Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed.
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Observatory - Overview July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed
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Transcript of Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed.
Observatory - Overview
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review1
Single ObservatoryStowed
MMS Observatory w/SA Removed
Mission Overview
July 13 & 14, 2010 2
MMS I&T Pre-CDR Peer Review
MMS I&T Pre-CDR Peer Review July 13 & 14, 2010 3
SMART IS Components
Mission Overview
DIS
DIS
DIS
DISDES
DES
DES
DES
ASPOC
ASPOC
FEEPS
EDI
EDI
SDP
SDP
SDP
SDP
HPCA
EIS
IS safe/arm panel
1
2
34
5
6
78
+X
-X
-Y
+Y
ADP
DSS
DSS
FEEPS
Mag boomSCM & AFG Mag boom
DFG
SMART Components• ADP - Axial Double Probe• AFG - Analog Flux Gate
Magnetometer (mounted on boom)
• ASPOC - Active Spacecraft Potential Control
• CEB - Central Electronics Box (Fields)
• CIDP - Central Instrument Data Processor
• DES - Dual Electron Spectrometer
• DFG - Digital Flux Gate Magnetometer (mounted on boom)
• DIS - Dual Ion Spectrometer• EDI/GDU - Electron Drift
Instrument/ GunDetector Unit• EIS - Energetic Ion
Spectrometer• FEEPS - Fly’s Eye Energetic
Particle Sensors• HPCA - Hot Plasma
Composition Analyzer• IDPU - Instrument Data
Processing Unit (FPI)• SCM - Search-Coil
Magnetometer (mounted onboom)
• SDP - Spin-Plane Double Probe
CIDP, IDPU, and CEB are mounted under the IS deck
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 4
Clampband Locations
Active Ring Simulator - Future Work
Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design
Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design
Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design
Launch Vehicle Separation System Atlas D1666 - 1666mm clampband, shear pin design - Also supplied by RUAG
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 5
Observatory - Dimensions
+X-X
+Y
-Y
(3150 mm)[124.0”]
(3478 mm)[136.9”]
(3680 mm) [144.9”]
(3690 mm)[145.3”]
(3033 mm)[119.4”]
+Y
-Y
+X-X
maximum dimension = 3690 mm [145.3”] [12’ 1.3”]
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 6
Observatory - Dimensions
Active
SOLAR ARRAY PANEL (.850 m2)
Passive
Sep Plane
Sep Plane
(1230 mm)[48.4”]
(680 mm)[26.7”]
(66 mm)[2.6”]
(110 mm)[4.3”]
(1250 mm)[49.2”]
(133 mm) [5.2”]
(930 mm)[36.6”]
(1666 mm) [65.6”]
(1054 mm)[41.5”]
Thrust Tube
+X-X
+Z
-Z
ORIGIN
(216 mm)[8.5”]
(167mm) [6.6”]
(490 mm)[19.3”]
(526 mm)[20.7”]
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 7
Launch Configuration
4 Meter Fairing
#1
#2
#3
#4
4916 mm[193.5”]
5936 mm[233.7”]
LV I/F
Four observatories will be stacked on top of each otherwill be clocked 180° from each otherseparation system details in covered in the Mechanical PDR
Instrument Suite Harness• IS harness is the responsibility of SwRI• SwRI is using the GSFC Pro-E model for
harness routing and transfer of harness tie-down locations– as harness segments are fabricated, the
mass of each segment will be added to the model
• Spacecraft is providing production break connector brackets where IS harness joins SC harness– brackets are attached to the thrust tube
• Harness between IS deck and SC deck is routed along the thrust tube and is attached via threaded inserts in the thrust tube ribs
• Some IS harness is routed across SC deck (FEEPS, magnetometers)– these areas are shown on the deck MICD
• Harness tie downs on the IS deck are bolted to the deck in post cured inserts and with bonded TC105s
• Purge lines are also routed using the same model
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review8
CEB
CIDP
IDPU
AEB
DIS#4
DIS #3
DIS#2
DIS #1
DES#2
DES #3
DES#4
DES #1
ASPOC #1
ASPOC #2
FEEPS
EDI #2
EDI #1
SDP #4
SDP #2
SDP #1
SDP #2
HPCA
EIS
IS safe/arm panel
+X-X
+Y
-Y
purge manifold
S-BandAntenna
1
87
6
5
43
2Test/thermal pwrdistribution panel
vent
Instrument Deck Components
July 13 & 14, 2010 MMS I&T Pre-CDR Peer Review 9
Instrument Deck Components• ADP - Axial Double Probe• AEB - Axial Electronics Box• ASPOC - Active Spacecraft Potential Control• CEB - Central Electronics Box (Fields)• CIDP - Central Instrument Data Processor• DES - Dual Electron Spectrometer• DIS - Dual Ion Spectrometer• EDI/GDU - Electron Drift Instrument/ Gun
Detector Unit• EIS - Energetic Ion Spectrometer• FEEPS - Fly’s Eye Energetic Particle Sensors• HPCA - Hot Plasma Composition Analyzer• IDPU - Instrument Data Processing Unit (FPI)• SDP - Spin-Plane Double Probe
- 19 IS instruments - SC vent- 4 IS electronics boxes - S-band antenna- IS safe/arm panel - 6 thrusters- IS purge manifold- IS test/thermal pwr distribution panel`(blue = SC components mounted on instrument deck)
thrusterthruster
thrusterthruster
MMS I&T Pre-CDR Peer Review July 13 & 14, 2010 10
Remaining Integration
install solar arrays &magnetometer booms
install ADP receivingelement & orbital debrisshields
GPS Hat Coupler
1
2
3
4
5
6
7
8
S-band Hat Coupler (+Z direction)
DES Sensor Head
SCM and AFG (mounted on mag boom not shown)
DES Sensor Head
GPS Hat Coupler
DES Sensor Head
DSS Stimulator
DSS Stimulator
DES Sensor Head
GPS Hat Coupler GPS Hat Coupler
GPS Hat Coupler
GPS Hat Coupler
GPS Hat Coupler GPS Hat Coupler
S-band Hat Coupler (-Z direction)
DFG (mounted on mag boom not shown)
Star Sensors (really on underside of spacecraft deck)
EIS
HPCA
Total of 24 Add-On Stimulus GSE for Thermal Tests
Adding 1 foot clearance for TVAC GSE. The current minimum width needed with TVAC GSE attached = 157.5” or 13.1 feet
145.5” or 12.1’
FEEPS
FEEPS (mounted on spacecraft deck)
Stimulus and GSE Locations
July 13 & 14, 2010 11
MMS I&T Pre-CDR Peer Review
