SDO Project Status AIAHMI Science Team Meeting

1
SDO Project Status AIA/HMI Science Team Meeting

• Elizabeth Citrin
• SDO Project Manager
• February 13, 2006

2
Mission/Project Overview

• Mission development management at GSFC
• S/C build Observatory integration will be
  performed in-house at GSFC
• GSFC responsible for ground system
  development/management Mission Operations
• Instrument contracts managed by GSFC Principal
  Investigators responsible for development of
  their Instrument Science Operations Centers.
• August 2008 Atlas V launch from KSC into
  GEO-Transfer Orbit (GTO), circularize to GEO-Sync
  Orbit, inclined 28.5 degrees with semiannual
  eclipse seasons
• Spacecraft robust/redundant, 3-axis stabilized,
  solar-tracking with low jitter, continuous high
  rate data (130 Mbps), 5 year life
• Single ground station with distributed Science
  Operation Centers.

3
SDO Project Organization
SDO PROJECT
PROJECT SCIENTIST DEAN PESNELL
GSFC
PM E. Citrin DPM - R. Lilly DPMR T. Miller
GSFC
Mission Assurance Lead B. Calvo
Mission Systems Engineering Lead J. Ruffa
Launch Services

Ground System
Observatory
INSTRUMENTS
MIM R. Mueller
Mgr. R. Pages Dep. Mgr. C. Weikel

Mgr. B. Robertson Dep. Mgr. W. Potter

KSC
GSFC
GSFC
ILS Prog. Dir/SDO J. Casani LMA Prog. Mgr./SDO
A. Brandts
AIA
EVE
HMI
PI A. Title PM L. Springer DPM G. Kushner
PI T. Woods PM M. Anfinson
PI P. Scherrer PM R. Bush
SU
LMSAL
CO-LASP
PM L. Springer DPM B. Fischer
PI L. Golub PM J. Bookbinder
PI D. Judge PM A. Jones
PI G. Berthiaume
SAO
LMSAL
USC
MIT-LL
4
SDO Project Summary Schedule
CY 2002
CY 2001
CY 2000
CY 2003
CY 2004
CY 2005
CY 2006
CY 2007
CY 2008
99
Q1
Q2
Q3
Q4
Q1
Q2
Q3
Q4
Q1
Q2
Q3
Q4
Q4
Start Implementation
7/04
(5 Yrs B/L EPM 8/13)
PCA MILESTONES
8/08
LRR
Formulation
Pre-Form
Ops
Implementation
Phase C/D
Phase A
Phase B
4/05
9/03
8/08
3/04
4/03
6/04
5/08
8/07
MISSION MILESTONES
LAUNCH
SRR/ SCR
ICR
PDR
CR
CDR
PSR
PER
AO Rel
Inst. Selections
INSTRUMENT DEVELOPMENT
1/02
8/02
3/07
Ship
AIA - LMSAL
PER
Procure
Build/Test
Concepts/Design/Long Lead
2 mo.s
CDR
AO Process
9/02
Ship
2/07
Award Contracts
Procure
HMI - SU
PER
Concepts/Design/Long Lead
Build/Test
2 mo.s
CDR
2/07
Ship
EVE - LASP
PER
Procure
Build/Test
Concepts/Design/Long Lead
2 mo.s
CDR
Instrument Integration
SPACECRAFT DEVELOPMENT INTEGRATION
In-House ATP
5/06
3/07
Procure
S/C Int.
S/C Bus Studies
1 mo
3/08
Build Comp.s
7/07
Concepts/Design/Long Lead
Obs Test
OBSERVATORY TEST
(8 mo.s)
2.25 mo.s
5/05
5/08
GS CDR
GS MOR
FOR (System Freeze)
GS TRR
6/07
GROUND SYSTEMS DEVELOPMENT
4/06
Procure
Ship
Procure/Develop/Test
Concepts/Design
5/08
L.V. Selection
LAUNCH VEHICLE DEVELOPMENT _at_ KSC
LV Development/Integration
(36 mo.s)
Launch
2 wks
Code M ATP Issue RFO
L-30 month funding profile
8/08
2/06
As of January, 2006
Reserve (S/C 3.75 months, GS 2 months)
Original Date
Legend
Progress Bar
Original Date
SUStanford University
LMSAL Lockheed Martin Solar Astrophysics
Laboratory
LASP Laboratory For Atmospheric and Space Physics
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Status

• All activities are proceeding very well
• Mission issues/risks are typically schedule and
  funding related, not technical
• One exception the late-discovery of High Gain
  Antenna seasonal blockage occurrences during
  normal mission observing
• An incorrectly used parameter in our STK attitude
  analysis tool had the observatory pointing earth
  north instead of solar north
• Many options were explored to resolve this
  satisfactorily
• Selected solution involves adding hardware to
  radiate out of both high gain antennas at the
  same time, and avoid blockage by slowly slewing
  the non-blocked antenna into position while
  slewing the other antenna away
• Use of polarization settings on ground and flight
  antennas will minimize interference and data loss
• Schedule and cost reserves are adequate
• Still recovering from funding rescission of FY05,
  so this year is tight
• But, no further funding hits are expected this
  year, and
• Presidents FY07 budget looks good for SDO

6
SDO Observatory On orbit configuration
Instrument module (IM) designed to place
instrument radiators outboard and on North/South
faces in order to have clear field of view
AIA (which uses GT signals for IMC) all on one
face, HMI, EVE (which do not) on the other
AIA
Instrument module constructed from composite
material to minimize thermal distortion, mounted
to spacecraft using kinematic mounts
EVE
Spacecraft structure, showing two short arrays
(tapered to meet HGA field of view reqs), cell
side out in deployed position
HMI
Spacecraft bus module (contains spacecraft
Instrument electronics boxes)
Internal propulsion module, allows for parallel
integration and test flow early
Orbit injection engine (exit nozzle shown) and
ACS control thrusters located opposite end from
instruments

• Approximate characteristics
• Mass 3200 kg
• Width 2.25 m
• Height 5.25 m

Redundant High Gain Antennae (HGA) (only one
visible) at the end of rigid booms (must be rigid
due to required waveguides). HGA field of view
allows each antenna to be used continuously for
6 months/year (scheduled antenna handovers
twice/year)
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SDO Structure Overview
Three Primary Modules Instrument Module,
Spacecraft Bus, Propulsion Module
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SB Fabrication/Assembly Status
Flt SVU SB assemblies are completed IRU and RW
brackets are in fabrication
.
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PM Fabrication/Assembly Status

Both PM primary structures are completed Secondary
structure are in fabrication
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IM Fabrication/Assembly Status

AIA inserts bonding is completed HMI/EVE inserts
bonding is in process
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EVE
ESP
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AIA
13
HMI
HMI Flight Structure
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Atlas V