sat 2 samara system for small geo - esa's artes ... (tx) (12.735 - 12.745 ghz) fwd (rx) (14.235...

2/27/2008, Thales Alenia Space

TASI- BU Navigation & Integrated Communications

Date: 6/2/2009 THALES ALENIA SPACE All rights reserved,

SAMARASatellite communicAtion systeM for Atm seRvice

System & Payload Solutions for Small GEO Platforms

ESTEC Noordwijk, 6th February 2009

Thales Alenia Space Italia Thales Alenia Space Espana Thales Alenia Space France



Date: 6/2/2009

THALES ALENIA SPACE ITALIA All rights reserved,

Contents

1.1. Highlights and BackgroundHighlights and Background2.2. SAMARA studySAMARA study

•• Activities OverviewActivities Overview•• Requirements and DriversRequirements and Drivers•• Main Outcomes and Key findingsMain Outcomes and Key findings•• Development and Deployment ApproachDevelopment and Deployment Approach

3.3. Conclusions Conclusions 4.4. WayWay forwardforward



Date: 6/2/2009


Overview of the Activities & Background

SESAR: initiative from the aerospace industry Indicates need for a new dual-link system for Air/Ground communications for 2020 with complementary terrestrial-based and satellite-based mobile communication technologies.

Iris: ESA programme dedicated to support SESAR Single European Sky Air Traffic Management Research Programme.

SAMARA: (Satellite communicAtion systeM for Atm seRvice):Phase A: Analysis and definition of the Satellite System Study leaded by Thales AleniaSpace – Italia as Prime Contractor Consortium composed by Thales Alenia Space Espana and Thales Alenia Space France, Selex SI, INDRA Espacio, OHB, Airtel ATN, Frequentis, Conplan, JSC “ISS –Reshetnev Company”.Defines the satellite communication system to fulfil the aviation service requirements.



Date: 6/2/2009


Need of a Satellite Dedicated System

Existing systems providing satellite communications for the ATM servicesGEO: INMARSAT, MTSAT LEO: Iridium constellation. providing the ATM services for Oceanic, Remote and Polar (ORP) regions operating in L-band (AMS(R)S)ICAO standard

ICAO Future Communication Infrastructure study: existing aeronautical communication satellites not capable of fulfilling the aeronautical communication requirements because the insufficient throughput per aircraft availability requirements not satisfied

A dedicated satellite system is also necessary to comply with the reliability performance required by the Safety of Life servicesto provide the ATM service on the ECAC area in the dual link configuration (terrestrial Air/Ground link and satellite link) as indicated in the SESAR programme.



Date: 6/2/2009


SAMARA Study (1/2)

SAMARA mission: to provide alternative comms means to carry Air Traffic Communications by satcom system

Baseline: full coverage over the ECAC European AreaOptions: over the whole world and the north polar areas.

to provide satellite based ATS (Air Traffic Service) and AOC (Airline Operational Communication) services between the airspace users and the ground aeronautical entities (ANSPs and Airline Operation Centers ) aligned with the SESAR implementation of the Single European Sky target concept.answer to the challenging Safety of Life services requirements

SAMARA satellite system and the deployment strategy defined starting from:

System Requirements Document,Protocol definition as provided by both Communication studiesTarget of a low cost new avionic satisfying the availability requirement for the safety of life operations,

SESAR time line



Date: 6/2/2009


SAMARA Study (2/2)

Assessment of satellite system user requirements in the context of the SESAR initiativeTrade-offs between different system architecture optionsDefinition of System Operational ConceptSatellite System Architecture definition

definition of preliminary Satellite System Architecture with aeronautical active antennastrade off for Ancillary Payloads

refinement with low gain antenna for the airborne equipment basing on on communication standard system performances and architecture provided by both communication standard.

Definition “subset system” to allow the system validation and certification during the preoperational phase.Two options for ATM Payload:

Payload with “reduced” capacity to be used for the subsetPayload with “full” capacity to be used for operational systems

Certification and liability issues analysis SAMARA Business Case and Service Model



Date: 6/2/2009


Analyses of Input Requirements (1/2)

COVERAGE REQ.: Subset Mobile and Fixed Link Requirement Compliance over ECAC Boundary

Carrier data rates vs spot beams:Refined information rates and number of channels based on optimized link budgets and capacity allocation provided by the Agency and based on Communication Studies

Scenario subsetMinimum number of carriers : 22 Assuming the 3 spot beams originally used in Task 2, the distribution among the beams is 5-12-5, one carrier per beam of 16 kbps, 1 carrier per beam of 32 kbps and all other carriers of 64 kbps

Scenario fullMinimum number of carriers : 59Assuming the 3 spot beams originally used in Task 2, the distribution among the beams is 13-32-142 carriers per beam of 16kbps, 2 carriers per beam of 32kbps and all other carriers of 64kbps

Mobile Fixed

A

BC



Date: 6/2/2009


15Lifetime (Years)

18 target 2014 target 1818 target 2014 target 18C/I (dB)

-1.0-1.0-1.0-1.0Min G/T (dB/K)

3141.83141.8Min. EIRP (dBW)

U/L: RHCPD/L: LV

U/L: LHD/L: RHCP

U/L: RHCPD/L: LV

U/L: LHD/L: RHCP

Ant. Polarization

5.045.192.101.94Total BW (MHz)

3 carrier rate types: 12.5 kbps25 kbps50 kbps

3 carrier rate types: 16 kbps, 32 kbps 64 kbps

3 carrier rate types: 12.5 kbps25 kbps50 kbps

3 carrier rate types: 16 kbps, 32 kbps 64 kbps

Carrier data rate

From SB A: 12From SB B: 41From SB C19

RTN

From SB A: 6From SB B: 13From SB C: 6

RTN FWDFWD

Tot. no of carriers

Scenario fullScenario subset

To SB A: 13To SB B: 32To SB C: 14

To SB A: 5To SB B: 12To SB C: 5

Analyses of Input Requirements (2/2)



Date: 6/2/2009


SAMARA Study Outcomes for In Orbit Design

User link at L band characterised by: multi beams coveragehigh EIRP demanding G/T

Low cost approach

Dimensioning and design of L band antennabeams generation approachreflector dimensions

Payload driversarchitectureconsumption, dissipation and mass

Two payload options:Payload with reduced capacityPayload with full capacity

Small/Medium GEO platformsA. OHB Luxor for reduced capacity

payloadB. Spacebus 4000 B2 for full

capacity



Date: 6/2/2009


Subset Payload: Key findings

Subset Payload:Repeater mass: 270 kgDC consumption: 3230 W (Psat-4 dB OBO)L-Band antenna

shaped reflector 4 meters diameter

OHB Luxor platform.

The proposed design resulted form the trade-off analysis as the most cost effective solution.



Date: 6/2/2009


Subset Payload Block Diagram

Ku-BandFeeder link

RTN (TX) (12.735 - 12.745 GHz)

FWD (RX) (14.235 - 14.245 GHz)

MLO

LNA L-band 5-for-3

POWER COMBINER

POWER DIVIDER

FORWARD

RETURN

PARALLELIZED L-Band LTWTAs 8:6

RE

DU

ND

AN

CY

RIN

G

RTN (RX) (1646.5 - 1656.5 MHz)

FWD (TX) (1545 - 1555 MHz)

ECAC 2

ECAC 3

ECAC 1

IF1 (1735 - 1745 MHz)

IF1 (1435 - 1445 MHz)

50MHz

PTWT: 100W

PARALLELIZED Ku-Band LTWTAs 7:5

CHANNELIZATION (Programmable SAW Filter) 5-for-3

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

CHANNELIZATION (Programmable SAW Filter) 5-for-3

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

UPCON L/Ku

DOCON Ku/L LNA Ku

OMT

L-Band Antenna


HP

OA

1

PTWT: 235W

PTWT: 190W

HP

OA

2

HP

OA

3

RE

DU

ND

AN

CY

RIN

G

HP

OA

2

RE

DU

ND

AN

CY

RIN

GR

ED

UN

DA

NC

Y R

ING



Date: 6/2/2009


Subset PL Accomodation on Luxor Satellite Platform

Accommodation in any candidate LV

Support structurefor reflectorduring launch

Ku-band and TT&C accommodation duringGTO-to-GEO transfer



Date: 6/2/2009


Full Capacity Payload:Repeater mass: 335 kg DC consumption: 5841 W (Psat-4 dB OBO)L-Band antenna

shaped reflector 6 meters diameter

Target platform: TAS Spacebus 4000 B2 platform.

Full Capacity Payload: Key findings



Date: 6/2/2009


Full Capacity Payload Block Diagram

Ku-BandFeeder link

RTN (TX) (12.735 - 12.745 GHz)

FWD (RX) (14.235 - 14.245 GHz)

MLO

LNA L-band 5-for-3

POWER COMBINER

POWER DIVIDER

FORWARD

RETURN RTN (RX) (1646.5 - 1656.5 MHz)

FWD (TX) (1545 - 1555 MHz)

ECAC 2

ECAC 3

ECAC 1

IF1 (1735 - 1745 MHz)

IF1 (1435 - 1445 MHz)

50MHz

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

SAW

PLLPLL

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

SAW

PLL PLL

UPCON L/Ku

DOCON Ku/L LNA Ku

OMT

L-Band Antenna


RED

UN

DAN

CY

RIN

G

x28

CHANNELIZATION (SAW Filter, Bw=1.2MHz) 5-for-3

CHANNELIZATION (SAW Filter, Bw=0.98MHz) 5-for-3

PARALLELIZED Ku-Band LTWTAs 10:8

RED

UN

DAN

CY

RIN

G

PTWT=200W

PTWT=100W

POWER DIVIDER

POWER COMBINER

HPO

As

HPO

As



Date: 6/2/2009


SAMARA Space Segment Overview

SAMARA study defines:satellite constellationground part of the space system (SCC, SOC and TT&C stations)

Space segment identified optioncomposed by at least two geostationary telecommunications satellites as baseline to ensure the ATS/AOC services coverage to the ECAC area.GEOs sats operating in hot redundancysupporting simultaneously the same coverage area with the same services

Each satellite will provide the following mission services:

L band Mobile link: Communication links between satellite and aircraft (uplink and downlink)Ku band Fixed link: Communication links between satellite and ground stations (uplink and downlink)L band Antenna covering ECAC Service area by means of 3 spot beamsEach satellite providing link for TT&C functions .

L band Coverage Ku band Coverage



Date: 6/2/2009


Subset Concept & Development Approach

Space Segment Samara: Development approach:

dedicated, specially-developed mobile communications payload standard spacecraft bus for which a number of off the shelf products exist Ground Control Segment: integration with terrestrial network & potential interoperability with HEO/LEO constellation control centre for high altitude and polar routes

The Iris Subset satellite system:qualification of the ATM SatCom services system validation in all operational conditionsable to ensure qualification of the servicecertification preparationminimum set of elements required to perform the End to End validationPreoperational service

Inherent deployment costs of the GEO Subset:to be used not only for validation purposes, butwill become a first building block of the complete system as an integral part of the operational European ATM System

Iris Subset system preliminary definition:

Space Segment1 GEO dedicated satellite (platform and payload with reduced capacity)Part of Ground Control Segment



Date: 6/2/2009


SAMARA System Deployment Approach

2009 2014 2015 2020

now

First launch

E2E validation and transition to preoperational phase

Full Operational System

TIMEFRAMEDeployment approach in line with SESAR

master plan:SESAR master plan:

R&D: 2013-2018Implementation: 2016-2020Available for Operations: 2019+



Date: 6/2/2009


Conclusions

SAMARA main outcomes: Definition of a satellite-based communication system specifically designed for the provisioning over the ECAC area of satellite based ATS (Air Traffic Service) and AOC (Airline Operational Communication) Air Traffic Communication services Two GEOs satellites

operating in hot redundancysupporting simultaneously same coverage area with the same services.

Two payloads:Subset payload with reduced capacity (pre-operational phase)Full capacity payload for operational phase

Space Segment two steps deployment strategy proposed: 1° step

Delivering a subset satellite system with reduced payload capacity Able to qualify the services, validate the system and to be used as space segment element for the full operational capability.

2° stepDelivering a satellite with full capacity payload full operational capability

Deployment strategy in line with SESAR master plan



Date: 6/2/2009


Way Forward / Main Topics

Way Forward/Main Topics Consolidation of the communication traffic (i.e wxgraph sevice, multicast vsunicast)Consolidation of the link budgets (ie waveform optmization)Complexity of final technical baseline: L-Band antenna sizing and design (e.g. BFN solution/frequency reuse..), Payload architecture, and related budgets (mass, consumption)Schedule and technical coherence and consistency between SESAR and Iris programmes considering the involvement of the Iris stakeholders in the SESAR programreduction of satellite production cost (by analyzing the possibility to produce spare payloads in advance respect to the foreseen launch time)Following the design consolidation, to identify and the satellite elements potentially impacting the overall program schedule interoperability with other satellite communication systems existing (INMARSAT, MTSAT) or not (HEO constellation for north and polar routes)



Date: 6/2/2009


Thanks for your attention !

sat 2 samara system for small geo - esa's artes ... (tx) (12.735 - 12.745 ghz) fwd (rx) (14.235...

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