SAMARA Satellite 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 THALES ALENIA SPACE All rights reserved, 2/27/2008, Thales Alenia Space
Contents Page 2 1. Highlights and Background 2. SAMARA study Activities Overview Requirements and Drivers Main Outcomes and Key findings Development and Deployment Approach 3. Conclusions 4. Way forward
Overview of the Activities & Background Page 3 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 Alenia Space 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.
Need of a Satellite Dedicated System Page 4 Existing systems providing satellite communications for the ATM services GEO: 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 services to 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.
SAMARA Study (1/2) Page 5 SAMARA mission: to provide alternative comms means to carry Air Traffic Communications by satcom system Baseline: full coverage over the ECAC European Area Options: 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 studies Target of a low cost new avionic satisfying the availability requirement for the safety of life operations, SESAR time line
SAMARA Study (2/2) Page 6 Assessment of satellite system user requirements in the context of the SESAR initiative Trade-offs between different system architecture options Definition of System Operational Concept Satellite System Architecture definition definition of preliminary Satellite System Architecture with aeronautical active antennas trade 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 subset Payload with full capacity to be used for operational systems Certification and liability issues analysis SAMARA Business Case and Service Model
Analyses of Input Requirements (1/2) COVERAGE REQ.: Subset Mobile and Fixed Link Requirement Compliance over ECAC Boundary Page 7 Mobile Fixed B C A 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 subset Minimum 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 full Minimum number of carriers : 59 Assuming the 3 spot beams originally used in Task 2, the distribution among the beams is 13-32-14 2 carriers per beam of 16kbps, 2 carriers per beam of 32kbps and all other carriers of 64kbps
Analyses of Input Requirements (2/2) Page 8 Tot. no of carriers FWD To SB A: 5 To SB B: 12 To SB C: 5 Scenario subset RTN From SB A: 6 From SB B: 13 From SB C: 6 FWD To SB A: 13 To SB B: 32 To SB C: 14 Scenario full RTN From SB A: 12 From SB B: 41 From SB C19 Carrier data rate 3 carrier rate types: 16 kbps, 32 kbps 64 kbps 3 carrier rate types: 12.5 kbps 25 kbps 50 kbps 3 carrier rate types: 16 kbps, 32 kbps 64 kbps 3 carrier rate types: 12.5 kbps 25 kbps 50 kbps Total BW (MHz) 1.94 2.10 5.19 5.04 Ant. Polarization U/L: LH D/L: RHCP U/L: RHCP D/L: LV U/L: LH D/L: RHCP U/L: RHCP D/L: LV Min. EIRP (dbw) 41.8 31 41.8 31 Min G/T (db/k) -1.0-1.0-1.0-1.0 C/I (db) 14 target 18 18 target 20 14 target 18 18 target 20 Lifetime (Years) 15
SAMARA Study Outcomes for In Orbit Design Page 9 User link at L band characterised by: multi beams coverage high EIRP demanding G/T Low cost approach Dimensioning and design of L band antenna beams generation approach reflector dimensions Payload drivers architecture consumption, dissipation and mass Two payload options: Payload with reduced capacity Payload with full capacity Small/Medium GEO platforms A. OHB Luxor for reduced capacity payload B. Spacebus 4000 B2 for full capacity
Subset Payload: Key findings Page 10 Subset Payload: Repeater mass: 270 kg DC 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.
Subset Payload Block Diagram Page 11 ECAC 2 ECAC 3 RTN (RX) (1646.5-1656.5 MHz) LNA L-band 5-for-3 POWER COMBINER IF 1 (1435-1445 MHz) PARALLELIZED Ku-Band LTWTAs 7:5 P TWT: 100W RETURN ECAC 1 RTN (TX) (12.735-12.745 GHz) MLO 50MHz Ku-Band Feeder link PARALLELIZED L-Band LTWTAs 8:6 FWD (TX) (1545-1555 MHz) REDUNDANCY RING CHANNELIZATION (Programmable Filter) 5-for-3 POWER DIVIDER FWD (RX) (14.235-14.245 GHz) L-Band Antenna CHANNELIZATION (Programmable Filter) 5-for-3 UPCON L/Ku REDUNDANCY RING HPOA 3 OMT HPOA 1 DOCON Ku/L LNA Ku PTWT: 235W PARALLELIZED L-Band LTWTAs 4:3 HPOA 2 REDUNDANCY RING IF 1 (1735-1745 MHz) FORWARD HPOA 2 REDUNDANCY RING PTWT: 190W
Subset PL Accomodation on Luxor Satellite Platform Page 12 Accommodation in any candidate LV Ku-band and TT&C accommodation during GTO-to-GEO transfer Support structure for reflector during launch All rights reserved, 2/27/2008, Thales Alenia Space
Full Capacity Payload: Key findings Page 13 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 Block Diagram Page 14 L-Band Antenna ECAC 2 ECAC 3 RTN (RX) (1646.5-1656.5 MHz) LNA L-band 5-for-3 CHANNELIZATION ( Filter, Bw=0.98MHz) 5-for-3 POWER COMBINER IF 1 (1435-1445 MHz) UPCON L/Ku PARALLELIZED Ku-Band LTWTAs 10:8 REDUNDANCY RING HPOAs RETURN ECAC 1 RTN (TX) (12.735-12.745 GHz) P TWT=100W MLO 50MHz OMT Ku-Band Feeder link POWER COMBINER PARALLELIZED L-Band LTWTAs 28:24 POWER DIVIDER CHANNELIZATION ( Filter, Bw=1.2MHz) 5-for-3 POWER DIVIDER FWD (RX) (14.235-14.245 GHz) FWD (TX) (1545-1555 MHz) DOCON Ku/L LNA Ku HPOAs x28 REDUNDANCY RING IF 1 (1735-1745 MHz) FORWARD P TWT=200W
SAMARA Space Segment Overview Page 15 SAMARA study defines: satellite constellation ground part of the space system (SCC, SOC and TT&C stations) Space segment identified option composed 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 redundancy supporting 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 beams Each satellite providing link for TT&C functions. L band Coverage Ku band Coverage
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 conditions able to ensure qualification of the service certification preparation minimum set of elements required to perform the End to End validation Preoperational service Inherent deployment costs of the GEO Subset: to be used not only for validation purposes, but will become a first building block of the complete system as an integral part of the operational European ATM System Page 16 Iris Subset system preliminary definition: Space Segment 1 GEO dedicated satellite (platform and payload with reduced capacity) Part of Ground Control Segment
SAMARA System Deployment Approach Page 17 TIMEFRAME Deployment approach in line with SESAR master plan: SESAR master plan: R&D: 2013-2018 Implementation: 2016-2020 Available for Operations: 2019+ E2E validation and transition to preoperational phase Full Operational System First launch now 2009 2014 2015 2020
Conclusions Page 18 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 redundancy supporting 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 step Delivering a satellite with full capacity payload full operational capability Deployment strategy in line with SESAR master plan
Way Forward / Main Topics Page 19 Way Forward/Main Topics Consolidation of the communication traffic (i.e wxgraph sevice, multicast vs unicast) 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 program reduction 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)
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