Gaia
GAIA.ASU.SP.ESM.00007
Issue 2.00
Page 8 of 79
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GAIA.ASU.SP.ESM.00007 (Avionics SCOE Req Iss 2).doc
EGSE
REAL-TIME
NETWORK
CN1002
Avionics SCOE
CDMU
Power/Pyro
SCOE
PDHU
PCDU
STR1
STR2
Spacecraft
Interface
Bracket
X401A
Battery Power Prime
X401B
TM/TC
BYPASS
Central Checkout
System (CCS)
Controller
FPA
Simulator
P401
Avionics
Model Test
Bench
(AVM)
VPU
CDU
CPS nom
MPE nom
LGA-2
LGA-1
STR1
STR2
GYR O 1
BATTERY
CDU
SCOE
PDHU
SCOE
Optical
Stim SCOE
FPA
PLM 1553
EGSE
LAN
Payload Module (PLM)Service Module (SVM)
TTL
TRIG
109
Solar
Array
Simulator
Majority Voter
Test Interface
TMTC
SCOE
Star Tracker
SCOE #1
Real-Time
Simulator
CDMU
Sim
ERC32
Emulation
CSW
SpaceWire x2
(A/B)
Discrete
Data I/O
2x
MIL-STD-
1553B (A/B)
EIU nom
uPropul sion nom
SREM
SpW
OSE
MDE
107
Pyro/NED
Simulator
Umbilical
Rack
X402A
X807
TM/TC from TTC SCOE
DR0107
DR0101
DR0102
DR0109
DR0103
DR0104
DR0105
DR0106
DR0401 A
DR0402
DR0603
DR0604
DR0607
DR0609
DR0701
DR0702
DR0801
DR0802
DR1107
DR1101
DR1102
DR1109
DR1103
DR1104
DR1105
DR1106
DR1701
DR1702
DR1801
DR1802
Test Cap
Power
Simulation
EGSE Supplier
Furnished Cables
Astrium
Furnished Cables
Battery
Simulator
Battery Charge
Power Supply
DR0113
X113
Battery Charge
Interface
BAT TERY
Star Tracker
SCOE #2
DR0110
DR0111
DR0112
Battery Power Redundant
Battery Signals (Prim e/Redundant/AIV)
108DR0108 DR1108
X110
X111
X112
Pyro Signals Prim e
Pyro Signals Redundant
MV Tes t Interface
SAS FSA Prime
SAS FSA Redundant
SAS DSA P rime
SAS DSA Redundant
Umbilical #1
Umbilical #2
103
104
105
106
101
102
X107
X108
X109
X103
X104
X105
X106
X101
X102
X601
X603
X604
X607
X620
X622
X624
X627
X609
603
604
607
609
624
627
701
702
801
802
EGSE Configuration for GAIA
Issue: 6
Date: 29th November 2006
X602
LCL Sim#1
LCL Sim#2
DR0605
X605
605
DR0606
X606
606
DR0608
X608
608
CDMU ( SHP, ALARMS, PP S)
EIU (SHP)
CPS (LV/F CV/PT/Status)
MPS (LV/F CV/PT/Status)
TTC
SCOE
DR0803 DR1803803
D
R
0
8
0
4
-
D
R
0
8
2
7
X801
X802
X803
X804-X827
LGA-2 Test
LGA-1 Test
PAA-Reference
PAA-Test Port I nputs (24x)
X701
X702
EIU Discrete I/O
610DR0610
EIU (FSS)
X625
625
X626
626
DR0620
DR0625
DR0624
DR0626
DR0622
DR0627
SVM 1553
Transponder #1
Transponder #2
PAA
PacketWire
SpW
SpW
DR1604
DR1607
DR1609
DR1605
DR1608
DR1625
DR1627
DR1624
DR1626
CDMU/EIU
CDM U/PDHS
SVM P rime
SVM Redundant
PLM Prim e
PLM Redundan t
IRIG RX
IRIG-B Time
Code S ignal
803 -
827
D
R
1
8
0
4
-
D
R
1
8
2
7
Central
Archive
Disc
PacketWire x4
(A/B)
Timing &
Synch
X628
PPS (EGSE 1H z)
Datation
GYR O 3
MPE red
uPropulsion red
EIU red
CPS red
FSS 1
FSS 2
FSS 3
EIU (Gyro)
DR1606
X610 SRE M Simulation
T T
T
T
BC
BC
RT
RT
RT
RT
RT
RT
RT
RT
RT
RT
RT
RT RT
RT
RT
RT
CLOCKS
Test Cap
Test Cap
PYRO
DR1610
GYR O 1 RT
DR0601
DR0602
DR1603
Figure 1.4-1: Gaia EGSE Configuration
1.4.2 Spacecraft PFM AIT
During the Spacecraft PFM AIT test campaign, the RTS is used to Model the Spacecraft Mission
Environment and Dynamics and the AOCS Actuators and Sensors (which remain simulated throughout). In
addition, any missing Spacecraft units may be modelled. Using direct electronic stimulation and
measurement provided by the Avionics SCOE and other EGSE, it allows closed-loop testing of the
Spacecraft Avionics.
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