy for Helioseismology and Magnetic Fields

– Observe ripples and polarization properties on the surface of the Sun

– Sound waves require long strings of continuous data to interpret—satellites may have no day/night cycle

– Convection zone velocities and magnetic fields require high spatial resolution

• Coronal Imaging

– Observe bright plasma in the corona at ultraviolet wavelengths —can’t be seen from ground

– Temperatures of the plasma range from 50,000 K to >3 million K

– High spatial resolution to see the detailed interaction of the magnetic field and the plasma

– High time resolution is required to see how those features develop

• Spectral Irradiance

– Measure the total energy in narrow wavelength bands

– Measure from space to avoid the twinkling and absorption of atmosphere

– Essential for models of the ionosphere

• Coronagraphs

– Light scattered from the corona and solar wind

– Track material as it exits the Sun and moves through the solar system

• Energetic Particles and Fields

– Point measurements from many platforms to resolve structure


The SDO MissionNASA/LWS Cornerstone Solar Mission

• NASA and three Instrument Teams are building SDO

– NASA/ Goddard Space Flight Center: build spacecraft, integrate the instruments, provide launch and mission operations

– Lockheed Martin & Stanford University: AIA & HMI

– LASP/University of Colorado: EVE

– Launch is planned for August 2008 on an Atlas V EELV from Cape Canaveral

– SDO will be placed into an inclined geosynchronous orbit ~36,000 km (21,000 mi) over New Mexico for a 5-year mission

– Data downlink rate is 150 Mbps, 24 hours/day, 7 days/week (1 CD of data every 36 seconds)

– Data is sent to the instrument teams and served to the public from there

• The primary goal of the SDO mission is to understand, driving towards a predictive capability, the solar variations that influence life on Earth and humanity’s technological systems by determining:

– How the Sun’s magnetic field is generated and structured

– How this stored magnetic energy is converted and released into the heliosphere and geospace in the form of solar wind, energetic particles, and variations in the solar irradiance.

Atlas V carries Rainbow 1 into orbit, July 2003.


The SDO SpacecraftThe SDO Spacecraft

The total mass of the spacecraft at launch is 3200 kg (payload 270 kg; fuel 1400 kg).

Its overall length along the sun-pointing axis is 4.5 m, and each side is 2.22 m.

The span of the extended solar panels is 6.25 m.

Total available power is 1450 W from 6.5 m2 of solar arrays (efficiency of 16%).

The high-gain antennas rotate once each orbit to follow the Earth.

AIA (1 of 4 telescopes)

EVE (looking at CCD radiator and front)

HMI (looking down from top)

High-gain antennas (1 of 2)


EUV Variability Experiment

• EVE is the Extreme ultraviolet Variability Experiment

• Built by the Laboratory for Atmospheric and Space Physics at the University of Colorado in Boulder, CO

• Data will include– Spectral irradiance of the Sun

• Wavelength coverage 0.1-105 nm

• Photodiodes to give activity indices

• Full spectrum every 20 s

– Information needed to drive models of the ionosphere

– Cause of this radiation

– Effects on planetary atmospheres


SDO Operations

• Mission operations for SDO are at NASA's Goddard Space Flight Center near Washington, DC.

• Communications with the spacecraft are via two radio dishes at NASA's site in the White Sands Missile Range in New Mexico.

• The main tasks of the controllers are to keep SDO pointing at the Sun, maintain its inclined geosynchronous orbit, and keep the data flowing.

• A scientific team, led by NASA and instrument project scientists, plans and executes programs of observations with SDO’s 3 instruments suites, and analyzes the data.

• Unique Operations Mode

– Few observing modes: turn it on and let the data flow!

– Raw images are sent to the ground for processing

– Data is made available soon after downlink; people can use the data in near-real-time

– Campaigns and collaborations are coordinated where convenient, but the data is always available

TDRSS antennae in White Sands Missile Range


Mission Orbit Overview

• The SDO geosynchronous orbit will result in two eclipse seasons with a variable daily eclipse each day

– The two eclipse seasons will occur each year

– During each eclipse season, SDO will move through the earth’s shadow- this shadow period will grow to a maximum of ~72 minutes per day, then subside accordingly as the earth-sun geometry moves out of the SDO eclipse season

• Eclipse season effects:

– Instrument• Interruption to SDO science collection

• Thermal impacts to instrument optical system due to eclipse

– Power • Temporary reduction or loss of power from solar arrays

• Battery sizing includes eclipse impact

– Thermal• S/C thermal design considerations due to bi-annual eclipses


HMI Instrument Overview


Helioseismic & Magnetic Imager

• HMI is the Helioseismic and Magnetic Imager

• Built at Stanford University and Lockheed

Martin in Palo Alto, CA

• Two 4096 x 4096 CCDs

• Instrument is designed to observe polarized

light to measure the magnetic field


HMI Overview

• The primary goal of the Helioseismic and Magnetic Imager (HMI) investigation is to study the origin of solar variability and to characterize and understand the Sun’s interior and the various components of magnetic activity.

• HMI makes measurements of several quantities

– Doppler Velocity (13m/s rms.).

– Line-of-sight (10G rms.) and vector magnetic field.

– Intensity

– All variables all the time with 0.5” pixels.

– Most at 50s or better cadence.

– Variables are made from filtergrams, all of which are downlinked.

• Higher level products will be made as part of the investigation.

• All data available to all.

• Launch in August 2008. 5 Year nominal mission.

• Education and Public Outreach program included!


Instrument Overview

• Optics package

– Telescope section

– Polarization selectors – 3 rotating waveplates for redundancy

– Focus blocks

– Image stabilization system

– 5 element Lyot filter. One element tuned by rotating waveplate

– 2 Michelson interferometers. Tunable with 2 waveplates and 1 polarizer for redundancy

– Reimaging optics and beam distribution system

– Shutters

– 2 functionally identical CCD cameras

• Electronics package

• Cable harness


Image stabilization mirror

CCD fold mirror

CCD fold mirrorFold mirror

¼ Waveplate ½ Waveplates

Telescope lens set Telecentric

lens

Calibration lensesand focus blocks

Front window filter

Relay lens set

Blocking filter

BDS beamsplitter

NarrowbandMichelson

Polarizer

ISS beamsplitterand limb tracker assembly

Tuningwaveplates

Beam control lens

Lyot

WidebandMichelson

CCD

CCD

Shutter assemblies

Aperture stop

Instrument Overview – Optical Path

Optical characteristics:Focal length: 495 cmFocal ratio: f/35.2Final image scale: 24m/arcsec = 0.5”/pixelPrimary to secondary image magnification: 2Focus adjustment aange: 16 steps of 0.4 mm

Filter characteristics:Central wavelength: 613.7 nm FeIFront window rejects 99% solar heat loadFinal filter bandwidth: 0.0076 nmTuning range: 0.069 nmAll polarization states measurable


Ray trace


Instrument Overview – HMI Optics Package (HOP)

OP Structure

Telescope

Front Window

Front Door

Vents

Support Legs (6)

Polarization Selector

Focus/Calibration Wheels

Active Mirror

Limb B/S

Alignment Mech

Oven Structure

Michelson Interf.

Lyot Filter

Shutters

Connector Panel

CEBs

Detector

Fold MirrorFocal Plane B/S

Mechanical Characteristics:Box: 0.84 x 0.55 x 0.16 mOver All: 1.19 x 0.83 x 0.29 mMass: 39.25 kgFirst Mode: 63 Hz

YX

Detector

Limb Sensor

Z


HMI Assembly Status

Optics Package Assembly

Detector Assembly(Non-Flight)

CEB (Non-Flight, DM1)

Flex-Cables(Eng Model)

Telescope(Flight)

Front Window(Flight)

Primary work after Sun testing:• Bond optics in place• Replace painted parts (including the oven)• Replace one HCM and focus/cal optical mounts

ISS Mirror(Flight)

Polarization Selector(Flight)

Focus/Cal Wheels(Flight)

Limb Sensor(Non-Flight)

ISS Beam Splitter(Flight)

Oven Assembly(non-flight)Parts to replace:E1 and E2 in LyotNB MichelsonPainted housing

BDS Beamsplitter(Flight, hidden by shutter)

Shutters(Flight)

BDS Fold Mirror(Flight)

CCD Fold Mirror(Flight, hidden by detector)

Alignment Mechanism(Flight, hidden in view)

Internal Harness(Flight, not complete)

Limb Pre-amp Box(Flight, not complete)

StructureW/ legs and heaters(Flight)

Oven Controller(ETU)


Status - Michelsons

Michelson ETU


HMI Assembly Status

Structural model testing completed ETU oven testing completed BB HEB fabrication completedSUROM acceptance test completed

mission CDR

Received flight MichelsonsAll flight optics in house

Received flight metering tubeCompleted telescope alignment

Received flight structureStart alignment on GSE bench

Hollow core motors completedReceived DM cameras

Received 4 grade zero CCDs

Alignment mechanism completedStarted optical alignment of HOP

BB HEB and EGSE readyShutter & F/C wheels completed

Internal harness completed

Lyot completedInternal mechanisms tested

Focal plane completedOven completed

First image


Status - Cameras

Image of CCD Image with CCD


HMI Testing Progress

12/22/06 02/01/0601/30/0601/25/0601/11/06

Tests Performed:

Initial set up w/ lampFocus test w/ lampDistortion, field curvature and MTF w/ lampFocus test w/ SunFilter wavelength dependence w/ Sun

Filter wavelength dependence w/ laserField curvature and MTF w/ SunPolarization calibration w/ Sun

Tests In Progress:

Laser dotBefore holidayNo relay lensNo Lyot No frt Window

Special targetLamp - stim telLyot installedTemp mnt for relay lensNot fully aligned stim tel

Air Force targetLamp - stim telAll together

Laser intensity improved

“HMI is Alive”First Image “Special Target”

First Lamp Image “Ready to Test”Instrument All Together “No More Moon”

Better Laser Image “It’s a Beautiful Day”First Sun Image

Just sunlightWith air/vac corrector


HMI Calibration Activities


Status

• Instrument is almost complete

– Only one non-flight Camera installed

– No CIF and DCHRI boards installed

– No radiators

– No heaters and thermistors

– No vents

– No front door

– Non flight cover

– ISS still being worked

– Many items need to be mounted permanently

– Except, perhaps, for one of the Michelson all optics are flight

• In-Air and vacuum calibrations later this summer

• Delivery in March 2007

• Launch in August 2008


Upcoming Tests

• Suntest2

– Mostly repeat what was done in first suntest

• Verify that instrument has been properly reassembled

– Check for gross errors

– Check that earlier problems have been corrected

• Eg. Birefringence in focus block

– Provide data to adjust various components

• Eg. Calmode lenses, waveplate rotation, CCDs, …

– Check software

• Must be in good shape before actual calibrations

• In-air calibration

– Gather actual calibration data

• Some, such as part of polarization may not be doable in vacuum

• Vacuum calibration

– Repeat most in-air calibrations with lower noise

– Some items only doable in vacuum (E.g. Noise tests)


Sun Test Objectives

• Learn how to operate the HMI optics package.

• Learn how to characterize/calibrate the instrument.

• Discover gross errors in design or workmanship of the HMI optics package.

• Determine position of focus to set the final shim on the secondary lens.

• Determine position of waveplates in polarization selector to set the final orientation relative to hollow core motor step locations.

• Results of the Sun test will directly feed into the plans and procedures for the formal test and calibration series.

• The Sun test does not provide formal verification of any requirements.

• The Sun test does not provide final calibration data.

• The instrument had not been finally assembled during first Sun test.

– Several components were missing.

– Several components have since been changed.

– Test setup was under development.

– Test procedures and analysis software were under development.


Calibration Matrix

123456789

1013141617181920212223

24

252628

30

31

32333435363839

A B C F G N O P QTest Group Property First

SunLight Source Status

1 Image quality Distortion Yes Lamp Not yet finished2 Image scale Yes Sun All OK

3a MTF Yes Lamp Minor problem3b MTF Yes Sun Taken Bad4a Focus Yes Lamp Really bad4b Field curvature Yes Lamp4c Focus Yes Sun4d Field curvature Yes Sun Taken*7 Ghost images Yes? All? ?????*8 Scattered light Yes? All? ?????10 CCD and Camera Flat field Yes Lamp11 Linearity Yes Lamp

*12a Quadrant crosstalk No? Lamp ?????*12b Quadrant crosstalk No? Laser ?????13a Contamination Yes Lamp13b Contamination Yes Sun13c Contamination Yes Laser14 Image motions Offset and distortion Yes Lamp15 Filter transmission Wavelength and

spatial dependenceYes Laser + Sun

16 Angular dependence Yes Laser + Sun

17 Stability No? Laser or Sun? ?????19 Throughput Yes Sun

21a Polarization All sorts of stuff Yes Lamp

21b Polarization All sorts of stuff Yes Sun

22 Observables performance

Doppler Yes Sun

23 Line of sight Yes Sun24 Vector Yes Sun

*25 Thermal effects Pointing No? Lamp ?????*26 Focus No? Lamp ?????28 Alignment legs Range and step size Yes Lamp29 Repeatability Yes Lamp


Image Quality

• Distortion

• Image scale

• MTF

• Focus and field curvature

• Ghost images and scattered light

• Contamination

• Image motions


Image Wobble


Image focus


HMI Testing Progress

First Magnetogram First Dopplergram


HMI Science Goals


Primary goal: origin of solar variability

• The primary goal of the Helioseismic and Magnetic Imager (HMI) investigation is to study the origin of solar variability and to characterize and understand the Sun’s interior and the various components of magnetic activity.

• HMI produces data to determine the interior sources and mechanisms of solar variability and how the physical processes inside the Sun are related to surface and coronal magnetic fields and activity.


HMI Science Objectives

• HMI science objectives are grouped into five broad categories:

– Convection-zone dynamics

• How does the solar cycle work?

– Origin and evolution of sunspots, active regions and complexes of activity

• What drives the evolution of spots and active regions?

– Sources and drivers of solar activity and disturbances

• How and why is magnetic complexity expressed as activity?

– Links between the internal processes and dynamics of the corona and heliosphere

• What are the large scale links between the important domains?

– Precursors of solar disturbances for space-weather forecasts

• What are the prospects for prediction?

• These objectives are divided into 18 sub-objectives each of which needs data from multiple HMI data products.


A. Sound speed variations relative to a standard solar model.

B. Solar cycle variations in the sub-photospheric rotation rate.

C. Solar meridional circulation and differential rotation.

D. Sunspots and plage contribute to solar irradiance variation.

E. MHD model of the magnetic structure of the corona.

F. Synoptic map of the subsurface flows at a depth of 7 Mm.

G. EIT image and magnetic field lines computed from the photospheric field.

H. Active regions on the far side of the sun detected with helioseismology.

I. Vector field image showing the magnetic connectivity in sunspots.

J. Sound speed variations and flows in an emerging active region.

B – Rotation VariationsC – Global Circulation

D – Irradiance Sources

H – Far-side Imaging

F – Solar Subsurface Weather

E – Coronal Magnetic Field

I – Magnetic Connectivity

J – Subsurface flows

G – Magnetic Fields

A – Interior Structure

HMI Data Product Examples


HMI Science Objectives

• Convection-zone dynamics and the solar dynamo

• Structure and dynamics of the tachocline

• Variations in differential rotation

• Evolution of meridional circulation

• Dynamics in the near surface shear layer

• Origin and evolution of sunspots, active regions and complexes of activity

• Formation and deep structure of magnetic complexes of activity

• Active region source and evolution

• Magnetic flux concentration in sunspots

• Sources and mechanisms of solar irradiance variations

• Sources and drivers of solar activity and disturbances

• Origin and dynamics of magnetic sheared structures and d-type sunspots

• Magnetic configuration and mechanisms of solar flares

• Emergence of magnetic flux and solar transient events

• Evolution of small-scale structures and magnetic carpet

• Links between the internal processes and dynamics of the corona and heliosphere

• Complexity and energetics of the solar corona

• Large-scale coronal field estimates

• Coronal magnetic structure and solar wind

• Precursors of solar disturbances for space-weather forecasts

• Far-side imaging and activity index

• Predicting emergence of active regions by helioseismic imaging

• Determination of magnetic cloud Bs events


HMI Science Analysis Plan

Magnetic Shear

Tachocline

Differential Rotation

Meridional Circulation

Near-Surface Shear Layer

Activity Complexes

Active Regions

Sunspots

Irradiance Variations

Flare Magnetic Configuration

Flux Emergence

Magnetic Carpet

Coronal energetics

Large-scale Coronal Fields

Solar Wind

Far-side Activity Evolution

Predicting A-R Emergence

IMF Bs Events

Brightness Images

Global Helioseismology

Processing

Local Helioseismology

Processing

Version 1.0w

Filtergrams

Line-of-sightMagnetograms

Vector Magnetograms

DopplerVelocity

ContinuumBrightness

Line-of-SightMagnetic Field Maps

Coronal magneticField Extrapolations

Coronal andSolar wind models

Far-side activity index

Deep-focus v and cs

maps (0-200Mm)

High-resolution v and cs

maps (0-30Mm)

Carrington synoptic v and cs

maps (0-30Mm)

Full-disk velocity, v(r,Θ,Φ),And sound speed, cs(r,Θ,Φ),

Maps (0-30Mm)

Internal sound speed,cs(r,Θ) (0<r<R)

Internal rotation Ω(r,Θ)(0<r<R)

Vector MagneticField Maps

Science ObjectiveData ProductProcessing

Observables

HMI Data


Solar Domain of HMI Helioseismology

rota

tion

2

3

4

5

6

7

Sun

Log

Siz

e (k

m)

Zonal flow

AR

spot

SG

dynamoP

-mod

es

Tim

e-D

ista

nce

Rin

gs

Glo

bal H

S1 2 3 4 5 6 7 8 9

min

5min

hour

day

year

cycl

e

Log Time (s)

10

polar field

Earth

HMI resolution

granule


Solar Domain of HMI Magnetic Field

2

3

4

5

6

7

Sun

Log

Siz

e (k

m)

Large-Scale

AR

spot

SG

dynamoP

-mod

es

1 2 3 4 5 6 7 8 9

min

5min

hour

day

rota

tion

year

cycl

e

Log Time (s)

10

polar field

Earth

HMI resolution

Granule

Coronal field estimates

Vector

Line-of-sight


Key Features of HMI Science Plan

• Data analysis pipeline: standard helioseismology and magnetic field analyses

• Development of new approaches to data analysis

• Targeted theoretical and numerical modeling

• Focused data analysis and science working groups

• Joint investigations with AIA and EVE

• Cooperation with other space- and ground-based projects (SOHO, Solar-B, PICARD, STEREO, RHESSI, GONG+, SOLIS, etc)


HMI Observing Scheme


Observing Scheme

• Observables

– Dopplergrams

– Magnetograms, vector and line-of-sight

– Others: Intensity, line depth, etc.

• Observables made from filtergrams described by framelists

• Filtergram properties

– Wavelength – selected by rotating waveplates (polarizer for redundancy only)

– Polarization state – selected by rotating waveplates

– Exposure time

– Camera ID

– Compression parameters, …

– Determined by subsystem settings

• E.g. motor positions

• Framelists

– List of filtergrams repeated at fixed cadence during normal operations

– Entirely specified in software – Highly flexible


Framelist Example

• Time: Time of first exposure at given wavelength since start of framelist execution

• Tuning: I1, I2, … specify the tuning position

• Doppler pol.: Polarization of image taken with Doppler camera

– L and R indicate left and right circular polarization

– Used for Doppler and line of sight field

• Vector pol.: Polarization of image taken with vector camera

– 1, 2, 3, 4: Mixed polarizations needed to make vector magnetograms

– Used for vector field reconstruction

• Note that the data from the two cameras may be combined


Observables Calculation

• Make I, Q, U, V, LCP, RCP

– Linear combinations of filtergrams

– Correct for flat field, exposure time and polarization leakage

– Correct for solar rotation and jitter (spatial interpolation)• Sun rotates by 0.3 pixels in 50s, so interpolation necessary

• Fast and accurate algorithm exists

– Correct for acceleration effects (temporal interpolation)• Nyquist criterion almost fulfilled for Doppler and LOS but is violated for vector measurements

• Significant improvement from interpolation and averaging

– Fill gaps• Data loss budget gives missing data in every filtergram, various algorithms exist

• May do nothing for vector field

• Calculate observables

– MDI-like and/or least squares for Doppler and LOS

– Fast and/or full inversion for vector field

• Many challenges remain

– Calibration, code development, lists of dataproducts etc.

– Community input needed!


HMI Data Processing and Products

HMI Data Analysis Pipeline

DopplerVelocity

HeliographicDoppler velocity

maps

Tracked TilesOf Dopplergrams

StokesI,V

Filtergrams

ContinuumBrightness

Tracked full-disk1-hour averagedContinuum maps

Brightness featuremaps

Solar limb parameters

StokesI,Q,U,V

Full-disk 10-minAveraged maps

Tracked Tiles

Line-of-sightMagnetograms

Vector MagnetogramsFast algorithm

Vector MagnetogramsInversion algorithm

Egression andIngression maps

Time-distanceCross-covariance

function

Ring diagrams

Wave phase shift maps

Wave travel times

Local wave frequency shifts

SphericalHarmonic

Time seriesTo l=1000

Mode frequenciesAnd splitting

Brightness Images

Line-of-SightMagnetic Field Maps

Coronal magneticField Extrapolations

Coronal andSolar wind models

Far-side activity index

Deep-focus v and cs

maps (0-200Mm)

High-resolution v and cs

maps (0-30Mm)

Carrington synoptic v and cs

maps (0-30Mm)

Full-disk velocity, v(r,Θ,Φ),And sound speed, cs(r,Θ,Φ),

Maps (0-30Mm)

Internal sound speed,cs(r,Θ) (0<r<R)

Internal rotation Ω(r,Θ)(0<r<R)

Vector MagneticField Maps

HMI DataData ProductProcessing

Level-0

Level-1


Joint Science Operations CenterJSOC – HMI & AIA


Joint HMI/AIA SOC

• Common aspects– Instrument commanding

– Telemetry data capture (MOC to JSOC and DDS to JSOC interfaces)

– Pipeline generation of Level-1 data

– Distribution of data to co-investigator teams and beyond

– Location of facilities

• Unique requirements– HMI Higher Level Helioseismology Data Products

– AIA Visualization and Solar Event Catalog


JSOC Scope

• The HMI/AIA Joint SOC consists of two parts:– Science Data Processing (SDP) – at Stanford and LMSAL

– Joint Operations Center (JOC) – at LMSAL

• JSOC JOC includes:

– HMI and AIA Commanding and Health Monitoring

– HMI and AIA Engineering support as needed

• JSOC SDP includes:

– HMI and AIA Telemetry Data capture (from DDS) and archive

– HMI and AIA Level-0 processing and archive

– HMI processing through to level-2 with archiving of end products

– AIA processing through level-1a with online archive at Stanford

– AIA level-2 processing at LMSAL

– Data export of the above and other HMI and AIA products as needed

• JSOC does not include tasks such as:

– Science analysis beyond level-2 products

– HMI and AIA EPO

– HMI & AIA Co-I science support


SDO Ground System Architecture

10/21/03

Telemetry & Command System

ASIST / FEDSTelemetry Monitoring

Command Management

HK Data ArchivalHK Level-0 Processing

Ground Station Control

DDS ControlAutomated Operations

Anomaly detection

Flight DynamicsSystem

Maneuver PlanningProduct Generation

R/T Attitude Determination

Sensor/Actuator Calibration

SDO Mission Operations Center

EVE SOC

Acquisition Data

Observatory Commands

Observatory HK Telemetry

Tracking Data

Integrated Trending& Plotting System

Mission Planning& Scheduling

Plan daily/periodic eventsCreate engineering planGenerate Daily Loads

HMI Science Data (55Mbps)

Ka-Band:150 Mbps

Science Data

Instrument Commands/Loads

Data DistributionSystem

(Incl. 30-Day Science Data Storage)

Ka Science Data

AIA R/T HK Telemetry/ Science Planning and FDS Products

EVE R/T HK Telemetry Science Planning and FDS Products

Universal Space Network

S-Band HK Tlm

CMD, Acquisition

Data

Station/DDS Control

Station/DDS Status

SDO Ground StationWSGT

Ka-Band:150 Mbps

Science Data

S-Band: TRK, Cmd & HK Tlm

S-Band: TRK,Cmd & HK Tlm

Alert NotificationSystem

Flight Software Maintenance Lab

Flight software loadsSimulated housekeeping telemetry

S/C Memory dumpsSimulated commands

Same Interfaces

as WSGT Ground Station

HMI AIA JSOC

Stanford Univ.

Science Data Capture

LMSAL

Instrument Monitoring& Control Instrument Commands/Loads

SDO Ground StationSTGT Flight Dynamics

FacilityOrbit DeterminationProduct Generation

Tracking Data

OD Products

Space Network(L&EO only)

S-Band: TRK,Cmd & HK Tlm

S-Band HK Tlm

Tracking Data

CMD

Acquisition DataS-Band: TRK & HK Tlm

DDS & Ground Station Control

AIA Science Data (67Mbps) EVE Science Data (7Mbps)

(Palo Alto, CA)

(Stanford, CA)

Tracking Data

Ka Science Data

Status and

Control

LASP(Boulder, CO)

Science Data CaptureInstrument Monitoring

& Control

Data Ack. & Retrans. RequestsData Ack. & Retrans. Requests

FLATSAT

Instrument Commands/LoadsHMI R/T HK Telemetry/ Science Planning and FDS Products

SDO

WSC

FSW SupportTool Suite

DDS & SDOGSIntegrated Manager

GSFC

S-Band RF &FEP system

Ka-Band RF system

(Includes 72-hr storage)

DDS FEP(Incl. 120-hr

storage)

S-Band RF &FEP system

Ka-Band RF system

(Includes 72-hr storage)

DDS FEP(Incl. 120-hr

storage)

Status and

Control

Mini MOC


HMI & AIA JSOC Architecture

Redundant

Data Capture System

Redundant Data Capture System

AIA HMI

30-DayArchive

Science TeamForecast Centers

EPOPublic

Catalog

Primary Archive

HMI & AIAOperations

House-keeping

Database

OffsiteArchiv

e

OfflineArchiv

e

JSOC Pipeline Processing System

HMI/AIA Level-0, 1, HMI-level2

DataExport& WebService

Stanford

LMSAL

High-LevelData Import

AIA Analysis System

Local Archive

QuicklookViewing

MOCDDShousekeeping

GSFCWhite Sands

World


JSOC Data Export System

DRMS

Pa

cka

ge

Format

Custom Keywords

Utilities

Selected

DataRecords

API

Dril

ldo

wn

OverviewNew/AvailStatistics

KeywordsRange

Se

arc

hB

row

se

Researcher A

General Public

Grid AdaptorGrid

VSO AdaptorVSO

CoSEC CoSEC Adaptor

Researcher B

Script Access

Space Weather

VSO – Virtual Solar ObservatoryDRMS – Data Record Mgmt Sys


JSOC SDP Development Milestones

• HMI and AIA Data EGSE installed

– Prototype for I/F testing with GS March 2005

– Version 2 to support flight inst. June 2005

• JSOC Capture System

– Purchase computers Fall 2006

– Final system installed Spring 2007

– Support DDS testing Summer 2007

• JSOC SDP Infrastructure, SUMS, DRMS, PUI

– Prototype testing of core system June 2005

– Fully functional Jan, 2006

• Purchase computers for JSOC Spring, 2007

• Infrastructure Operational Summer, 2007

• Data Product Modules Spring, 2008

• Test in I&T and with DDS,MOC as called for in SDO Ground System schedule


Summary

•HMI/SDO Will Provide Excellent New Data

•The Instrument Development is On Track

•Much Science Can Be Accomplished

•All Data are Available to Any Researcher

•The Team Very Much Wants Your Participation


Backup slides


• The AIA team will stimulate joint observing and analysis.– Coordinated observing increases the coverage of the global Sun-Earth system (e.g., STEREO, coronagraph,

wind monitors, …), provides complementary observations for the solar field (e.g., vector field, H filament data) and its atmosphere (Solar-B/EIS spectral information). And it increases interest in analysis of AIA data.

– The AIA team includes PI’s and Co-I’s from several other space and ground based instruments committed to coordination (perhaps “whole fleet months”):

• EVE and HMI needs have been carefully taken into account in setting plate scale, field of view, cadence, and channel selections, and in science themes.

Science Coordination

HVMI GBO coronagr.

SOLIS

SOLAR B EIS

SOLAR B FPP

SOLAR B XRT

AIA

Soft X-ray images for complementary T-coverage in corona

Full-Disk:Vector Field Convection

Flows (spectra) for 3-D velocities & geometry

Densities + Calibration

Vector Field small scales

H

EVECalibration

STEREO SECCHI2D 3D

GOES

CME propagationHigh Field Wind structure

Energetic Particles

RHESSIACESTEREO -WAVES

Flows (spectra) for 3-D velocities and geometry

FASRVLA

OVRO

Full-Disk Chromosphere Surface Vector Field for field extrapolation

(Non) Thermal ParticlesCoronal Field

Other

AIA Co-I’s

On SDOLegend:


The EVE Instrument on SDO


EUV Variability Experiment

• EVE is the Extreme ultraviolet Variability Experiment

• Built by the Laboratory for Atmospheric and Space Physics at the University of Colorado in Boulder, CO

• Data will include– Spectral irradiance of the Sun

• Wavelength coverage 0.1-105 nm

• Photodiodes to give activity indices

• Full spectrum every 20 s

– Information needed to drive models of the ionosphere

– Cause of this radiation

– Effects on planetary atmospheres


EVE Data & Research

• One spectrum every 20 seconds is the primary product

• Driver of real-time models of the upper atmosphere of the Earth and other planets

• Identify sources of EUV irradiance (with AIA)

• Predict the future of EUV irradiance (with HMI)

Below (left): Example spectrum from EVE. The elements emitting some of the lines and where the lines are formed in the solar atmosphere is noted at the top.

(right) Absorption of radiation as it enters the Earth’s atmosphere. Red areas are altitudes that do not absorb a wavelength, black means complete absorption. The layers of the atmosphere are also listed. All of the radiation measured by EVE is absorbed above 75 km, most above 100 km.


JSOC Data Requirements

this version modified to show the links to the hardware plan

img size channels

cadence

compress

HMI: 55,000,000 bps ** SU 553 30 16 200% 395 90

AIA: 67,000,000 bps ** SU 674 30 20 200% 482 90

HMI: 4k*4k*2 bytes/2-seconds*(pi/4) 3.4E+07 2 4 0.39 SU 530 100 52 100% 189 180

AIA: 4k*4k*2 bytes * 8 imgs per 10 seconds 3.4E+07 8 10 0.50 SU 1,080 30 32 100% 386 1,900

HMI: V,M,Ic @ 45s & B, ld, ff @ 90s*(pi/4) 3.4E+07 5.5 45 0.39 SU 130 0 0 46 0

AIA: Level 1.0 same as level-0 3.4E+07 8 10 0.50 tbd 1,080 90 95 10% 39

HMI: See below 7.5E+10 1 86400 1.00 SU 70 0 0 25 100% 25 0

AIA (lev1a): movies & extracted regions. @ 20% 6.7E+06 8 10 0.50 LM 216 0 0 77 100% 77 0

HMI: Magnetograms (M, B) 3.4E+07 5 90 0.39 na 59 100 6 0

AIA: Full Level-0 data+lev1_extract 3.5E+07 8 10 0.50 na 1,134 100 111 0

HMI: 2 * Higher Level products + 5*10 min B SU 149 60 1 0

AIA: 3* higher Level products (TRACE < 1) SU 648 60 6 0

HMI: tlm SU 553 100% 198

AIA: tlm SU 674 100% 241

HMI: Lev0, Lev-1, All Higher SU 730 412

AIA: Lev0, Lev1a SU 1,296 743

HMI Totals 68 71 610

AIA Totals 146 77 984

Combined (TB) 214 148 1,594

Tape shelf size (TB) 7,968

Tape shelf number of tapes - mixed density 11,257

Export

Near-line retain days

Tape Archive Fraction

Totals

2,026Local tape

LMSAL Link 1,193

1,227Offsite tape

Higher level 286

Level-1

Data Path Assumptions Combined (GB/day)

Fixed Disk cache (TB)

Online disk cache days

Perm disk per year (TB)

Level-01,610

Volume (GB/day)

Processed at

In from DDS

Tape per year (TB)

1,227

1,210

797

TotalsCapture System Offsite Archive SUMS Archive Transient, 10 day


JSOC Pipeline Processing System Components

Database Server

SUMSStorage Unit

Management System

DRMSData Record

Management SystemSUMS Tape Farm

SUMS Disks

Pipeline Program, “module”

Record Manage

ment

Keyword Access

Data Access

DRMS Library

Link Manage

ment

Utility LibrariesJSOC Science

Libraries

Record Cache

PUIPipeline User

Interface

Pipeline processing

plan

Processing script, “mapfile”

List of pipeline modules with needed datasets for input, output

Pipeline Operato

r

Processing History Log


Illustration of solar dynamo


Calibration Status as of Feb. 12, 2006

• White – Not yet finished

– Taken: Data taken but not yet analyzed

– ?????: May not be doable with current configuration (eg. high camera dark current)

• Green – Test done, all is OK

• Yellow – Minor problems

– Incomplete or buggy analysis software.

– Fixable test setup problem or apparent test glitch (eg. clouds)

– Problem is understood and is easy to correct

– Problem is understood and can’t be fixed, but does not impact full science objectives

• Red – Instrument problem potentially impacting science objectives, but

– Not yet fully understood

– Has known likely solution with modest modest schedule and cost impacts

• Black – Fatal problem found

– Problem understood and science objectives can’t be met

– Solution is unknown or has severe cost or schedule impacts

• Surgeon General’s warning: Preliminary results may cause severe upsets!


Image Quality

• Distortion– Procedure works, but problems with stimulus telescope illumination. Difficult to do with Sun.

• Image scale– All OK. 0.5025”/pixel

• MTF– Astigmatism seen, but problems with stimulus telescope illumination

– Sun data not yet analyzed

• Focus and field curvature– Right on for lamp. Bad seeing during Sun test

– Field curvature analysis not complete

• Ghost images and scattered light– Difficult to do with high camera noise. May have to be deferred to vacuum test

• Contamination– Still needs to be done

• Image motions– Saw problems with test setup. Probably has been solved

– Some displacements seen with focus blocks


Special target continued


Observables and Miscellaneous

• Observables

– Still to be done. May wait for some instrument upgrades

• Thermal effects

– Probably not doable in air

• Alignment legs

– Range and step size determined. Meets spec.

– Repeatability. Looks adequate, but more tests planned


Status - Mechanisms


Conclusion

• Tests progressing– Some tests done

– Some not

• Some problems found– Some fixed

– Some still need work

– No showstoppers!

• Lots of data to analyze– Over 10000 images so far

– Need people

• Stay tuned!

• Ask not what HMI can do for you!

• Ask what you can do for HMI!


CCD and Camera

• Flat Field

– Details still to be worked out

• Linearity and gain

– Still to be done.

– Difficult due to thermal noise and camera drifts

– Drifts believed due to known problem with this particular camera

• Quadrant crosstalk

– Probably has to await vacuum test due to high thermal noise in air


Filter transmission

• Wavelength and spatial dependence

– Phase maps have been made with laser and Sun

– Test equipment problems for wavelength dependence. Believed fixable.

– Elements will be replaced (decided before this test)

• Angular (as seen from detector) dependence

– Still to be done

• Stability

– Will try, but oven stability in air likely insufficient

• Throughput

– Looks good

– But gain drifts make things difficult


Phase Maps


Polarization

• Some data taken, but much analysis still to be done

• Significant problem found. – Linear polarization into instrument gives circular polarization of up to +/- 0.4!


Schedule Summary (As of February)

• Complete initial testing Feb 06

• Complete instrument integration April 06– Except flight camera electronics box

• Pre-Environmental Review April 06

• Instrument calibration April – July 06– In air April – May 06

• Need brassboard camera interface board

• Use demonstration camera electronics box

– In vacuum June – July 06• Mid-stream install flight camera electronics box

• HOP vibration & acoustic test July 06

• Comprehensive performance test Aug 06– With flight HMI electronics box

• Instrument EMI/EMC test Sept 06

• HMI electronics box vibration test Oct 06

• Thermal vacuum cycling and balance test Nov – Dec 06

• Comprehensive performance test Dec 06

• Alignment with instrument module panel Jan 07

• Pre-Ship Review Jan 07

• Ship to Goddard Feb 07


Ray trace – Obsmode and Calmode


Calibration Matrix

123456789

10

11

121314

151617181920212223

24

2526

2728

29

30

31

3233343536373839

A B C F GTest Group Property Sun

TestsLight Source

1 Image quality Distortion Yes Lamp2 Image scale Yes Sun

3a MTF Yes Lamp3b MTF Yes Sun4a Focus Yes Lamp4b Field curvature Yes Lamp4c Focus Yes Sun4d Field curvature Yes Sun

5 Relative alignment of cameras

No Lamp

6 Relative focus of cameras

No Lamp

*7 Ghost images No TBD*8 Scattered light No TBD9 CCD and Camera Noise No Dark

10 CCD and Camera Flat field Yes Lamp+Sun11 Linearity Yes Lamp

*12a Quadrant crosstalk No TBD*12b Quadrant crosstalk No TBD13a Contamination Yes Lamp13b Contamination Yes Sun13c Contamination No Laser14 Image motions Offset and distortion Yes Lamp15 Filter transmission Wavelength and

spatial dependenceYes All

16 Angular dependence Yes Laser + Sun

17 Stability No Laser or Sun18 Turn-on transients No Laser or Sun?

19 Throughput Yes Sun20 Contrast Yes Laser + Sun

21a Polarization All sorts of stuff Yes Lamp

21b Polarization All sorts of stuff Yes Sun

22 Observables performance

Doppler Yes Sun

23 Line of sight Yes Sun24 Vector Yes Sun

*25 Thermal effects Pointing No Lamp*26 Focus (Yes) Lamp+Sun27 ISS Range and stability No Lamp28 Alignment legs Range and step size Yes Lamp29 Repeatability Yes Lamp


Test Setup – Stimulus telescope with white light lamp

Stim tel w/ lamp

SpacecraftSimulator

HEB

Inside cleanroom

Outside cleanroom

HOP

PC

U

Line of Sight

Work area

Ent

ran

ce to

cle

anr

oom

Entrance to gowning area

page 1cospar2006-a-01469 hmi hmi helioseismic and magnetic imager for the solar dynamics observatory...

Documents

hmi hmi helioseismic

magnetic fields

solar surface

science of sdo slide

hmi sdo science requirements

magnetic imager

magnetic reconnection

magnetic activity cycle