SpaceWire use on future space systems

Transcription

1 SpaceWire use on future space systems SpaceWire Working Group Meeting N 5 ISAS/JAXA, Japan November 2005 Olivier NOTEBAERT - Data Processing and Advanced Studies High speed data links on recent spacecrafts Needs for high speed data links High speed data links on future missions Olivier.notebaert@astrium.eads.net

2 SpaceWire use on future space systems SpaceWire Working Group Meeting N 5 ISAS/JAXA, Japan November 2005 Olivier NOTEBAERT - Data Processing and Advanced Studies High speed data links on recent spacecrafts Needs for high speed data links High speed data links on future missions Olivier.notebaert@astrium.eads.net

3 High speed data links on recent spacecrafts Rocsat 2 / Theos (export) Small/Medium size (750kg) on LEO Two observation instruments Pan chromatic Telescope (10 Mpix/s 240 Mbps digital) Multispectral camera (5 Mpix/s 60 Mbps digital) Specific high speed links for image data transmission CCD video signals PAN Electronics Video Signal Board and synchro PAN Focal Plan Assembly PAN Video Board PAN Compr. Board n 1 PAN Compr. Board n 2 Image Data Image Data Input I/F PAN Ciphering Formatting High Rate Link TMI XS Electronics Board Video Signal and synchro XS Video Board XS Compr. Board Image Data Input I/F XS Scrambling Output I/F I&Q RF modulation + Emission CCD video signals XS Focal Plan Assembly Secondary Voltage Video CV Board Data Transfer Controller Housekeeping board IPU1 Mass memory SSR 1 IPU2 SSR 2 TMI 1 TMI 2 MILSTD 1553 B DC-Bus Page 3 SpaceWire Data Links and Networks in Space Applications 20/07/2005

4 High speed data links on recent spacecrafts Pleiades (Cnes) Medium size (1500kg) on LEO Two observation instruments with proximity electronics for signal digitalisation Pan chromatic Telescope (58 Mpix/s 690 Mbps) Multispectral camera (14 Mpix/s 172 Mbps) Re-use the SPOT/Helios High Speed Links for image data transmission Detectors PAN (5x) Signal video Power/Clock Video Modules PAN (5x) Control Module XS PAN High Rate Links XS High Rate Links COME (6x) High Rate Link TMI Ciphered TMI Detector XS Signal video Power/Clock Video Module XS Control Module PAN Mass Memory CCSDS TM formatter RF modulation +Emission Instruments Proximity Electronics TMCU TMI MIL-STD-1553B Page 4 SpaceWire Data Links and Networks in Space Applications 20/07/2005

5 High speed data links on recent spacecrafts TerraSAR-X (DLR) Earth observation (DLR) Two spacecrafts system One complex instrument X-Band Synthetic Aperture Radar (SAR) Specific Digital Control Electronic Instrument close loop control P/L data processing and delivery to Solid State Mass Memory (880Mbps on G-link) Instrument Analog & discrete signals Digital Control Electronics Sampling Digitalisation Compression CCSDS formatting HSL 2x880 Mbps Solid State Mass Memory Storage Ciphering Formatting Scrambling Emission X-Band Downlink Unit Page 5 SpaceWire Data Links and Networks in Space Applications 20/07/2005

6 High speed data links on recent spacecrafts Cryosat (ESA) Earth watch Ice thickness survey (polar orbit) Two instruments: SIRAL: SAR/Interferometric Radar Altimeter that measures the ice elevation DORIS: Doppler Orbit and Radio Positioning Integration by Satellite that allows very precise orbit determination Page 6 SpaceWire Data Links and Networks in Space Applications 20/07/2005

7 High speed data links on recent spacecrafts Cryosat (ESA) File and Packet Control (FPC) Interfaces between MMS, UIC, TMF and the Memory Modules Controls the data flow via a Switching Matrix SW handling of files and packets to/from CDMU TM/TC MIL-1553 Mil Bus Controller 'MIC' Memory System Supervisor 'MSS' DC / DC Converter Control Bus Memory Module Power Control Memory Module Control Link (RS232) Data Channel 1 from SIRAL Instrument Data Channel 2 to QPSK-Mod. to Test Interface IEEE 1355 (25 Mbps) IEEE 1355 (25 Mbps) ECL (2 x 50 Mbps) ECL (2 x 50 Mbps) Input-UIC 'UIC' Output-UIC 'TMF' Control Bus File and Packet Controller 'FPC' Communication Switching Matrix 'CSM' Memory Module 'MM0' Memory Module 'MM1' Redundant Function - active and - cold redundant CryoSat Memory Module and Formatting Unit Page 7 SpaceWire Data Links and Networks in Space Applications 20/07/2005

8 High speed data links on recent spacecrafts Rosetta (ESA) Rosetta Mission 10-years long cruise toward comet 67P/Churyumov-Gerasimenko Fly-by at least one asteroid during the cruise phase. In-orbit comet scientific observations during one year down to the comet perihelion Land smoothly on the comet surface a Science Package (named RoLand) for in-situ measurements Launched in 02/2004 Initial scenario with comet Wirtanen and asteroids flybys Page 8 SpaceWire Data Links and Networks in Space Applications 20/07/2005

9 High speed data links on recent spacecrafts Rosetta: On board communications Standard Avionics Command Control on OBDH Remote Terminal Units on OBDH with discrete links to instruments (11 P/L instruments) IEEE 1355 serial data link between the different data processing nodes and the Solid State Mass Memory 2 P/L Instruments (VIRTIS@400Kbps, OSIRIS@4Mbps) Navigation camera 4 Avionics processor modules (5Mbps, redounded) Redounded link to Transfer Frame Generator for telemetry Mass memory access with File management System Page 9 SpaceWire Data Links and Networks in Space Applications 20/07/2005

10 High speed data links on recent spacecrafts Rosetta (ESA) 1355 (SpaceWire) links Page 10 SpaceWire Data Links and Networks in Space Applications 20/07/2005

11 High speed data links on recent spacecrafts Mars Express (ESA) Mars exploration 6 months cruise to Mars followed by planetary observation from orbital position First contribution of the European nations to Mars exploration High Resolution stereoscopic Camera producing 25Mbps of digitalised and compressed data Large re-uses of the Rosetta design with adaptations Soyuz Launch from Baikonur (June 2003) 0 to 2 Kbps S-X Band Uplink Perth 35 m Station Data Downlink 19 to 230 Kbps X Band TM G3-Ub Orbit - Pericentre 260 km Alt. - Apocentre km Alt. - Inclination 86 deg. Lander Ejection Remote Sensing and Lander Relay MAT C Cruise High Resolution Stereoscopic Camera Page 11 SpaceWire Data Links and Networks in Space Applications 20/07/2005

12 High speed data links on recent spacecrafts Planetary exploration: Mars Express Processed image from the Mars express High Resolution Stereoscopic Camera Page 12 SpaceWire Data Links and Networks in Space Applications 20/07/2005 ESA

13 High speed data links on recent spacecrafts Venus Express (ESA) Venus Exploration 5 months cruise to Venus 5 days to manoeuvre into its operation orbit, looping around the poles of the planet 2 days* to study the atmosphere, the plasma environment, and the surface of Venus in great detail 7 Instruments Just launched (November 9th) Re-uses the design of Mars express with adaptations * 2 days on Venus = 500 Earth days! Page 13 SpaceWire Data Links and Networks in Space Applications 20/07/2005

14 High speed data links on recent spacecrafts Summary Missions Payload Data Data links Data rate Number (without redundancies) ROCSAT 2 THEOS 300 Mbps LVDS 300 Mbps 3 (Instruments data) Pleïades 860 Mbps LVDS 200 Mbps 13 (Instruments data) TerraSAR-X 880 Mbps Glink 880 Mbps 1 (SAR Instrument) CRYOSAT 25 Mbps 1355 (SpaceWire) 25 Mbps 1 + redundant (Siral instrument) Rosetta 10 Mbps 1355 (SpaceWire) 10 Mbps 2 payload instruments (VIRTIS + OSIRIS) 1 AOCS sensor (navigation camera) Mars Express 25 Mbps 1355 (SpaceWire) 25 Mbps 2 Payload instruments (HRSC + OMEGA) 1 AOCS sensor (StarsTracker) Venus Express 10 Mbps 1355 (SpaceWire) 10 Mbps 2 payload instruments (VIRTIS + VMC) 1 AOCS sensor (StarsTracker) Page 14 SpaceWire Data Links and Networks in Space Applications 20/07/2005

15 SpaceWire use on future space systems SpaceWire Working Group Meeting N 5 ISAS/JAXA, Japan November 2005 Olivier NOTEBAERT - Data Processing and Advanced Studies High speed data links on recent spacecrafts Needs for high speed data links High speed data links on future missions Olivier.notebaert@astrium.eads.net

16 The need for High Speed data-links General trend for future missions New missions call for new requirements Robotics, Autonomy, Security, formation flying New instruments technology generates more on-board data (and TM rates cannot increase accordingly) SW development techniques raises CPU use & data volumes General increase of on-board data processing needs (performance, volumes and transfer rates) Need for overall budget reductions Power consumption reduction Mass and Volume reduction Operational costs: reduction of the satellites dependence beside ground (i.e. mission autonomy) Manufacturing delay reduction (parallel development, AIT) Costs Technology upgrade enforcing re-usable solutions Page 16 SpaceWire Data Links and Networks in Space Applications 20/07/2005

17 The need for High Speed data-links Advanced studies in support to future applications Advanced studies Aurora Avionics Architecture System Definition (A3SysDef) Payload Data Processing Architectures (PaDaPAr) Generic Architecture for Mass Memory Access (GAMMA) Distributed Core SW (DISCO) Page 17 SpaceWire Data Links and Networks in Space Applications 20/07/2005

18 Aurora Avionics Architecture System Definition Context for Planetary Exploration Missions ESA Interplanetary Missions Cosmic Vision programme Aurora programme Technology Reference Missions Cornestone missions Flexible missions Flagship missions Arrow missions Jupiter MicroSat Explorer Programme Rosetta Orbiter Lander BepiColombo Mars Express Orbiter Lander Venus Express ExoMars Orbiter Descent Module Rover Mars Sample Return Earth re-entry Vehicle Demonstrator Mars Aerocapture Demonstrator Mars micromissions JMO 1 JMO 2 JMO 3 JMO 4 JMO 5 JMO 6 Venus probes Mercury Polar Orbiter (MPO) Mercury Magnetospheric Orbiter (MMO ISAS) Mercury Surface Element (MSE) Orbiter Descent Module Mars Ascent Vehicle (MAV) Earth Re-entry Capsule (ERC) In-Situ Resource Utilisation Moon landing Advanced Mars missions Page 18 SpaceWire Data Links and Networks in Space Applications 20/07/2005

19 Aurora Avionics Architecture System Definition Study Objective To define an avionics reference architecture suitable to support different Mars exploration missions and vehicles Taking into account Bepi-Colombo pre-development assets (Highly Integrated Control and Data System-HICDS) Based on a core of mission independent functions Consistent with the communication standardisation (CCSDS/SOIS) Able to ease the integration of new technology items during the long time frame of the Aurora Programme Page 19 SpaceWire Data Links and Networks in Space Applications 20/07/2005

20 Aurora Avionics Architecture System Definition Main User Requirements & Design Drivers Autonomy due to long signal round-trip duration Variable TM and TC bit rate Power minimisation Fail-op capability Extended thermal range Radhard components Mission critical phases Variable distance from the Sun Harsher environment Large distance from the Earth Interplanetary mission Unknown conditions Reprogrammability Design robustness On-board autonomy Variable distance from the Earth Long cruise duration Short launch windows Multistage design Dormant modes High reliability Long lifetime for items subject to wearout Spare policy Maintenability Inter-module interfaces Dormant modes Resource sharing Page 20 SpaceWire Data Links and Networks in Space Applications 20/07/2005

21 Aurora Avionics Architecture System Definition Functional Architecture and Performance Requirements Very large scale of functions and performances We can define generic data processing functions Communications (on-board, between spacecrafts, with ground) Command and Control Failure Detection Isolation and Recovery Autonomy Need to cope with different properties Wide range of spacecrafts bus and instruments performances Reliability, Availability, Safety issues Operational and maintenance requirements Mission profile (Technology constraints, Qualification levels ) MODULAR ARCHITECTURE Need for a scalable set of HW and SW building blocks interconnected on a flexible architectural system Page 21 SpaceWire Data Links and Networks in Space Applications 20/07/2005

22 Aurora Avionics Architecture System Definition Constraints Harsh physical environment (Radiations, Mechanic, Thermic ) Induces high costs for development and qualification programs Mission and phase dependant (Launch, Orbital, Deep space, landing ) Limited resources in space for embedded electronics Communication Link (rates and delays) Power budget (electrical and propulsion) Mass and volume (launch cost, life-time ) Fast evolution of the technologies induces obsolescence risks Evolution of systems needs for the development of new functions and performance range EVOLUTIVE TECHNOLOGY Need to focus the necessary development efforts on a limited set of standardised solutions Page 22 SpaceWire Data Links and Networks in Space Applications 20/07/2005

23 Payload data processing architecture PaDaPAr Study overview Study overview Functional analysis of current and future P/L architecture Definition of typical generic functional architecture versus instruments performance requirements Definition of typical building blocks (toolbox) Benchmark the toolbox on current/future missions Instrument Processing Unit Data Storage Unit Instrument Analog HSL Amplification Digitalisation Processing Compression Storage Ciphering Formatting Scrambling HSL Emission TM Example of a typical High Performance Instrument On-board Data communication chain Page 23 SpaceWire Data Links and Networks in Space Applications 20/07/2005

24 Payload data processing architectures Modular functional architecture Performance oriented architecture Independent instruments data processing units chains Full availability of SPW bandwidth through Direct interfaces to Mass Memory for high rate science data Instrument control through system bus and Remote Terminal Units (RTU) Instrument electronics Sensors Mechanisms Thermal Instrument Data Processing Unit Control & Monitoring drivers High rate Digital High I/Frate Digital I/F Low rate Digital LowI/Frate Digital - LowI/F rate Discrete Digital - I/F Interface Discrete - Interface Discrete Interface Mass Memory Unit RTU electronics System bus OBMU TFG Spacecraft Data Processing Unit Recommended for high data processing requirements on P/L Page 24 SpaceWire Data Links and Networks in Space Applications 20/07/2005

25 Payload data processing generic architectures Modular functional architecture Resource optimisation oriented architecture Instrument pre-processing chains connected to SpaceWire Network Share of common data processing functions and resources Lower number of nodes and links variants Can be combined with platform avionics resources Shared DPU Instrument electronics First-stage Data Processing Sensors Mechanisms Thermal Control & Monitoring drivers Remote Terminal Digital Interface Digital (Spacewire) Interface (Spacewire) Data Processing Unit SpaceWire Routing unit Mass Memory Unit To/from S/C Platform To TFG Recommended for multi instruments P/L and medium data processing requirements Page 25 SpaceWire Data Links and Networks in Space Applications 20/07/2005

26 Generic Architecture for Mass Memory Access (GAMMA) Concept overview Distributed architecture for data storage management Several memory users (Calculators, instruments, ) Several memory modules Manage concurrent data accesses Protect transactions Ensure data consistency Virtual Memory Management Logical partitions can be composed of several physical storage areas. The memory mapping is transparent to the applications. Increase security Increase maintainability Support transparent reconfiguration Optimize performance User Memory FPGA 1 Memory User FPGA 42 Partition a x y b c z User FPGA 1 User Router FPGA 2 Memory User FPGA 3 Memory modules a x y b c z M 1 M 2 M 3 Page 26 SpaceWire Data Links and Networks in Space Applications 20/07/2005

27 Generic Architecture for Mass Memory Access (GAMMA) GAMMA Implementation AP 1 User AP 2 AP n 3 FMS libraries included: ERTFS PRBFS RAWFS Memory Module Data Storage Pure Software FMS Services Pure Hardware MM FMS Services MM Primitives Software Stub MM Primitives Hardwired functions Connection Services SpaceWire IP + drivers Connection Services SpaceWire IP SpaceWire network Page 27 SpaceWire Data Links and Networks in Space Applications 20/07/2005

28 Generic Architecture for Mass Memory Access (GAMMA) GAMMA prototype Demonstrator on a representative environment based on five identical commercial FPGA boards 3 LEON2 users at 40 MHz 2 Memory Modules SpaceWire network: Over 200 Mbps 2 SpaceWire interfaces per board to test concurrent accesses. RS232 interfaces 2xSUBD9 (SpW) Reset buttons 2xDB9 (RS232) SpW router SpW SpW SpW SpW SpW SpW SpW SpW CPCI PC board (gamma2) Linux PC (gamma1) DSU DSU DSU DSU DSU 6U GR-CPCI-XC2V boards with GR-CPCI-SER2-SPW2 interface LAN Page 28 SpaceWire Data Links and Networks in Space Applications 20/07/2005

29 Central Engineering - Data-processing and Software Division (AOE7) Generic Architecture for Mass Memory Access (GAMMA) GAMMA prototype Demonstrator on a representative environment based on five identical commercial FPGA boards 3 LEON2 users at 40 MHz 2 Memory Modules SpaceWire network: Over 200 Mbps 2 SpaceWire interfaces per board to test concurrent accesses. Now operational at ESA/ESTEC premises Page 29 SpaceWire Data Links and Networks in Space Applications 20/07/2005

30 Generic Architecture for Mass Memory Access (GAMMA) SpaceWire network data rates Data rates result (Mbps) Useful data rate link 1 to link 2 link 2 to link 1 link 1 to link 2 & link 2 to link 1 transmission rate 78,08 77,76 37,2 66,72 global board rate 156,16 155,52 207,84 Raw data rate link 1 to link 2 link 2 to link 1 link 1 to link 2 & link 2 to link 1 transmission rate 99, , ,616 85,4016 global board rate 199, , ,0352 Page 30 SpaceWire Data Links and Networks in Space Applications 20/07/2005

31 Distributed SW application Distributed Core Software (DISCO) Objective Development of a core software for complex payload requiring distributed processing Study plan Analysis of future payload systems and definition of a reference mission requiring distributed processing. Specification and development of a Space-Oriented Middleware prototype Evaluation and refinement of the middleware prototype in the context of the reference mission, raising it to the level of a product. Implementation baseline on SpaceWire network Page 31 SpaceWire Data Links and Networks in Space Applications 20/07/2005

32 SpaceWire use on future space systems SpaceWire Working Group Meeting N 5 ISAS/JAXA, Japan November 2005 Olivier NOTEBAERT - Data Processing and Advanced Studies High speed data links on recent spacecrafts Needs for high speed data links High speed data links on future missions Olivier.notebaert@astrium.eads.net

33 High speed data links on future missions Bepi-Colombo mission characteristics Mercury observation Composite vehicle built through European-Japanese cooperation Main Modules: MPO & MMO Mercury Planetary Observer (ESA) Mercury Magnetospheric Orbiter (JAXA) 5 to 6 years long complex cruise phase including Moon, Venus and Mercury Fly-by s. Multiple instruments for data collection in several scientific areas Launch ~2012 Trajectory correction Mercury flyby (x 2) SEPM jettison MOI M e r c u r y Trajectory correction MPO orbit CPM jettison Insertion orbit Conjunction S U N Thrust arcs (after Venus) Opposition Coast arc Venus Venus flyby (x 2) Thrust arc (before the Moon) Trajectory correction Lunar flyby Moon Launch and early operations The Earth Bepi-Colombo initial mission scenario Trajectory correction Page 33 SpaceWire Data Links and Networks in Space Applications 20/07/2005 Earth flyby Coast arc

34 High speed data links on future missions Bepi-Colombo mission characteristics Key Issues for Bepi-Colombo avionics architecture Complex P/L which includes 11 instruments (50Mbps overall science data rate and 115Kbps C&C). High level of autonomy (mission and FDIR) Reliability of inter-modules communication links at separation time Centralised versus decentralised architecture Technology trade-off SpaceWire network or direct links? P/L Command and Control dedicated links or over science data links? System on a Chip Computer core or reuse from flying and ongoing programmes? Bepi-Colombo initial mission scenario Page 34 SpaceWire Data Links and Networks in Space Applications 20/07/2005

35 High speed data links on future missions Bepi-Colombo MPO proposed data links architecture Platform Central Computer (OBMU) Platform C&C via 1553B and direct I/O system Repeaters adapted from Ariane 5 Payload Data Processing (PDPU) science data acquisition On-board processing Compression and storage PacketWire link to TM P/L data interface with SpaceWire links Network with router for low-rate instruments Direct links for High rate instruments P/L C&C over SpaceWire links Payload (11 instruments) SpaceWire SpaceWire Platform I/O SpaceWire BC 3 (OBMU) PDPU Bus I/F Sys_MM SSMM 8 Gb TFG Sci_SSMM256 SSMM Gb Memory Processor(ERC32) SpaceWire SpW router System bus (MIL -STD-1553B) X-TX Ka-TX PacketWire Page 35 SpaceWire Data Links and Networks in Space Applications 20/07/2005

36 High speed data links on future missions GAIA mission characteristics and main drivers Astronomy science mission Lagrangian L2 point orbital position Very high stability and fine pointing Optical instrument with high data processing capability (for science algorithms) Launched foreseen in 2012 Key drivers Modularity Ease of AIT & operations Performance of the video processing chain Performance of Attitude and Orbit control Main data processing challenges Video processors (~1000Mips) On-board data reduction and storage High rates of data from P/L instrument Page 36 SpaceWire Data Links and Networks in Space Applications 20/07/2005

37 High speed data links on future missions GAIA proposed data links architecture Payload Module Video Processing Units (VPU) Optical Data Front end processing All data on SpaceWire direct links Payload Data Handling (PDHU) science data acquisition, final, processing and storage SpaceWire links to TM through CDMU internal Router Service Module Central Distribution and Monitoring (CDMU) Routing of SPW P/L science data to TM Link with I/O system through SpaceWire Command control Avionics system through SVM 1553 bus Payload through Payload 1553 bus TM TC Optical terminal Payload Module I/O EIU TT&C AOCS Service Module VPU VPU VPU VPU VPU VPU VPU HK TM data storage (8 Gb) Power Payload bus Bus I/F Bus I/F SVM bus PDHU Science data storage (700 Gb) Synch CDU Synch CDMU µpropulsion SpaceWire MIL-STD-1553 Page 37 SpaceWire Data Links and Networks in Space Applications 20/07/2005

38 High speed data links on future missions Other future missions calling for SpaceWire networks Mars Rover & Pasteur Payload (Exomars ~2012) The Rover payload (Pasteur package) integrates 8 instruments, 5 for sample observation and 3 for environment observation. A high level of autonomy and a large computing power for data/image compression is required for the platform. Sharing of resources between Pasteur and Rover is expected (computing, mass memory) SolO (Solar Orbiter ~ 2014) 14 instruments foreseen with a huge volume of raw data produced Need for very efficient data reduction techniques as well as autonomous observation management. A potential late adaptation of on-board algorithms has to be considered, claiming for a flexible approach. Bepi-Colombo initial mission scenario Page 38 SpaceWire Data Links and Networks in Space Applications 20/07/2005

39 High speed data links on future missions Conclusion for SpaceWire application SpaceWire provides a standard solution supporting the need for high data processing performance on future spacecrafts Standard high speed data link for acquisition of a large range of payloads Simple devices access with RMAP protocol CCSDS TM/TC packet routing between intelligent terminals (e.g. complex instruments, star-trackers ) Solution for on-board Network Optimisation of on-board resources Infrastructure for future on-board data processing performance increase Contributes to the development of generic data processing architectures and Building Blocks Page 39 SpaceWire Data Links and Networks in Space Applications 20/07/2005