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SpaceWire Driven Architecture for the ASTRO-H Satellite Masanobu Ozaki (ISAS/JAXA), T. Takahashi, M. Kokubun, T. Takashima, H. Odaka (ISAS/JAXA), M. Nomachi (Osaka Univ.), T. Yuasa (UTokyo), I. Fujishiro (SHIMAFUJI), T. Tohma (NEC), H. Hihara (NEC-Toshiba space), K. Masukawa (MHI) ASTRO-H • Japanese 6th X-ray astronomy space observatory • 2014 launch (scheduled) • Multi-country mission (Japan, US, Nederland, Canada, France, ...) 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 2 ASTRO-H (2) • Multiple and distributed payloads • Low budget, short term construction -> a new standard of – network protocol – Router – Standard computer architecture – Standard I/O module with SpW 2010-06-22/23/24, ISC2010 Star trackers SXS Extensible Optical Bench SpW driven architecture for the ASTRO-H satellite (M. Ozaki) SXI L = 14 m HXI 3 Architecture Requirements • Data rate: 12 Gb/day (140 kbps) at satellite output • Communication among instruments are 10100 times faster than that, however. -> Reliable network topology is a key. 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 4 Network Topology (physical) • Twin star-topology networks – No packet collision between channels Data Handling network Telemetry Command Interface Module TCIM (No Time Packet Propagation) X SpW router SpW router SMU Satellite Management Unit AOCP 2010-06-22/23/24, ISC2010 SpW router Attitude and Orbit Control Processor SpW router HXI-DE Attitude Control network DR SXS-DE SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 5 Network Topology (logical) • Tree-topology network – Communications are limited between the parent and each child nodes. DR Telemetry Command Interface Module TCIM (Ground Stations) AOCP Attitude and Orbit Control Processor SMU Satellite Management Unit SXS-DE HXI-DE 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 6 Protocols • Everything is on RMAP – CCSDS space packets on RMAP space – PIM (Peripheral Interface Module: ISAS traditional communication I/F) protocol on RMAP/SpW – Time slot bases: SMU controls everything • SMU sends out space packet commands to payloads • SMU collects space packet telemetry or raw data from payloads – DR delegates SMU in case of space packet telemetry 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 7 Components: SpaceCube • Computer architecture with SpW I/F – open architecture based on T-Engine – SpW connection – source-code level compatibility in the application layer between different implementation – small, low mass, low power consumption and low cost • Developed by SHIMAFUJI (commercial base), NEC and MHI (flight models) 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 8 Components: peripherals • Embedded RMAP devices – I/F ASIC by NEC – Standard I/O boards with FPGAs by MHI • Usable as memory or memory-mapped I/O devices on SpW network without CPU 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 9 Development Supports • GSE – SMU simulators using SHIMAFUJI SpaceCube (by NEC) – SpW <-> TCP/IP bridges (by T. Yuasa) – SpW test lab. supported by the community (at SHIMAFUJI office) 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 10 Development Supports (2) • Community – Front runners in universities and companies help the followers regular basis. – Mainly by email/IT based supports, sometimes by training courses. 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 11 Conclusion • ASTRO-H is a SpW-based space observatory. • The network topologies are configured to keep the throughputs as fast as possible with limited link speed. • Standardization of components reduces the development costs and period. • Development supports by the project and user community are important keys. 2010-06-22/23/24, ISC2010 SpW driven architecture for the ASTRO-H satellite (M. Ozaki) 12