High technology small Space Systems High technology small
Transcript of High technology small Space Systems High technology small
High technology small Space SystemsHigh technology small Space Systems New operational concepts, innovative manufacturing
and air-launched platforms
The vision of Thales The vision of Thales AleniaAlenia Space ItaliaSpace Italia
Massimo Di Lazzaro SVP Sistemi di Osservazione e Radar- Thales Alenia Space - Italia
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Introduction
TAS is a World leader in the development of high performance Satellite Systems for Observation, Telecoms, Navigation .
Capabilities ranges from complex space systems engineering, integration and testing, to high technology equipments development.
TAS is a system leader in Constellation conception, development, and implementation.
� Mastering satellite series production : from COSMO-SkyMed, Sicral, Globalstar, Globalstar 2° generation, Galileo,… to new Iridium-next and O3b.
� About 150 satellites. � High volume production capability means mastering of processes, from design to
quality control of production and subcontractors, processes…
Small Satellites and Operationally Responsive Space will require Innovative System Architecture, technology developments and industrial co-operation to miniaturise high performance systems .
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A Complete Range of Space Competence and Technologies ready for microsatellites
GROUND SEGMENTSGROUND SEGMENTSSPACE SEGMENTSPACE SEGMENTE2E SYSTEMSE2E SYSTEMS
SATELLITES
PLATFORMS
PAYLOADS
INSTRUMENTS
EQUIPMEN T
System EngineeringMission ConceptionAnalyses and Design, ArchitectureDevelopment, AIV, IOT End to-End Deployment
GS EngineeringGS Procurement and
QualificationPDS/UGS Development
TECHNOLOGIES
EUROPEAN LEADEREUROPEAN LEADERFROM END-TO-END (E2E) SYSTEMS TO TECHNOLOGY FOR:
EARTH OBSERVATION , TELECOMUNICATION and NAVIGATION
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System Architecture Earth Observation – COSMO-SkyMed
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D-UGS
C-UGS
CGSGGS
Kiruna
Cordoba
External
Station
External
Station
Fiducial Network
Creil
F-DUGS
Fucino
MateraPratica di Mare
Geographical Distribution
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Major evolutions being implemented after COSMO : Highly integrated TRM with reduced MMIC, LTCC substrates and Molybdenum Carriers, Po > 42dBm, RF Core Chip for phase and amplitude control, evolution of ASIC’s to 18μ technology…
TPSU SBC
RADIATINGBOARD
T/R MODULE
TDL
Active SAR antenna is a key enabling technology
Enabling Technologies Earth Observation – COSMO-SkyMed
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System Architecture Telecommunication - SICRAL
Stazione TT&Cbanda SStazione TT&C
EHF Harden
FE “S”FE “S”FE “EHF”FE “EHF”
Stazione TT&C EHF
Stazione TT&C EHF
FE “EHF”FE “EHF”
Sicral 1B
Stazione TT&C EHF SICRAL 1
TLC SHFTLC SHFFE “EHF”FE “EHF”
Sicral 1
Satellite Control Center (Vigna di Valle)
TLC UHFTLC UHF
Satellite Control Center (Fucino)
TLC Control Center (Vigna di Valle)
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Enabling Technologies Telecommunication - SICRAL
Defense telecom system to for tactic and strategic use Multi-transmission communication payload operating in several frequency bands:
EHF Band (20-44 GHz), mainly devoted to infrastructural communication, with an antenna which footprint principally covers the Italian territory
UHF Band (260-300 MHz), primarily used for tactical mobile communication, with antenna footprint that covers the hemisphere of the Earth visible by the satellite
SHF Band (7/8 GHz), complementary to the EHF band, devoted to the large bandwidth communications
UHF Antenna
Antenna module
Solar ArrayDeployment
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Current product capabilities Small Satellites Telecom Constellations
GLOBALSTAR-2, O3B, and the IRIDIUM-NEXT.
O3B's network will consist of 16 satellitesfor faster, affordable internet to all the world's uncovered regions. Same platform of
Globalstar-2.
Globalstar-2’s network will consist of 48 satellites
for worldwide personalphone communication, which
will replace the existing Globalstar-1 system already
developed by TAS.
Iridium-next's network will consist of 66 satellites
providing voice and data coverage to satellite phones and integrated transceivers over Earth's entire surface
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Available PRIMA-S Platform Technology Ready for mini-Satellite
Compact SAR Mini-Satellite
Optical Mini-Satellite
Spacecraft parameters
Spacecraft structure Aluminum structure, Size: 1.3x1.3x1.3 m
Launch mass 400-500 kg
AOCS (Attitude & Orbit Control Subsystem)
- Gyro, Sun Sensors, Star Trackers, Magnetometer
- Autonomous GPS position determination - 3-axis attitude control, 4 RW- 1 hydrazine tank, up to 130 kg capacity; 4 thrusters 1 N configuration
EPS (Electric Power Subsystem)
-Power generated by two deployable solar array (GaAs; up to 1500 W EOL)
- 1 Li-ion battery; PCDU (Power & Control Distribution Unit)
On-board data handling
- On-board computer- 2 S-band transceivers for communication
Payload data management
- X band downlink - Storage memory
Performance - Payload mass: up to 200 kg - Spacecraft high agility
Possible PayloadsPossible Payloads
SIGINT Interception and decryption of military and strategic communicationsTELINT: Receptions of telemetry signals during ballistic missile tests
ELINT Interception of radar signal
TLC For tactical use
SAR Compact SAR reflector
Optical Panchromatic, Hyperspectral,IR
Sounder, Meteorology
Subsurface and atmosphere sounding
Current products allow the implementation of mini satellite configurations
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TAS I understanding of ORS Key Requirements
• The average time for deploying a Space Asset using existing technologies is today in the order of 24 months.
• That’s too long for applications that cannot be planned such as military tactical operations.
• New Space Systems requirements which may be met by small satellites: Responsiveness - provide required information when they are needed
trough:� Single Function - 1 payload per spacecraft � Fast integration & Verification (hours) => modular architecture, standard,
plug and play� Rapid launching system (days) => aircraft launch� Secure overall infrastructure to deliver acquired data� Data delivered to the end user nearly immediately in a form that they can
use
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TAS I understanding of ORS Key Requirements (cont’d)
• New Space Systems requirements which may be met by small satellites:
Flexibility - Provide multiple types of data (from different satellites based on the same bus)
Short duration - 6 months mission, optionally improved by propulsion system to 1-2 years
Micro S/L Class - 100Kg/300W ... Can be launched by available low cost rapid systems in response to worlds events or immediate needs:
� Reconstitute lost capabilities - Augment/Surge existing capabilities� Fill Unanticipated Gaps in capabilities - Focused coverage that can’t be
predicted Low Altitude - 200-400Km (allows small payloads & better
performance)
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Small Space Systems to enhance the defence space assets
Small Space Systems integrated and interoperable with current Space Assets of Defense (COSMO, SICRAL), to enhance their capabilities:
Improve responsiveness and effectiveness for specific crisis scenarioAdditional sensors (optical, passive, sounders…) and telecom servicesComplement COSMO observations, using same ground network and having data fusion in processingLEO Telecom services may use SICRAL 1B as GEO (visible at least for 10min in most orbits)A real breakthrough may result from deployment of low cost formations, for Imaging, ELINT, Telecom and other operational applications (e.g. meteorology)
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Possible Launch Scenarios
Several launch Options are possible for the proposed Micro-Satellites of which the two dominant low cost are:
Expendable Launch Vehicle (ELV)� Delta 4, Atlas v, Delta 2, Zenit 2 , Soyuz, Taurus PSLV, Falcon.
Converted Missiles� Minotaur 1, Cosmos 3M, Dnepr 1, Start, Rockot, Minotaur 4.
In addiction Micro Satellites meet Avio Launch requirements:� E.g. Pegasus, QuickReach
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Micro-Class Multi-Purpose Satellite Concept
MicroMicro--S/C spacecraft parametersS/C spacecraft parameters
Spacecraft structure Honeycomb, Size: 0.8 x 0.8 x 0.8 m
Spacecraft lauch mass < 100 kg
AOCS (Attitude & Orbit Control Subsystem)
- Sun Sensors, Star Trackers, (Magnetometer), (Gyro)
- Autonomous GPS position determination - 3-axis attitude control, 4 Micro-CMG- Chemical propulsion 2-4 thrusters
EPS (Electric Power Subsystem)
-Power generated by two deployable solar array (GaAs; up to 300W)
- 1 Li-ion battery; Power & Control Distribution Module
On-board data handling - On-board computer integrating data handling management and transceiver communication
Performance - Payload mass: up to 45% of launch mass- Spacecraft high agility
SAR
SIGINT
Optical
Possible InstrumentsPossible Instruments
ELINT, SIGINT
Small instruments, flying formations
TLC For tactical use, single or formations
SAR Small instruments, flying formations
Optical Panchromatic, Hyperspectral,IR
Sounder, Meteorology
Subsurface and atmosphere sounding
SHF- UHF CommsStore Forward
-Secure Comms. Data communication at 2Mb/s with S1B ad DRS (secure, global, integrated)-S1B UHF also could be used for H/K with larger coverage with data rate of 2Kb/s.-Enlarge the Sicral1B Operative Area by Store and Forward service.
Micro-Satellite 100 kg – 300 W Platform :
� Multi-purpose� Fast integration & verification� Fast commissioning & calibration
Responsive launch (on Demand).
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BUSPAYLOAD
Solar Array
Star Tracker
Helicoidal ELINT Antenna
X-band Mini SAR
Optical Telescope
Micro-Class Multi-Purpose Satellite Concept Standard Platform
Standard Platform with integrated high performance Communications and Data Handling:
Flexibility of Inter-Satellite Link (ISL) in for flying formations and DRS to GEO
TT&C, Payload Downlink and ISL are integrated to reduce mass and power, allowing to manage multiple data flow .
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EO Mission – SAR Satellites Constellation
LEO Inclined LEO SSO
LEO Sun Synchronous Orbit grants global Earth access capabilities (including polar regions).
LEO inclined allow to improve the revisit time performance on the mid latitude and equatorial areas but do not allow global Earth access
SAR Payload grants night/daylight and all weather observation capabilities.
Access areas can be both right and left looking within a typical incidence angle range from 20° to 60°
The revisit time depends on the selected orbital design and on the number of deployed satellites
On the whole Mediterranean areas a constellation of 12 SAR satellites operating at about 300km altitude is able to provide an average revisit time ranging from 2 hours (inclined solution) to 3 hours (SSO solution).
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EO Mission – Optical Satellites Constellation
LEO Inclined LEO SSO
Optical Payload requires daylight and cloud free observation conditions.
Access area is nadir looking with a typical FOV of +/-50°
The revisit time depends on the selected orbital design and on the number of deployed satellites.
On the whole Mediterranean areas a constellation of 12 Optical satellites operating at about 300km altitude is able to provide an average revisit time ranging from 3.5 hours (inclined solution) to 4.5 hours (SSO solution).
Solar illumination condition (e.g. reduced in Winter season on the northern hemisphere) and cloud coverage distribution can degrade these performance.
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EDRS
SICRAL 1B
GB2 / IridiumGB2 / Iridium
Elint Formation
Optical
CONTROL CENTER
Target TargetTarget
UHF SHF
SAR
LASER
Envisioned Operational Scenarios
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Single Satellite Responsive Operation
1
2
3
4
Mobile Ground Station
Warfighter
Target Area
Ground Network
PR
E-
TA
SK
IN
G
5
Single Satellite Responsive Operation
1. Send Tasking
2. Uplink Tasking
3. Target Acquisition
4. Downlink Tactical Product
5. Data Transmission to the Warfighter
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Enhanced Applications: Formation Flying
Formation Flying can enhance Mission Performance over single satellite : Access to targets from multiple angles or for longer time Opportunity to create synthetic apertures for interferometry or radar surveillance
missions and to increase the scope of field measurements for survey missions. Flexibility and Responsiveness Robustness and failure tolerance (at constellation level) Cost effective space systems
Key technologies : Intra Satellite Link (ISL) & synchronization among spacecrafts Accurate control of orbital position and relative baseline
Mission Domains: Optical Multi-static (MIMO) SAR formations
� Super-resolution imagery in range and azimuth� Digital elevation Model� Moving Target Detection
Passive Observation � ELINT : extended coverage, Direction Finding Techniques (DOA)� Microwave Radiometry (coverage, resolution with passive interferometry)
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SAR Micro-Satellite
Main features Programmable access by satellite elevation
steering in the range [20° .. 30°] (i.e. 60 km access region @300km altitude)
Strip-map mode Programmable range resolution (1..3 m)
Parameter Value
Access Region 20° …. 30°
Swath 8 … 10 km
ResolutionAzimuth
Range0.7 mSubmetric as a target
Nes°(@ 1m Rres)(@ 3m Rres)
-15 dB-20 dB
Parameter Value
Frequency Band 9600 MHz
PRF 10 .. 15 kHz
Pulse Width 20 us
Pulse Bandwidth 135 .. 400 MHz
Tx Duty Cycle 20 .. 25%
Peak RF Power 2000 W
Peak DC Power (short time)
1500 W
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Micro Satellite SHF TX/RX Data Relay
Micro Satellite SHF TX/RX features: Micro-strip Patch Array Antenna 12
elements X-Band sat-com STANAG 4484 :
� 7.25-7.55 GHz uplink� 7.90-8.40 GHz downlink� Tx Power ~10 W
Link and data handling performance: Data Rate: 2Mbps(1Mbps) with 0.5m
pointing (fixed) antenna TX/RX Carrier shift for Doppler
Compensation On Board Optional data storage up to 1000 Gbits,
with Flash memories or hard disks. Optional high rate X-Band downlink (>
200Mbps) using high order adaptive coding and high gain antennas.
Synchronization services for Micro Satellites flying formations: Interferometry Techniques for ELINT Interferometry Techniques for SAR
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.
Optical Micro-Satellite
S/C mass: 100 kg option (about 30 kg payload mass) � GSD : metric order (at nadir) @ 300 km � optical aperture less than 40 mm� swath width: 40 km� Communications: TT&C S-Band and Image transmission X-Band
S/C mass: 150 kg options (about 45 kg payload mass) � GSD : 1 meter order (at nadir) @ 300 km � optical aperture less than 200 mm� swath width: 15 km� Spectral bands: PAN+RGB+NIR� Communications: TT&C S-Band and Image transmission X-Band
Features� Low cost, maintain high performances and data quality;� Design to produce high data volume per day;� Design for low-cost constellation able to enhance system response capability and delivering
frequent and reliable information; � Platform design to provide the necessary highly agile attitude control, the system is capable
of time delay integration and rapid pitch and roll off-pointing, with the necessary stability.
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ELINT & SIGINT Micro-Satellite
Satellite clusters for ELINT Single satellite operations Cluster (cooperative) operations, to
better performance in terms of:� Detection� Emitters localization
Composite antenna Composite antenna
Antenna clusterAntenna cluster
Single antenna apertureSingle antenna aperture
Guard element Guard element
Resulting lobepatterns
Frequencies of interest:Pure ELINT
Navigation radars (2.9 - 3.1 GHz and 9.2 - 9.5 GHz in the S and X bands)
Surveillance radars (1 - 8 GHz in the L, S and C bands)
Tracking and fire control radars (8 - 20 GHz in the X, Ku and K (partly) bands)
Other applications In addition to radar emitters, radar jammers
and GPS jammers (at ~1.2 and ~1.5 GHz).
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Small Space Systems : Vision
The vision is in the Title of our Meeting: High technology small Space SystemHigh technology small Space SystemSubsystem and equipments modularity and scalability:
Inject new technology for miniaturization Standardisation and re-use of “building blocks” Seamless adaptability/configurability Rapid final testability/deployment
Systems modularity and scalability (e.g. “Formation Flying”, “Fractionated spacecraft systems”): Distributed architectures Multifunctional systems (e.g. in flight re-configurability) Inter-satellite and space-ground links High level of automation and autonomy
Strong interoperability with current Space assets Enhance performance and capability of existing systems (e.g. COSMO, SICRAL,….) Re-use of existing infrastructures for cost effective missions (e.g. Ground segment,
operational procedures, processors, data fusion, etc.)
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Final notes
• Italy has done the right investments that have created the necessary heritage, know-how and facilities to undertake the challenge to lead an Italian development for a Micro-Satellite based mission
• Enabling Technologies for MicroSats have been identified, as well as potential applications
• OSR and Microsatellite is not a Single company effort• Led by MoD and Agencies, TAS I, teaming with PMI and other
enterprises, proposes to define suitable mission profiles and industrial plans in order to : Execute feasibility and definition studies Establish development plans Plan the key technology developments
� Modular expandable micro-bus� Plug and Play Payloads (Radar, ELINT, SIGINT, Optical)
Propose & Develop a demonstrator