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November 26 , 2007
GMES Sentinel-1Industry Day for EC FP7 CountriesProgrammatics
All rights reserved © 2007, Thales Alenia Space
Corporate Communications
Objective of the Sentinel-1 Industry Day for EC-FP7 countries is to provide adescription of :
Sentinel-1 Program Procurement approach Satellite Subsystems ITTs to be issued from now on on EMITS open to FP7 countries Current ITT release plan Q&A
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Corporate Communications
Sentinel-1 Industrial Roles
Prime Contractor Thales Alenia Space Italia (TAS-I) Spacecraft Thales Alenia Space Italia
SAR Instrument Astrium GmbH (ASD) SAR Antenna Astrium GmbH
SAR Electronics Astrium Ltd (ASU)
Additional Core Team partners
The Sentinel 1 Core Team will select its subcontractors largely through open competitiveprocurement under ESA control in accordance with “Best Practices”.
http://esamultimedia.esa.int/docs/industry/BestPractices/Best_Practices_August_2006.pdf
As the GMES Space Component Programme is a joint programme with the EuropeanCommission, competition enlarged to the participating countries to the 7th Framework Programme
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Corporate Communications
Sentinel-1 Mission Objectives
The Sentinel-1 mission provides continuity of C-band radarobservations and satisfies the requirements of itsoperational users in terms of data availability, coverage &revisit, timeliness and the quality of its data products.
The Sentinel-1 provides radar data products in support ofthe GMES Services.
Launch of Sentinel-1A: second half 2011
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Sentinel-1 Data Products for Marine Services
Sea ice monitoringIceberg detectionShip detectionFisheries monitoringOil spill detectionOcean wavesSea surface windsOcean front featuresOcean currents
ASAR image of mobile sea ice aroundWard Hunt Island
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Corporate Communications
Fast Track Data Products: Land Monitoring
Land cover classification ofagricultural fields in Flevoland(NL) using ERS interferometry
Land surface subsidencemonitoring in Carbonile, Tuscany(It) using ASAR interferometryRefined risk-zone limits
Red: previous risk area Pink: revised risk area
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Corporate Communications
SENTINEL-1 Satellite Flying Attitude
Nominal Right Looking Flying Attitude
C-SAR Antenna
S/C Velocityentering into the
plane
STT
SBA
SBA
RCT(orb.contr.)
SAS
SAW
PDHTAntenna
SAW
RCT(attit. control)
GPSAntenna
s
29.45°
Nadir
AAS-I
5. Spacecraft (S/C) Concept
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SENTINEL-1 Satellite Configuration
Satellite -Y, +X sides Satellite +Y, -X sides
Stowed Satellite Views
Satellite -Z side
Standard 1194 mm clampband I/F GNSS Antenna
SAS
RCT(PRP Module)
5. Spacecraft (S/C) Concept
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Corporate Communications
SENTINEL-1 Configuration
Deployed Satellite Isometric Views
Satellite +Y side (anti-Sun) Satellite -Y side (Sun side)
C-SAR Antenna
SAW
STT
PDHT Antenna
S-Bant Ant.RCT
S-Bant Ant.
SVM
PLM
SAW
5. Spacecraft (S/C) Concept
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Corporate Communications
SENTINEL-1 Configuration
S-1 –X, +Y, +X panels lay-out(+X panel rotated 90°)
S-1 Central StructureLayout
Satellite Internal Layout
S-1 PropulsionModule
DCU
PropellantTank
5. Spacecraft (S/C) Concept
All rights reserved © 2007, Thales Alenia Space
Corporate Communications
Avionics S/S General Architecture
TTRM
M
TTRM
R
PM
M
PM
R
SMM
M
SMM
R
SL-HK
M
SL-HK
R
X-STRAP
DC/DC
CV
R
DC/DC
CV
M
HPC
HPTM
GNSS
PPS
RM
PPS
SYSTEM
ALARMS
TT&C
S/SS-BAND
HPC
HPTM
GNSS
PPS
RM
PPS
THERMAL
S/SEPS
SMU1553B BUS
SUN
SENSOR
MAGNETO-
METERMAGNETIC-
TORQUERS
GYRO
M
STAR
TRACKER
M
AVIONICS S/S
PROPULSION
S/S
P/L
SPWIRE
SPWIRE
REACTION
WHEELS
GNSS
RX
MX-STRAP
PCU
PWR
GEN
SADM-1
SADM-2
EPS
PW-AL
PDHT
S/S
X-BAND
C-SAR
P/L
RM
PPS
PPDU
CAPS
FIRE P/L
OptionRM
PPS
RM
PPS
ACE
M
ACE
R
X-STRAP
SM SUN
SENSOR
COARSE
GYRO
SPWIRE
SPWIREI/O & DC/DC conv. Module
Main
I/O & DC/DC conv. ModuleRedoundant
1553B BUS
5. Spacecraft (S/C) Concept
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Mono-propellant hydrazinesystem
Provides propellant/pressurantstorage capability
Operates in blow-down mode Provides impulse and steady
state thrust for:■ Drag compensation■ Orbit modification and
correction■ De-orbiting manoeuvres
Unit pictures for ref.only
Propulsion Subsystem
•
•T
FVV•
FDV•
PT•
•LF•
LT•
mechanical joint
RCT14 RCT8 •…• RCT7• RCT1• •…•
LV1
LV21•
5. Spacecraft (S/C) Concept
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CAPS
ToPayload
SOLAR ARRAY WING
SADA 1 SADA 2
To Bus Units
To Heaters To Pyro Devices
To TM/TC I/FsPCU
Battery Modules
Performing the following functions:
Electrical power generation & storageConditioning/protection/distribution
SADA may be replaced by twist capsulesystem
Unit pictures for ref.only
Power Subsystem Architecture
PPDU
5. Spacecraft (S/C) Concept
SOLAR ARRAY WING
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Performs two-way transfer of information betweenthe satellite and the ground
Up-link command data Down-link telemetry data
Filters may be introduced following RFC analyses
Telemetry & Telecommand (TT&C)
5. Spacecraft (S/C) Concept
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Corporate Communications
PDHT Configuration A5. Spacecraft (S/C) Concept
Payload Data Handling & Transmission PDHT
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PDHT Configuration A PDHT Configuration B
Payload Data Handling & Transmission PDHT
5. Spacecraft (S/C) Concept
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Corporate Communications
The C-band SyntheticAperture Radar iscomposed by :
■ The SAR ElectronicsSubsystem (SES) isallocated on the internalpanels of the payloadmodule, and provides allradar control, signalgeneration and receivedata handling functions(including datacompression andformatting).
■ The SAR AntennaSubsystem (SAS) is anactive phased arrayantenna capable of fastscanning in bothelevation and azimuth
SAR Instrument Overview
5. Spacecraft (S/C) Concept
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Corporate Communications
Components pictures for ref. only
SENTINEL-1 Harness Subsystem provides the electricalinterconnections necessary to allow the distribution ofpower and signals. It is composed of the following maincomponents:
DC Harness Unit & Heater power supply TM / TC signals distribution (thermistors acquisition,
status telemetries, discrete commands, serial digital,broadcast pulses, etc.)
RF Harness Waveguides, coaxial cables and RF miscellaneous
Pyro / NEA / Thermal Knife Harness For deployment activation of SAR antenna, Solar
Panels, other possible appendages1553 Data BUS Harness
For data exchange between Bus Controller (BC)resident in SMU and Remote Terminals (RT)
Launch Vehicle Umbilical Connector Harness For on-ground Spacecraft to launch vehicle
interconnection
Harness
5. Spacecraft (S/C) Concept
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Corporate Communications
Sentinel-1 S/C Development Phases
7. PROGRAM PHASES
AAS-I
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Corporate Communications
Contact Points at Industry
11. Contact Points at Industry TAS-I [Thales Alenia Space – Italia] Via Saccomuro 24, 00131 Rome (Italy)
• Claudio Bruno tel. + 39 06 4151 2220 fax + 39 06 4151 2102 e-mail claudio.bruno@thalesaleniaspace.com
ASD [Astrium GmbH] D-88039 Friedrichshafen (Germany)
• Wolfgang Pitz tel. + 49 7545 8 9609 fax tel. + 49 7545 8 5869 e-mail wolfgang.pitz@astrium.eads.net
ASU [Astrium Ltd] Anchorage Road, Portsmouth, PO3 5PU, United Kingdom
• Mike Buckley tel. + 44 2393 705944 fax + 44 2393 708290 e-mail mike.buckley@astrium.eads.net
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ITT Calendar
System Procurement Item Procurement
Method
Procurement
Responsible
Planned Date ITT
Issue on EMITS
01 SMSW - Safe Mode SW OC TAS-I Feb 08 CW 09
02 FSS - Fine Sun Sensor OC TAS-I Dec 07 CW 49
03 STT - Star Tracker OC TAS-I Dec 07 CW 49
04 MGM - Magnetometer OC TAS-I Dec 07 CW 49
05 MGT - Magnetotorquer OC TAS-I Dec 07 CW 49
06 RW - Reaction Wheel OC TAS-I Dec 07 CW 49
07 GYRO - Gyroscope OC TAS-I Jan 08 CW 04
01 PCU - Power Control Unit OC TAS-I Jan 08 CW 03
02 PPDU - Power Protection & Distribution Unit OC TAS-I Jan 08 CW 05
03 CAPS - Central Antenna PS OC TAS-I Jan 08 CW 05
04 BTA - Battery OC TAS-I Jan 08 CW 01
05 SAW - Solar Array Wings OC TAS-I Jan 08 CW 01
06 SADA - Solar Array Deploym. Assy OC TAS-I Jan 08 CW 01
THERMAL CONTROL 03 01 TCS - Thermal Control S/S OC TAS-I Dec 07 CW 50
TT&C 04 01 SBA - S-band Antenna OC TAS-I Jan 08 CW 02
01 FVV - Fill and Vent Valve OC TAS-I Dec 07 CW 50
02 LT - Propellant Tank OC TAS-I Dec 07 CW 50
03 PT - Pressure Transducer OC TAS-I Dec 07 CW 50
04 FDV - Fill and Drain valve OC TAS-I Dec 07 CW 50
05 LF - Filter OC TAS-I Dec 07 CW 50
06 LV - Latching Valve OC TAS-I Dec 07 CW 50
07 RCT - Reaction Control Thruster OC TAS-I Dec 07 CW 50
PROPULSION 05
AVIONICS 01
EPS 02
ITT Reference
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ITT Calendar
01 DSHA - Data Storage & Handling Assembly OC Dec 07 CW 49
02 PDHT Antenna Assembly (Assy) OC TAS-I Dec 07 CW 50
01 S/C DC & PYRO Harness (BUS, PDHT) OC TAS-I Mar 08, CW 13
02 S/C RF Harness OC TAS-I Mar 08, CW 13
03 S/C 1553B Harness OC TAS-I Mar 08, CW 13
CS - Control Section (HW & SW)
PIE - Platform I/F EmulatorPDE - Payload & Data EmulatorPDHT SCOE (XB Data Ingestion, Std Instruments)
RF Equipments (XBFE, PCA)
PPC - Post-processing PC01 PWR SCOE - Power Supply SCOE OC TAS-I Jan 08 CW 03
02 TT&C SCOE OC TAS-I Feb 08 CW 08
03 DC LAS - DC Load Antenna Simulator OC TAS-I Jan 08 CW 03
04 TM/TC FE OC TAS-I Dec 07 CW 51 SCA - S/C Adaptor
SHS - S/C Horizontal Handling Device
SVS - S/C Vertical Handling Device
MCB - Manacle Clamp Band
BST - BUS Integration Stand
SIT - S/C Integration Trolley
OC
TAS-I
PDHT 06
01
01S/C MGSE 10
S/C HARNESS 07
S/C EGSE
PDHT EGSE
09
08 Feb 08 CW 06
OC
TAS-I Mar 08, CW 13
System Procurement Item Procurement
Method
Procurement
Responsible
Planned Date ITT
Issue on EMITS
ITT Reference
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Corporate Communications
ITT Calendar
S-Band Suitcase 11 01 S band Suitcase OC TAS-I Feb 08 CW 09
01 Tile Control Unit (TCU) OC ASD Nov 07 CW 46
02 Elevation Plane Distribution Network (EPDN) OC ASD Nov 07 CW 46
01 Tile & Antenna Thermal Hardware ATHW OC ASD Jan 08 CW 01
02 Azimuth Plane Distribution Network (APDN) OC ASD Nov 07 CW 46
01 Tile & Antenna non-RF Harness OC ASD Dec 07 CW 51
02 Tile & Antenna RF Harness OC ASD Dec 07 CW 51
SAS EGSE 15 01 SAS SCOE OC ASD Jan 08 CW 03
SAR Instrument Test 16 01 SAR Test Facility OC ASD Apr 08 CW 15
Payload Transportation Container OC ASD Apr 08 CW 15SAR Alignment and Integration MGSE OC ASD Apr 08 CW 15
SAR Deployment MGSE OC ASD Apr 08 CW 15
SAS Radiated Test Mechanical Support OC ASD Apr 08 CW 15
SAR Handling Device OC ASD Apr 08 CW 15
SAR Stand OC ASD Apr 08 CW 15
SES Instrument Control Electronics (ICE) 18 01 Power Control Module PCM DC Converter OC ASD Oct 07 CW 44
SES Harness 19 01 Harness OC ASD Oct 07 CW 44
SAR MGSE
CSAR Antenna Tile
CSAR Antenna Items
CSAR Harness
0117
12
13
14
System Procurement Item Procurement
Method
Procurement
Responsible
Planned Date ITT
Issue on EMITS
ITT Reference
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Corporate Communications
ESTEC & EC FP7 WEB SITES
11. Contact Points at Industry
FP7 EC Web Server (Intended ITT List) :
http://cordis.europa.eu/fp7/cooperation/space_en.html
FP7 ESTEC Web Server (ITT Published Packages for Download) :
https://gmesfp7emits.esa.int/
November 26 , 2007
GMES Sentinel-1Industry Day for EC FP7 CountriesEQUIPMENTS & GSE
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Corporate Communications
Function: Thermal control of the SAR AntennaNo. of Units:
1 set of EQM MLI blankets for a single tile
1 set of PFM MLI blankets for the complete SAS incl. spare items/material
Typical Performance & I/F: Standard Multi Layer Insulation with the following composition:
■ ITO/SiOx coating on external layer as protection against atomic oxygen andESD
■ 2.75 mil Black Kapton foil (1 x VDA) as external layer to avoid lifetimedegradation
■ 5 - 7 layers of 0.25 mil Mylar foil (2 x VDA) & Dacron spacer as innerpackage
■ 2 mil Kapton foil (2 x VDA) as inner layer
ASD
12/A. Mechanical & Thermal, MGSE
SAR Instrument – SAS Thermal HW(ATHW)
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MGSE Functional Description
12/A. Mechanical & Thermal, MGSE
MGSE identified as items elected for Open Competition :
■ PTC (Payload Transportation Container)■ SCA (S/C Adaptor)■ SHS (S/C Horizontal Sling)■ SVS (S/C Vertical Sling)■ MCB (Manacle Clamp Band)■ BST (BUS Integration Stand)■ SIT (S/C Integration Trolley)■ THTC (S/C Thermal Blanket Container)
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Power Subsystem Architecture
Electrical Power SubsystemPerforms the following functions:Electrical power generation & storageConditioning / protection / distributionSADA may be replaced by flex cable/ twist capsule system
S/C Power Generation and Distribution
SAW 1
SAW 2
SADM 1
SADM 2
BATTERY
PCU
CAPS
PPDU
Power (28 V reg, not switched) to P/L electr.
Power (65 V max, switched) to P/L ant.
Power (28 V reg, switched) to P/L ant.
Heaters (not switched) to P/L ant.
Lines (38 V max) to bus users
Pyro lines
Heaters lines
TM/TC to/from ICSTM/TC to/from P/L electr.
TM/TC to/from ICS
TM/TC to/from ICS
TM/TC to/from ICS Synch lines
TM
UMB interface
12/B. Power, Electrical, Harness, EGSE
AAS-I
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Unit main task is to provide an unregulated power bus up to 38V to Spacecraft users,with the exception of SAR P/L fed by CAPS, by performing the following functions: Solar Array power conditioning basing on MPPT tracking Li-Ion Battery charge management
Key Features Solar Array and Antenna deployment actuation (under OBC control) Heater lines handling (under OBC control) and Heaters current sensing Battery & Solar Array monitoring Umbilical IF to enable ground operations Housekeeping TM’s OBC interfacing by means of discrete TM/TC’s and 1553MIL-STD Bus
End of Life (EOL) Power Figures Overall Output Power = 4400W Output power to PPDU: 1300 W Output power to BATTERY/CAPS : 2900 W (including 2000 W for battery
charging) Output power for heaters: 200 W (average power)
AAS-I
12/B. Power, Electrical, Harness, EGSE
S/C Power Control Unit (PCU)
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ELECTRICALSCHEMATIC
202535Number of Outlets
10 A2.5 A1 ASteady-state current
MB-20FMB-5FMB-2F
AAS-I
12/B. Power, Electrical, Harness, EGSE
PPDU
The PPDU distributes on fuse protected lines the unregulated Main bus fromPCU
Key Features■ CERMET type fuses, in redundant configuration■ Maximum output power = 1700W■ Mass ≤ 3,2 Kg
F 3
F 2
F 1 F1
F 2
RS
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The unit shall supply P/L instrument providing the following lines: Power lines @ 28V regulated, switched and fused for P/L electronics Power lines up to 65V unregulated, switched and fused for antenna Tiles (TPSU) Power O/P capability towards TPSUs: 4200 W Power lines 30÷38V unregulated, switched and fused for Tiles Telemetry & Control
Units (TCU) Heater lines (unregulated) 100W @38V, switched, fused, grouped, group fuse and
group switch
Key Features Availability of Sync lines for C-SAR antenna and P/L electronics Voltage & current sensing on TPSU power lines Filtering on TPSU lines (to reduce conducted emission) Galvanic isolation on TPSU lines Serial I/Fs with C-SAR electronics Discrete TM/TC with OBC P/L Shut Down implementation by means of EQSOL (load-shed) signal receiving
from OBC Mass: 56 Kg
AAS-I
12/B. Power, Electrical, Harness, EGSE
CAPS
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The battery shall supply electrical power to the S/C during the following conditions: Eclipse Periods During peaks power demand in sunlight During launch phase (lift-off till solar array deployment)
Key Features Li-Ion cell technology CN, Nameplate Capacity (+20°C, BOL) = 324 Ah Max discharge power in eclipse ≥ 1950 W. Orbital Period = 99 min; Eclipse period = 3 month per year; Max eclipse duration =
19 min Performance degradation to be calculated over 50000 cycles (accounting 2 cycles
per each orbit with eclipse ,90 days per year, and 1 cycle x orbit w/o eclipse) EOL min Discharge voltage = 28 V; Max charge voltage = 37,4 V G10K4DX temperature sensors, Heater provision for thermal control Lifetime 7 years. Extension up to 12 years (in reduced operational mode) 10 years storage Battery assembly mass ≤ 130 Kg
AAS-I
12/B. Power, Electrical, Harness, EGSE
BTA
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12/B. Power, Electrical, Harness, EGSE
SOLAR ARRAY WINGS - SAW
Satellite -Y side (Sun side)
SOLAR ARRAY WING
Two Solar Array Wings
Each one made by : 5 sandwich panels GaAs Triple Junction solar cells One sandwich yoke One cable synchro system Ten spring actuated hinges
Each wing is stowed on S/C with HoldDown points by tie rods crossing thestack of panels
The release is made by releasecomponents internally redounded
Each panel is linked to the neighborby pairs of spring actuated hinges
GaAs solar cells network provide4800 W EOL 22° Sun Angle SummerSolstice.
Sandwich Panels
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Allowing Power Control Unit (PCU) to interface the Solar Array, the SADA functionsare: Perform Solar Array rotation under OBC commands Acquire power coming from Solar Array Wings and making it available on PCU
connectors Acquire Sola Array Wings telemetries, such as thermistors and/or deployment
switches Yokes mechanical interfacing.
Key Features Continuous sinusoidal rotation (sweep mode) with +/- 32° amplitude. 15000 cycles number; factor 2.0 to be applied for qualification. Solar Array power transfer up to 80 A for each SADM Solar Array signal and bleed lines transfer towards S/C TM/TC interfacing with OBC Overall assembly mass ≤ 3 kg
Alternatively SADA may be replaced by a “flex cable” or “twist capsule” system
AAS-I
12/B. Power, Electrical, Harness, EGSE
SADA
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Corporate Communications
Components pictures for ref. only
S/C Harness
SENTINEL-1 Harness Subsystem provides theelectrical interconnections necessary to allowthe distribution of power and signals. It iscomposed of the following main components:
DC Harness Unit & Heater power supply TM / TC signals distribution (thermistors acquisition,
status telemetries, discrete commands, serial digital,broadcast pulses, etc.)
RF Harness Waveguides, coaxial cables and RF miscellaneous
Pyro / NEA / Thermal Knife Harness For deployment activation of SAR antenna, Solar
Panels, other possible appendages1553 Data BUS Harness
For data exchange between Bus Controller (BC)resident in SMU and Remote Terminals (RT)
Launch Vehicle Umbilical Connector Harness For on-ground Spacecraft to launch vehicle
interconnection
AAS-I
12/B. Power, Electrical, Harness, EGSE
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12/B. Power, Electrical, Harness, EGSE
PDHT Harness
SENTINEL-1 PDHT Harness Subsystem provides theelectrical interconnections necessary to allowthe distribution of power and signals. It iscomposed of the following main components:
DC Harness Unit power supply TM / TC signals distribution between DSHA and
TXA-XBAA units (thermistors acquisition, statustelemetries, discrete commands, serial digital,etc.)
RF Harness Waveguides, coaxial cables and RF
miscellaneous for TXA
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S/C EGSE
AAS-I
12/B. Power, Electrical, Harness, EGSE
•ESE Overall Architecture
CCS
Monitor &Control Kernel
Test SequenceEnvironment
DatabaseManagementEnvironment
OperatorInterface &Synoptics
RuntimeDatabase
SCOE Interface
Test DataArchive
Reporting Tools
Ext. DB(SRDB)
Specific Post-Processing
Tools
Remote AccessInterface
DCLASICS SCOEPSS SCOE TT&CSCOE
LAUNCHBASECOTE
PDHTSCOE
ECHS
External Entities(on Internet)
AIS
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S/C EGSE
The following EGSE items shall be produced to support the various AIT phases:
SAS EGSE (used at Subsystem level)
SES EGSE (used at Subsystem level)
PDHT EGSE (used at S/S level and partially reused at System level) Partialnew development.
DCLAS + AIS (used at system level) New development. ICS EGSE (a.k.a. ICS TE or Avionics EGSE, used S/S level and partially reused
at System level)
PSS SCOE (used at system level to power up the S/C by means of Solar ArraySimulator, Batteries Simulation, Pyro and/or Thermal Knife measurement,Sensors Simulation). New development.
AAS-I
12/B. Power, Electrical, Harness, EGSE
EGSE Overall Description
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S/C EGSE
TMTC SCOE ( used at System level to get TM data stream, decommutate it,send to CCS, to get TC packet from CCS, encode them according ESAstandard and send to S/L). New development.
The TT&C Suitcase. New development
The TT&C SCOE (used at System Level to perform the test with the TT&CSubsystem). New development.
It shall be possible to interface all this EGSE items to a common Central CheckoutSystem (CCS) already available at AAS-I. Communication protocol specificationtoward CCS will be issued by AAS-I.
AAS-I
12/B. Power, Electrical, Harness, EGSE
EGSE Overall Description
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PDHT EGSE
The PDHT EGSE shall be composed by the following functional blocks:
Central Control Section (CCS): (set of) computer(s) running the software package to control the testexecution. It allows the test preparation and configuration, the execution of automatic testsequences, the data monitoring, archiving and the test report preparation
Platform Interface Emulator (PIE): a set of FEEs to handle power lines, TM/TC links, 1553 on-boardbus, analogue and digital lines.
SAR Data Simulator (SDS): a high-speed generator of SAR simulated data
PDHT SCOE, including: RF Equipment, including:
■ Double-Polarized Channel Assembly (DPCA)■ X-band Front-End (XBFE)■ X-Band Down-Converter and Q-PSK Demodulator■ EGSE Standard Instrumentation (ESI)
Data Archive Module (DAM) Post-Processing Computer (PPC)
AAS-I
12/B. Power, Electrical, Harness, EGSE
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SES SCOE Rack: 19 inches rack for housing of avionics system simulators, internal rack
harness, specific grounding to support EMC testing, power conditioning anddistribution
SES SCOE Test Control Computer : Man-machine interface, interface to avionics system simulators which are
integrated into SES SCOE, TM/TC database, provisions for automatic testprocedures development and execution, TCP/IP interface to InstrumentCheckout System (ICS) for SES SCOE remote control
CAPS Simulator (integrated into SES SCOE) : Provision of ICM power, Tx/Rx power, TGU power, CTRL IF to/from ICM
OBC Simulator (integrated into SES SCOE) : Provision of 1553B Bus, 1PPS and EQSOL interfaces
MMSU Simulator (integrated into SES SCOE) : Provision of SAR Data interface, TBD GByte Memory for intermediate
storage of radar data
ASD
12/B. Power, Electrical, Harness, EGSE
SAS EGSE
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TCU Simulator: Provision of Antenna Control Bus (ACB), Antenna Timing Bus (ATB)
interfaces, simulation of 1 to 14 TCUs
DEU (Data Evaluation Unit Computer): SAR Data IF, MATLAB SW and tools, raw data pre-processing, quick-look
plausibility check, data archiving possibility, TCP/IP IF for remote control
SES RF-SCOE: RF interfaces to ICE, TGU and MDFE, RF measurement Equipment
Echo Simulator: RF Tx/Rx interfaces, simulation of echo signals
ICS (Instrument Checkout System Computer): Man-machine interface, interface to various SCOEs, TM/TC database,
automatic test procedures development and execution, TCP/IP interface toSatellite Checkout System for ICS remote control
ASD
12/B. Power, Electrical, Harness, EGSE
SAS EGSE
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RF-SCOE : RF interfaces to SAS, RF measurement Equipment, TCPIP IF for remote
control
HPA Suppression Equipment :
Prevent TGU Enable/ Disable TPSU Outlet IF suppression electronic andradiation detectors
ASD
12/B. Power, Electrical, Harness, EGSE
SAS EGSE
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FSS
Fine Sun Sensor Specification
■ Each Sun Sensor assembly shall consist of two redundant two axis sun sensors.Each one is able to provide analog output data for the calculation of the solarangles.
■ The Overall Linear Field Of View of each Sun Sensor assembly over the twoaxes w.r.t. the Optical Axis shall be at least:
α ∈ [-64°,+64°] and β ∈ [-64°,+64°].■ The absolute accuracy of the Sun Sensor, on the determination of the Sun
position angles shall be better than 0.30° at EOL.■ The non systematic Noise Equivalent Angle (NEA) will be within 0.04°.
AAS-I
12/C. Avionics & Propulsion
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ASTR
Star Tracker Specification
■ The STRs are used for attitude determination throughout the overall mission■ 3 STRs will be used in a two out of three configuration for high precision
attitude tracking mode in Normal Pointing Mode (NPM).■ The STT shall be able to estimate the attitude with no a priori knowledge
(lost in space function). No permanent degradation with direct sun pointing.■ The low-frequency (orbital) error shall be better than 3.6 arcsec (3σ) under
thermal stability environment condition of +/- 5°C and S/C low rate (< 0.5°/s).■ Bias and Long Term error shall be better that 10 arcsec.■ Random error shall be better than 9 arcsec (3σ).
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12/C. Avionics & Propulsion
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MGM
Magnetometer Specification
■ The Magnetometer Assembly is composed of two Three Axes Magnetometers,one operating the second in cold redundancy.
■ The field measurement range: ±0.6 Gauss.■ The scale factor deviation within operating temperature range: ± 0.8% max■ The accuracy: < ±4 mGauss and once calibrated shall permit measurement
errors lower than 0.2°.■ The Root Mean Square (0.5-16) Hz of output noise is expected to be 0.03
mG/Hz0.5 max. (3σ) over the temperature range without calibration.■ Instrument Bandwidth: > 50 Hz■ Axial Alignment: ± 1°.
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12/C. Avionics & Propulsion
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MGT
Magnetic Torquers Specification■ The mission requires the usage of a Magnetic Torquer Assembly which shall
include three magnetic torque rods each including, in a single housing, two coils incold redundancy.
■ The Magnetic Dipole Moment shall be ±300 Am2 in linear range and ±375 Am2in saturation range.
■ Linear power consuption: < 7.5 W■ Supply voltage range: linear ±12 V – non linear ±16 V■ The Magnetic Dipole Moment (residual) shall be ±1.8 Am2 (3σ) after saturated
case.■ Dipole step response time: < 200 ms■ Linearity error: < 5%
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12/C. Avionics & Propulsion
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RW
Reaction Wheels Specification■ Reaction Wheel Assembly (RWA): four independent Reaction Wheels
arranged in a pyramidal configuration.■ The main parameters of each Wheel are listed in the following table:
< 14 WSTEADY STATE POWER CONSUMPTION
< 90 WPEAK TORQUE POWER CONSUMPTION
DIGITAL SERIAL BI-LEVELSPEED DIRECTION TELEMETRY
< 4 WSTANDBY POWER CONSUMPTION
< 8 KG (inc electronics)MASS
<10 G CM ²DYNAMIC UNBALANCE
<1.0 G CMSTATIC UNBALANCE
>10 HZMOTOR LOOP BANDWIDTH
0.02 Nm EOLLOSS TORQUE
±0.1 NmOUTPUT TORQUE CAPABILITY
±30 NmsANGULAR MOMENTUM RANGE
PerformanceParameter
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12/C. Avionics & Propulsion
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GYRO
Precise Gyro Package Sensor Specification■ The Redundant rate integrating Gyro Package shall provide to the AOCS an high
precision accumulated angular increments to reconstruct the 3 axis spacecraftrate.
■ The redundancy scheme shall be or a two fully redundant 3-axis packages or asingle 4-channels redundant package, where the fourth channel is able to providea backup measurement for all the three nominal ones.
■ The Gyro package sensor data shall be acquired by the SMU via Mil 1553 Bus.■ For attitude measurements the gyro data will be used in combination with STRs
<0.0025°/√hrAngular Random Walk ARW< 7 KgMass
EOL wc< 30 WPower
turn-on to turn-on< 0.25 °/hr (3σ)absolute bias repeatability
Under nominal missioncondition
< 0.02 °/hr (3σ)Bias Stability
Over full mission< 500 ppmScale factor stability
< 10 ppmScale Factor Linearity
both polarities=> 10 °/sLinear angular rate range
CommentsPerformanceParameter
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12/C. Avionics & Propulsion
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PROP
Main data and architecture Chemical monopropellant (hydrazine) blow-down
system with 14 RCTs arranged into twofunctionally redundant branches.
Helium gas for a 22bar BOL MEOP pressurelevel
Leak-fault protection with three barriers (LV anddouble-seats RCT)
Functions & Performance: Orbital insertion correction Orbital drag compensation EOL disposal maneuvers Mass: < 18kg
Major Items data: RCT: 1N, > 60,000 pulses, Mib_av: 0.029Ns Tank: PMD type,180 litres
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12/C. Avionics & Propulsion
•Propulsion •
TL•T
FVV •
FDV
•PT
•LF•
LT•
mechanical joint•
RCT14• RCT8• •…• RCT7• RCT1• •…•
LV1• •
•LV2
1.•L
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Role: Real-time control of the EFEs of each Tile, using look-up tables,based on timing signals received from SES-Timing Control Module(TCM)
No. of Units (each cold-redundant): 1 EBB + 1 EQM + 1 PFM + 14 FMs Envelope: max. 640 mm x 90 mm x 50 mm Mass: max. 3 Kg Power Consumption: max. 10 W
Key Features: Intelligent Packet Terminal based on microcontroller or microprocessor Boot-S/W in PROM plus Application S/W in non-volatile memory (modifiable
during mission), TM/TC by Services acc. to Packet Utilisation Standard Real-time calculation of EFE control parameter sets, based on look-up tables,
including compensation of parasitic effects of EFEs Acquisition and digitisation of analogue HK signals (voltages, temperatures) Non-volatile memory (~2 MByte) for look-up tables
ASD
12/D. Digital Electronics, RF Units, Antennas
TCU
SAR Instrument - Tile Control Unit
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Interfaces: Unregulated (30 ... 38 V) primary power
TM/TC Interface to SES via CAN-Bus (7 TCUs on the same Bus)
Timing Control Interface from SES■ Reception of 3 discrete Timing Signals (Tx Gate, Rx Gate, PRI Sync)
■ Reception of Table Addresses via serial Bus (16 bit)
Control and Monitoring Bus to EFEs■ Distribution of 4 discrete Timing Signals to 10 EFEs (Clock, Tx Gate, Rx Gate, PRI Sync)
■ Transmission of control parameters to 10 EFEs up to once per PRI (0.3 to 1 ms) via bi-directional serial Bus
■ Reception of Housekeeping Data from 10 EFEs via bi-directional serial Bus
Analogue Inputs for HK Voltages (0 … 5V)
Temperature Acquisition Inputs (PT1000 Sensors)
ASD
12/D. Digital Electronics, RF Units, Antennas
SAR Instrument - Tile Control Unit
TCU
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Role: Distribution of RF Signals on the Tile Per tile 1 unit consisting of 3 networks (Tx, RxV, RxH), preferably in a stack
configuration (one on top of the other) No. of units: 1 BB + 1 EQM + 1 PFM + 14 FMs
Key Features and Interfaces: 1:10 RF distribution (eventually 2 x 1:5 plus 1 x 1:2) Nominally equal phase/equal gain Frequency range 5.405 GHz ± 75 MHz Input power capability (Tx network): 27 dBm > 25 dB port isolation High thermal phase/gain stability (no PTFE allowed) SMA connectors Temperature range: -20°C to + 60°C Envelope: max. 200 mm x 50 mm x 25 mm Mass: max. 1 kg
ASD
12/D. Digital Electronics, RF Units, Antennas
EPDN
SAR Instrument - Elevation Plane Distribution Network
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Function: Distribution of RF Signals (Tx, RxV, RxH) from SES to the TilesElements: a) RF Harness b) Combiners / Splitters (2 individual Subcontracts)A) Typical Performance & I/F for RF Harness:
Phase and Amplitude Stable Coax Harness (no PTFE Anomaly allowed)
Low Loss ~1dB/m @ 5 GHz
Phase Matched in Groups of different lenghts
Connectors SMA
Total Number of cables40 cables 1.0 meters30 cables 2.5 meters10 cables 5.0 meters
ASD
12/D. Digital Electronics, RF Units, Antennas
APDN
SAR Instrument - Azimuth Plane Distribution Network
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B) Typical Performance & I/F for Combiners/Splitters: 16 divide by 3 dividers/combiners (Input Power 30dBm max)
14 divide by 2 dividers/combiners (Input Power 33dBm max)10 1/7 (-8.5dB) couplers (Input Power 40dBm max)
Phase and Amplitude Stable (no PTFE Anomaly allowed)
SMA Connectors
Low Mass
ASD
12/D. Digital Electronics, RF Units, Antennas
APDN
SAR Instrument - Azimuth Plane Distribution Network
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12/D. Digital Electronics, RF Units, Antennas12/D. Digital Electronics, RF Units, Antennas
TT&C (SBA)
S-Band Antenna Specification Good co-polar vs. cross polar performance Compactness and robustness of the design Good electrical performance vs. environmental factors Frequency Band:
■ TELEMETRY Tx: Fo±10MHz■ COMMAND Rx: Fo±10MHz
Polarization:■ Main antenna: Circular RHCP■ Fill-in antenna: Circular LHCP
Coverage■ 0° < Φ < 360°■ 0° < Θ < 95°
Minimum Copolar Gain : -3 dBi Input Ports: 1 Power Handling: 5 Watt (6 dB Test) Mass: ≤ 0.250 kg
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PDHT & Crypto
According to the Sentinel-1 requirements and proposed work plan, different conceptsand configurations will be traded-off for the PDHT.
Two reference configurations have been so far identified :
Configuration A : PDHT with polarization reuse; Configuration B : PDHT with frequency reuse;
It can be presumed that the final solution will lie within the range of possible solutionsidentified by these two concepts.
For these reasons, the reference configurations hereafter and all the equipmentcharacteristics currently defined shall be understood as provisional.
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AESEncryption
1900 MbpsPDHT overall throughput
RS (255,223)Coding
O-QPSKModulation Scheme
RHCP and LHCPPolarization
2 deg/sAntenna Pointing Mechanism Speed
450 WMaximum Power Consumption (10% of contingency)
> 20 dBAntenna Gain (at 4.5 deg wrt Boresight)
> 18.45 dBWEIRP (on each channel)
8180 MHzFrequency Carrier
280MHzBandwidth (on each Link, without baseband shaping)
32 GbitsMass Memory Capacity HK/GNSS/POD (EOL)
896 GbitsMass Memory Capacity SAR Data (EOL)
300 MbpsInformation Data Rate (on each Link)
PerformanceParameter/Function
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12/D. Digital Electronics, RF Units, Antennas
PDHT Main Performance - Configuration A
PDHT & CRYPTO, Overview
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AESEncryption
1790 MbpsPDHT overall throughput
RS (255,239)Coding
4D-TCM 8PSKModulation Scheme
RHCPPolarization
520 WMaximum Power Consumption (10% of contingency)
> 6 dBAntenna Gain (isoflux, at EOC of 63.97 deg)
> 22 dBWEIRP (both on single and double channel)
8105 MHz and 8270Frequency Carrier
120 MHzBandwidth (on each Link, without baseband shaping)
32 GbitsMass Memory Capacity HK/GNSS/POD (EOL)
896 GbitsMass Memory Capacity SAR Data (EOL)
225 MbpsInformation Data Rate (on each Link)
PerformanceParameter/Function
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12/D. Digital Electronics, RF Units, Antennas
PDHT Main Performance - Configuration B
PDHT & CRYPTO, Overview
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DSHA Required Performance
Compliant to CCSDS 732.0-B-1
Compliant to CCSDS 732.0-B-1Downlink frame Format
28 Kg28 KgMass
Up to 2 * 600 MbpsGigalink, Wizard Link, SpW
Up to 2 * 600MbpsGigalink, Wizard Link, SpWSAR Input Interface
1553B1553BCommand & Control
AESAESEncryption
2*225 Mbps2*300MbpsInformation Data Rate
< 270W
File Allocation Table
> 20 min/orbit
SAR : up to 60min/orbitHK: 100%
GNSS/POD: 100%
1900 Mbps
1553B or SpW
32 Gbits (SD-RAM basedcubes)
896 Gbits (SD-RAM basedcubes)
PDHT Conf. A
1700 MbpsDSHA overall throughput
> 20 min/orbitMax Downlink duration
< 270WPower Consumption
File Allocation TableFile Management
1553B or SpWHK & GNSS/POD I/F
32 Gbits (SD-RAM basedcubes)Mass Memory Capacity HK/GNSS/POD
(EOL)
896 Gbits (SD-RAM basedcubes)
Mass Memory Capacity SAR Data (EOL)
SAR : up to 60min/orbitHK: 100%
GNSS/POD: 100%
Storage Duty Cycle
PDHT Conf. BParameter/Function
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DSHA/MMSU
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> 6 dB> 30 dBXPD
1dBpp(130MHz band, aperture angle from -64.5°
to+64.5°)
1dBpp (280MHz band)Amplitude Ripple vs.Frequency
5 Kg20 Kg (including APM & APME)Mass
6 dB at EOC (63.97° ± 0.5°)21 dB at boresightAntenna Gain
4 dBN/AMax Amplitude Ripplefrom Gain Mask
2.5°pp(130MHz band, aperture angle from -64.5°
to+64.5°)
2°pp (280MHz band)Phase Ripple vs.Frequency
8025 MHz – 8350 MHz8025 MHz – 8350 MHzBandwidth
10 W for each carrier
See next view
±64.5°
High gain narrow beam, 2 axissteerable antenna
PDHT Conf. A (Hard Keyed-Modulator)
90 W for each carrierPower Handling
±64.5°Coverage
Isoflux Wide CoverageAntenna Type
See next viewGain shaping
PDHT Conf. BParameter/Function
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XBAA
12/D. Digital Electronics, RF Units, Antennas
Antenna Main Requirements:
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12/D. Digital Electronics, RF Units, Antennas
ACRONYMS
AIT Assembly Integration Testing AIV Assembly Integration and Verification
AR Acceptance Review BDR Baseline Design Review
BLM Balancing Masses BTA Batte ry Assembly CADM Configuration And Data Management
CAPS C-band Antenna Power Supply CBS Cost Breakdown Structure CCN Contract Change Notice
CDR Critical Design Review CFE Customer Furnished Equipment
CFI Customer Furnished Item CI Configuration Item CIDL Configuration Item Data List
CIL Critical Item List COC Certificate of Conformance COTS Commercial Off -The Shelf
CR Change Request CRB Change Review Board
CRSA Coarse Rate Sensor Assembly CSAR C-band Synthetic Aperture Radar P/L CV Curriculum Vitae
DCL Declared Component List DCN Document Change Notice DD&V Design Development and Verification
DJF Design Justification File DHM DC Harness & Miscellanea
DM Documentation Management DML Declared Material List DOD Department Of Defense
DPH DC & Pyro Harness DR Design Review DRB Delivery Review Board
DRD Document Requirements Description DRL Document Requirements List
DSBF Dual S -band Filter DSHA Data Storage & Handl. Assembly DSL Documentation Status List
DVCM Design Verification Control Matrix
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12/D. Digital Electronics, RF Units, Antennas
ACRONYMS
ECP Engineering Change Proposal ECR Engineering Change Request
ECSS European Cooperation for Space Standardization EGSE Electrical Ground Support Equipment EIDP End Item Data Package
EM Engineering Model EPS Electrical Power S/S
EQM Engineering Qualification Model ESA European Space Agency
ESCC European Space Components Coordination FDIR Fault Detection Isolation and Recovery FGU Frequency Generation Unit
FM Flight Model FSS Fine Sun Sensor
GMES Global Monitoring for Environment and Security GNSS Global Navigation Satellite System
GPS Global Positioning System GS Ground System / Ground Segment GSDR Ground Segment Design Revi ew
GSE Ground Support Equipment GSRQR Ground Segment Requirements Review
GSRR Ground Segment Readiness review GSS Ground Segment System
GYP Gyro Package HW Hardware HYB Hybrid
I/F Interface ICD Interface Control Document
ICS Integrated Control S/S ICU Instrument Control Unit
IOCR In-Orbit Commissioning Review ITT Invitation To Tender
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12/D. Digital Electronics, RF Units, Antennas
ACRONYMS
IV&V Integration Validation and Verification LEO Low Earth Orbit
LEOP Launch and Early Orbit Phase LV Launch Vehicle MAIT Manufacturing Assembly Integration and Test
MGM Magnetometer MGSE Mechanical Ground Suppo rt Equipment
MGT Magnetotorquer MPP Milestone Payment Plan
MRB Material Review Board MRR Manufacturing Readiness Review NA Not Applicable
NCR Non Conformance Report NRB Non-Conformance Review Board
ORR Operations Readiness Review OTS Off The Shelf
P/L Payload PA Product Assurance PCU Power Control Unit
PDHT P/L Data Handling & Transmission PFM Proto-Flight Model
PGS Payload Ground System PM Project Manager / Project Management / Progress Meeting
PMO Project Management Office PMP Project Management Plan PPAM Programme Product Assurance Manager
PPDU Power Protection & Distribution Unit PPL Preferred Parts List
PRP Propulsion S/S
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12/D. Digital Electronics, RF Units, Antennas
ACRONYMS
QML Qualified Materials List QPL Qualified Part List
QR Qualification Report / Qualification Review QSL Qualification Status List
QSR Qualification Status Review RAM Reliability Availability Maintainability RAMS Reliability Availabilit y Maintainability and Safety
RFA Request For Approval RFD Request For Deviation RFP Request For Proposal
RFW Request For Waiver RID Review Item Discrepancy
RMP Risk Management Plan RW Reaction Wheel RXCU RX Chain Unit
S/C Spacecraf t S/S Sub System SADA Solar Array Drive Assembly
SADHM SAS DC Harness & Miscellanea SAR Synthetic Aperture Radar
SAS SAR Antenna Subsystem SAWA Solar Array Wing Assembly SBA S-Band Antenna
SBFN SAS Beam Forming Network TX/RX SBT S-band Transponder SEDHM SES DC Harness & Miscellanea
SEMP System Engineering Management Plan SES SAR Electronics Subsystem
SM Stripmap SMEC SAS Mechanism SMU Spacecraft Management Unit
SOC Statement Of Compliance SOW Statement Of Work SPA Software Product Assurance / Societa’ P er Azioni
SRD System Requirements Document / S/W Requirements Document SRR System Requirements Review
SSO Sun-Synchronous Orbit STM Structural Model STR Structure S/S
STT Star Tracker SUBCO Subcontractor SWCB Software Configuration Control Board
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12/D. Digital Electronics, RF Units, Antennas
ACRONYMS
TBA To Be Agreed TBC To Be Confirmed
TBD To Be Defined TBW To Be Written THC Thermal Control S/s
TPN Tile Panel TRB Test Review Board
TRH TT&C RF Harness TRM Transmit / Receive Module
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