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

All rights reserved © 2007, Thales Alenia Space2

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 .


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


System Architecture Earth Observation – COSMO-SkyMed


D-UGS

C-UGS

CGSGGS

Kiruna

Cordoba

External

Station

External

Station

Fiducial Network

Creil

F-DUGS

Fucino

MateraPratica di Mare

Geographical Distribution


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


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)


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


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


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


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


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)


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)


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


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).


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 .


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).


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.


EDRS

SICRAL 1B

GB2 / IridiumGB2 / Iridium

Elint Formation

Optical

CONTROL CENTER

Target TargetTarget

UHF SHF

SAR

LASER

Envisioned Operational Scenarios


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


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)


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


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


.

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.


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).


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.)


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

High technology small Space Systems High technology small

Documents

Transcript of High technology small Space Systems High technology small