GALILEO Workshop, 26.Sep Marco FALCONE GALILEO System Engineering Manager GALILEO Project Office Tel

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1 GALILEO Workshop, 26.Sep.2005 European Space Agency A g ence spatiale européenne ESTEC Postbus NL2200 AG Noordwijk - Keplerlaan - NL 2201 AZ Noordwijk ZH - Tel. (31) Fax (31) Marco FALCONE GALILEO System Engineering Manager GALILEO Project Office Tel Marco.Falcone@esa.int

2 Galileo Programme Motivation and Organisation Galileo Added Value Galileo Development Objectives and Status Conclusion

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4 Both systems GPS and GLONASS developed for military applications although now recognized as dual-use: civil/military. No service guarantees. Complemented with Satellite Based Augmentation systems (SBAS): USA: WAAS Europe: EGNOS Japan: MSAS Elsewhere: planning stage

5 Step 1: EGNOS to provide civil complement to GPS and GLONASS, into operations in 2004 EGNOS EGNOS is an initiative of the European Commission, Eurocontrol and ESA Step 2: 2: GALILEO is is to to achieve European sovereignty and service guarantees through dedicated system under civil control: into operations by by 2008 GALILEO is an initiative of the European Commission and ESA

6 No single State control Modern system, increased # signals and bandwidth, new modulations and spreading codes, improved performance, robustness against interference Intended primarily for civilian applications Built-in Integrity, Safety and Security Built-in Regional and Local components Service guaranteed Fully interoperable with other GNSS components Open for international co-operation 6

7 The European Dimension European Union and European Space Agency European Space and Industrial Policy The International Context Interoperability With GPS (EU-US agreement) With GLONASS (under discussion with Russia) Cooperation with 3rd countries, regional and international organisation Participation (GJU shareholder) China, Israel

8 48 months 24 months 20 years Development and Validation Deployment Operations and Maintenance 1.2 Billion Public 2.2 Billion 1/3 Public, 2/3 Private 220 Million per year Private 1 Test Satellite & 4 Operational Satellites Ground Infrastructure 26 Satellites Ground Infrastructure Routine Operations and Replenishment EC/ESA Joint Undertaking GALILEO Concessionaire / Surveillance Authority

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10 Open Service Commercial Service Safety-Of-Life Service Public Regulated Service Support to Search-and-Rescue Service

11 GALILEO Global Services Open Service Commercial Service Safety of Life Service Public Regulated Service Coverage Global Global Global Global Positioning Accuracy (Horiz, 2 drms, 95%) (Vert, 95%) Timing Accuracy (95%) Integrity Alert Limit Time to Alert Integrity Risk Continuity Risk Service Availability Access Control Certification and Service Guarantees 15m or 24m H 35m V (single frequency) 4m H 8m V (dual frequency) 4m H 8m V (dual frequency) 15m or 24m H 35m V (single frequency) 6.5m H 12m V (dual frequency) 30 ns 30 ns 30 ns 30 ns None None 12m H 20m V 6 s 3.5 x 10-7 / 150 s 20m H 35m V 10 s 3.5 x 10-7 / 150 s 1 x 10-5 / 15 s 1 x 10-5 / 15 s 99.5% 99.5% 99.5% 99.5% Free Open Access None Controlled Access of Ranging Codes and Navigation Data Message Guarantee of Service possible Authentication of integrity information in the Navigation Data Message Build for Certification and Guarantee of Service Controlled Access of Ranging Codes and Navigation Data Message Build for Certification and Guarantee of Service

12 GPS alone vertical positioning single freq. accuracy (95% of the time with a confidence level of 1 sigma) ranges from 12 to 23 m. EGNOS enhances the performance over Europe and also on Africa (due to the ranging information of the GEOs) lowering the accuracy to less than 5m. NOTE: UERE Budget with nominal (not worse case) environment

13 The performances further increases (lowering the accuracy to less than 9m single frequency) adding GALILEO. The EGNOS improvement over Europe in this last case is still noticeable.

14 Protection level Alert Limit Computed navigation solution Alert Limit < Protection Level Alert (Abort Landing) Alert Limit > Protection Level No Alert (Continue Landing) Integrity provides timely warning to the user that the accuracy of the service is not sufficient for the intended application

15 Combined use of the two systems for better performance at user level : Common centre frequencies on L1 and E5a Coordinate Reference Frame Time Reference Frame and Broadcast of GPS- GALILEO Time Offset

16 ARNS Bands ARNS Bands L5 RNSS Bands RNSS Bands E5 L2 E6 E2 L1 E MHz MHz 1214 MHz 1215 MHz 1237 MHz 1260 MHz MHz 1300 MHz 1559 MHz 1563 MHz MHz 1587 MHz 1591 MHz 1610 MHz GALILEO Bands (Navigation) GLONASS Bands (Current & modernized) GPS Bands (Current & modernized) E2-L1-E1 and E5a/L5 are common to GPS Frequency bands for interoperability E2-L1-E1 and E5a/L5 are common to GPS Frequency bands for interoperability RNSS Radio Navigation Satellite Systems ARNS Aeronautical Radio Navigation Systems

17 E5A Signal: Data+Pilot BPSK mod. Rc=10.23 Mcps Rs=50 sps OS/CS Services E5B Signal: Data+Pilot BPSK mod. Rc=10.23 Mcps Rs=250 sps OS/CS/SOL Services E6P Signal: BOCcos(10,5) mod. Rc=5.115 Mcps PRS Service E6C Signal: Data + Pilot BPSK mod. Rc=5.115 Mcps Rs=1000 sps CS Service L1P Signal: BOCcos (15,2.5) mod. PRS Service L1F Signal: Data + Pilot BOC(1,1) mod. Rc=1.023 Mcps Rs=250 sps OS/CS/SOL Services 90x1.023 MHz 40x1.023 MHz 40x1.023 MHz MHz E5 Signal: AltBOC(15,10) mod MHz MHz Frequency (MHz)

18 Walker 27/3/1 plus 3 in-orbit spares (1/plane) Semi-major axis km inclination 56 deg Period: 14 hr 4 min 42 sec Ground track repeat cycle 10 days/17 orbits

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20 GSTB V 1 PROTOTYPING AND EXPERIMENTATION GSTB V IOV SYSTEM TEST RECEIVERS IN-ORBIT VALIDATION FULL OPERATIONAL SYSTEM FULL DEPLOYMENT USER EQUIPMENT

21 GSTB-V2 / A GSTB-V2 / B Lift-off mass 600 kg Lift-off mass 495 kg Power demand 700 W Power demand 760 W Stowed Dimensions Stowed Dimensions: 1.3 m x 1.8 m x 1.65 m m x m x 2.4 m

22 Two experimental satellites under development. The GSTB-V2 is planned to be operated for a period of two years after launch (2006 & 2007) Objectives Secure frequency filing Validate payload technology in orbit (e.g. clocks) Characterise radiation environment Signal characterisation and related receiver performance in combination with environmental effects Currently GSTB-V2/A undergoing final testing at ESA Testfacilities Thermo-Vacuum finalised Vibration Acoustic EMC Launch Dec 2005 on Soyuz from Baikonur

23 GSTB-V2 Experimental Test Receiver Acceptance 7/2005 from Septentrio (B) Currently undergoing extensive testing at ESA with GSTB-V2 Supports GPS L1/L2 support to frequency filing SIS experimentation characterization of SIS, UERE, Clocks, P/L, OD&TS (UERE contrib. and SISA confidence level) (GETR) Antenna from Space Engineering (I)

24 5V Adapt. GPS Antenna LAN Connection GSVF-v2 RF Signal GETR COM Connection Monitor Signal SSN BB COM Connection GETR Control PC Galileo RF Constellation Signal Simulator Digital Oscilloscope Spectrum Analyzer Real-Time Analysis Available for supporting Power Supply 15V AMP Matlab Bitgrabber LAN Connection DataLogger ORUS SW-RX ORUS Control PC Rx development Post-Processing Analysis

25 GSTB V 1 PROTOTYPING AND EXPERIMENTATION GSTB V IOV SYSTEM TEST RECEIVERS IN-ORBIT VALIDATION FULL OPERATIONAL SYSTEM FULL DEPLOYMENT USER EQUIPMENT

26 IOV to address in full Galileo design and development (FOC technical requirements) GOAL: qualification of space, ground and user segment through extensive test Analysis of system performance with the view to refine the system prior to full system deployment Verification of operational procedures Deployment risk reduction Based on manufacturing and deployment of a limited In-Orbit-Validation (IOV) System Configuration: 1 experimental satellite (GSTB-V2) (early version of operational IOV Sat.) 3-4 operation satellites (considered minimum number required) Associated ground (20 GSS, 5 ULS, 2 TTC, 1 GCC) and test user segment IOV Transition to FOC by recurring manufacturing / deployment / integration of IOV system components IOV to enable FOC within defined time and budget requirements

27 3 to 4 SV s Test User Segment for validation of the different Services Galileo IOV Galileo. Experim. OSS Experim. OSS 12 receiver 12 receiver receiver Galileo Sensor Stations Rubidium Rubidium Global Coveragea clock clock 18 to 20 Galileo Sensor Stations (worldwide) 3 ULS Global 2 ULS/TTC Global (collocated ULS/TTC at the same sites) Control Centre (1 site)

28 Definition Phase started in 2000 and was completed in 2003 Mid 2002 SystemPDR was achieved for overall development (Phase B2) Galileo System Test-Bed (GSTB-V1) developed to experiment with Galileo-like processing algorithms based on GPS Observables. Six months of results. The Galileo Development preparatory phase (phase C0) was Kicked-off in December 2003 and concluded in October 2004 with the Galileo Segment PDRs The Galileo Development & Validation phase (CDE1) was kicked-off in December 2004 for a planned duration of 48 months, including 6 months of In Orbit Validation (IOV) (phase E1). Currently Segment D-PDR are being held together with CCBs for the Segment Requirements ITTs for lower level items have been released, proposals have been received and evaluated to a large extent Schedule critical lower level elements haven been kicked-off (e.g. GRC, IPF, ) GSTB-V2 Extended IOT has been kicked-off (incl NW of 13 Sensor Stations) Critical technology developments completed: (i.e clocks Rubidium, H-Maser (1ns in 100min), Satellite Navigation Antenna, GSS Antennas, GSS Receiver PreDev, Simulator ) The GSTB-V2 Satellite development was Kicked-off in July 03 The CDE1 phase will be followed by the full deployment phase (E2) for a planned duration of 24 months

29 GSTB-V2 GSTB-V2 development IOT GSTB-V2 Operations GSTB-V2 Launch Galileo Overall System Phase C0 Galileo CDE1 IOV SEG-PDR S-PCDR S-CDR IOVRR IOVR SS Development Space Segment (SS) DPDR CDR Launches Ground Mission Segment (GMS) GMS Development DPDR CDR QR SAR Ground Control Segment (GCS) GCS Development DPDR CDR QR SAR Test User Segment (TUS) TUS Development DPDR CDR QR AR

30 Further Information