Transponder1

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



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

http://esamultimedia.esa.int/docs/industry/BestPractices/Best_Practices_August_2006.pdf



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



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



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



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



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)




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




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




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




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•




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


SOLAR ARRAY WING



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)




PDHT Configuration A5. Spacecraft (S/C) Concept

Payload Data Handling & Transmission PDHT



PDHT Configuration A PDHT Configuration B

Payload Data Handling & Transmission PDHT




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




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




Sentinel-1 S/C Development Phases

7. PROGRAM PHASES

AAS-I



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 [email protected]

ASD [Astrium GmbH] D-88039 Friedrichshafen (Germany)

• Wolfgang Pitz tel. + 49 7545 8 9609 fax tel. + 49 7545 8 5869 e-mail [email protected]

ASU [Astrium Ltd] Anchorage Road, Portsmouth, PO3 5PU, United Kingdom

• Mike Buckley tel. + 44 2393 705944 fax + 44 2393 708290 e-mail [email protected]



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



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


Method

Procurement

Responsible

Planned Date ITT

Issue on EMITS

ITT Reference



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


Method

Procurement

Responsible

Planned Date ITT

Issue on EMITS

ITT Reference



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/

http://cordis.europa.eu/fp7/cooperation/space_en.html/

https://gmesfp7emits.esa.int/

November 26 , 2007

GMES Sentinel-1Industry Day for EC FP7 CountriesEQUIPMENTS & GSE



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)



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)



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



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


S/C Power Control Unit (PCU)



ELECTRICALSCHEMATIC

202535Number of Outlets

10 A2.5 A1 ASteady-state current

MB-20FMB-5FMB-2F

AAS-I


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



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


CAPS



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


BTA




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



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


SADA



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



Corporate CommunicationsAAS-I


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



S/C EGSE

AAS-I


•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



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


EGSE Overall Description



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


EGSE Overall Description



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




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


SAS EGSE



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


SAS EGSE



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


SAS EGSE



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



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).

AAS-I




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°.

AAS-I




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%

AAS-I




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

AAS-I




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

AAS-I




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

AAS-I


•Propulsion •

TL•T

FVV •

FDV

•PT

•LF•

LT•

mechanical joint•

RCT14• RCT8• •…• RCT7• RCT1• •…•

LV1• •

•LV2

1.•L



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



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


SAR Instrument - Tile Control Unit

TCU



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


EPDN

SAR Instrument - Elevation Plane Distribution Network



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


APDN

SAR Instrument - Azimuth Plane Distribution Network



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


APDN

SAR Instrument - Azimuth Plane Distribution Network



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




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.



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

AAS-I


PDHT Main Performance - Configuration A

PDHT & CRYPTO, Overview



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

AAS-I


PDHT Main Performance - Configuration B

PDHT & CRYPTO, Overview



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)


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)


Mass Memory Capacity SAR Data (EOL)

SAR : up to 60min/orbitHK: 100%

GNSS/POD: 100%

Storage Duty Cycle

PDHT Conf. BParameter/Function

AAS-I


DSHA/MMSU



> 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

AAS-I

XBAA


Antenna Main Requirements:




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




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




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




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




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

Documents

Transponder1