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STEREO - Solar Terrestrial Relations Observatory Mission
STEREO
STEREO Science Team Meeting
May 2, 2005Presented by
Edward ReynoldsAPL STEREO Project Manager
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STEREO
General Status
• Observatory Integration status– Core spacecraft integration is nearly complete– Both spacecraft are ready for instrument integration
• Mission Operations Center– Facility complete and equipment operational– MOC facility used for Mission Simulations and DSN tests– POC facility ready for instrument teams
• Four Mission Simulations performed on each spacecraft• Five Dress rehearsals performed using equipment and
personnel being planned.
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STEREO
Spacecraft Stacking Operations
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STEREO
Spacecraft Stack – Dynamics Load Testing
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STEREO
Integration Status
• Spacecraft integration at APL – Both spacecraft integrated within the same room– Facility controlled for contamination, ESD, and security– Spacecraft to remain at APL until after stacked vibration testing
• Most environmental testing to occur at GSFC– Acoustics, thermal vacuum, shock, ESD, mass properties
• Launch activities will occur over a 11-week period– While at GSFC and Launch site, spacecraft will be controlled from
MOC at APL– Project will follow security procedures of KSC/CCAFS– Background checks need to be submitted in a timely manner– Visitors and guests will be escorted when required– Once spacecraft is fueled, access around it will be limited to
essential personnel
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STEREO
STEREO I&T Flow
12/1/2004 1/1/2005 2/1/2005 3/1/2005 4/1/2005 5/1/2005 6/1/2005 7/1/2005
CTTHarness insp.
PDU Int.IEM, Power System,
RF System, AutonomyIEM, G&C,IDPU, SIM1
HGA, battery, CPT,blankets, Sim2, align
1/1/2005 2/1/2005 3/1/2005 4/1/2005 5/1/2005 6/1/2005 7/1/2005 8/1/2005
CTTInstrument integration, thermal closeout,
phasing, alignments, SIM2Harness install,
Hi-PotPDU, EM IEM,
Power Sys, RF SysG&C, Autonomy, SIM1
Buses CompleteSpacecraft A Integration - APL
Spacecraft B Integration - APL
9/1/2005 10/1/2005 11/1/2005 12/1/2005
Vib, Shock,Align
Spin, Mass Props
EMC Testing
Thermal Vacuum Balance& Cycling (SIM3, CPT)
APL GSFC GSFC: SES ChamberCPT,Align.
Pack & Ship
1/1/2006 2/1/2006
Unpack& Setup
Alignment, CPT,& DSN
SIM4, Pyro,Lens C/O
Leak, Load Prop, Spin& Battery Condition
Canning, Transport,& Pad Operations
Astrotech or AE
Transport
CCAFS: Pad 17
Launch Site Ops: KSC
Environmental Testing
Instrument integration, thermal closeout,phasing, alignments, SIM2
BOOM
Note: The instrument dates denote their arrival at Receiving at APL and not the date of their installation onto a spacecraft
Rev: April 27, 2005
CPT
CPT
CTT
IDPU
Env.Prep
Env.Prep
Acoustic, ShockFunctional
Ship to GSFC
SWAV
SEP
SEP
PLAS
PLAS
HI
HI-B
SEB, SCIP
SCIP, SEBBOOM, IDPU
SWAV
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STEREO
STEREORecent Accomplishments
- Hi-Shear under contract for Pyro Sep-Nuts (replaces STARSYS QwkNuts)- DSN/CTT Testing Completed on Spacecraft A & B
- Performance and Operations
- Power, RF, G&C subsystems integrated on Spacecraft A & B- Propulsion system integrated and leak tested on Spacecraft A & B- IEM B cold lock-up root cause identified and mitigated,
- IEM B integrated on Spacecraft
- Mission Sim #1 on both Spacecraft A & B- Launch, Separation, Detumble, 1st contact, delta-V and momentum dumps, EA mode
- IMPACT IDPU & Boom Integrated on Spacecraft A- Command Loss Timer Test (72-hour) Spacecraft A- 85% of thermal blanketing complete- Flight batteries ready for integration- Solar arrays delivered and undergoing flash illumination testing- HGA assemblies completing TV chamber testing (deployments, actuations)
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STEREO
Photo Gallery
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STEREO
Educational Video Production
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STEREO
Mission Orbit
SunSun
Earth
Ahead @ +22/year
Behind @ -22/year
Heliocentric Inertial Coordinates(Ecliptic Plane Projection)
Ahead
Behind
Earth
1 yr.
2 yr.
3 yr.
4 yr.
1yr.
2yr.
3 yr.4 yr.
5 yr.
5 yr.
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STEREO
Phasing Orbit
Mission TimelineLaunch: Feb. 11 – 24, 2006 ~4:00 am EST
S1: April 8, 2006S2: May 16, 2006
Lunar Orbit
+22°/yr Ahead
-22°/yr Behind
• 4.5 Revolutions in Phasing Orbit• First lunar swingby, S1
– Behind escapes– Ahead spacecraft enters 1 month ‘outer loop’
• Second lunar swingby, S2– Ahead escapes
To Sun A1
A2A3
A4 A5S1
S2
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STEREO
Day 1 (11-Feb) Phasing Orbit Schematic
A17.2 / 77
A574.3 / 137
TIP42 min / h=178 km
C3 = -1.6 km2/s2 P114.5 / 1.32
P229.1 / 1.58
P340.4 / 1.80
P452.0 / 2.21
S294.5
S155.8
Behind
Ahead
KeyEvent ID
Elapsed Time (days)/Distance (Re)
A221.8 / 77
A334.7 / 65
A446.7 / 65
= Planned V
= TCM V
SummaryMin. Perigee Altitude = 2,036 km @ P1Lunar Flyby Radius: S1: Ahead = 12,361 km, Behind = 8,105 kmS2: Ahead = 16,214 km
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STEREO
Spacecraft Mission Operations Mission Operations Center Facility
MOC Space
CommandPit
HIL AHIL B
BPrimaryBackup
APrimaryBackup
AssessmentWorkstations
EngineeringDisplay
Workstations
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STEREO
Spacecraft Mission Operations Mission Operations Center Facility – At APL
POC Space
