Reconfigurable Communication Equipment on SmartSat-1 Nozomu Nishinaga Makoto Takeuchi Ryutaro Suzuki Smart Satellite Technology Group Wireless Communications Department National Institute of Information and Communications Technology Nishinaga No.
Download ReportTranscript Reconfigurable Communication Equipment on SmartSat-1 Nozomu Nishinaga Makoto Takeuchi Ryutaro Suzuki Smart Satellite Technology Group Wireless Communications Department National Institute of Information and Communications Technology Nishinaga No.
Reconfigurable Communication Equipment on SmartSat-1 Nozomu Nishinaga Makoto Takeuchi Ryutaro Suzuki Smart Satellite Technology Group Wireless Communications Department National Institute of Information and Communications Technology Nishinaga No. 1 B199/MAPLD2004 Outline Motivation SmartSat-1 Reconfigurable Communication Equipment Onboard software defined radio Heavy Ion test results of Vertex II pro Conclusion Nishinaga No. 2 B199/MAPLD2004 Motivation For next-generation satellite communications: bandwidth expansion expected (HIGH data rate: more than 1.5 Mbps) To expand bandwidth: Higher carrier frequency and Regenerative relay + Onboard switching Issue: Increased carrier frequency (ka band and above) requires high rain margin Solution: Regenerative relaying by installing multi-rate moderator/demodulator on communication satellites Nishinaga No. 3 B199/MAPLD2004 Bent-pipe relay system RF signal RF signal Low Noise Amplifier RX Antenna IF signal RF signal Down Converter UP Converter Local Oscilator Local Oscilator RF signal High Power Amplifier TX Antenna Base station Base station Bent-pipe, through repeater, or frequency conversion (dumb hub) Most commercial communication satellite systems have this kind of repeater All signals received at the satellite are amplified and sent back to base station Supports Point-to-Point link Nishinaga No. 4 B199/MAPLD2004 Regenerative Relay + Onboard Switching Baseband Switch Onboard Demodulator Onboard Modulator IF signal RF signal Low Noise Amplifier Down Converter UP Converter RF signal RX Antenna RF signal IF signal High Power Amplifier RF signal Local Oscilator Local Oscilator TX Antenna Base station Base station All signals received at the satellite are demodulated, switched, re-modulated and sent back to the base station (terminated in L2). Full mesh network (Multi points-to-Multi points). 3-dB power gain Boost the total system bandwidth by the statistical multiplexing effect by using the onboard baseband switch Flexible link design Already been tested and demonstrated with experimental satellites Still few commercial satellites with this type of transponder Nishinaga No. 5 B199/MAPLD2004 Issues (1) Recent communication satellite system: 10-20-year lifetime Cannot comeback from Geostational orbit Cannot upgrade communication system installed in satellites Flexible link design, but system not flexible IMAGINE the communication systems of 20 years ago! Acoustic coupler+RS232C+HDLC? (300 bps) Balefire? (1 bpd?) Nishinaga No. 6 B199/MAPLD2004 Issues (2) Multi rate DEM MOD for 128kbps DEM for 128kbps Multi rate MOD Multi rate DEM MOD for 256kbps DEM for 256kbps Multi rate MOD Multi rate DEM MOD for 512kbps DEM for 512kbps Multi rate MOD Multi rate DEM MOD for 1.5Mbps DEM for 1.5Mbps Multi rate MOD Multi rate DEM MOD for 10Mbps DEM for 10Mbps Multi rate MOD Multi rate DEM MOD for 45Mbps DEM for 45Mbps Multi rate MOD Multi rate DEM MOD for 100Mbps DEM for 100Mbps Multi rate MOD Multi rate DEM Traditional method Many fixed-rate MODEMs Huge redundant system Test procedure complicated Heavy payload Nishinaga IF Switch Matrix Multi rate MOD IF Switch Matrix DEM for 64kbps IF Switch Matrix IF Switch Matrix MOD for 64kbps Software-Defined-Radio method Many multi-rate MODEMs Simple redundant system Test procedure very simple Payload not so heavy No. 7 B199/MAPLD2004 Objectives 1. Technological demonstration of onboard software-defined radio • • • Versatile onboard modulator and demodulator (MODEM) with SDR technique application proof of highly functional onboard transponder application proof for next-generation communication satellite Adaptable to latest communications technology with flexible link design and high data rate 2. Gracefully degradable equipment with functional redundant technique • • • • Reliability enhancement of onboard MODEM with software-defined radio flexibility Paradigm shift from dual or triple modular redundant system with exclusive equipment to functional redundant system with versatile equipment Introducing a soft fault decision process (multilevel, not “hard decision”) for extending mission equipment lifetime (autonomous fault decision and resource evaluation) Reducing redundancy by assigning a light load to partially “out of order” equipment with taking account of a required computational complexity disequilibrium in an onboard MODEM Nishinaga No. 8 B199/MAPLD2004 SmartSat-1 Twin 150-kg class experimental satellites [ SmartSat-1a ] Missions: CME/plasma cloud observation Orbital maintenance experiment Optical inter-satellite communication experiment Reconfigurable communication experiment Launch: FY2008 Orbit: Geostational transfer orbit (piggy-back launch) [SmartSat-1b ] Nishinaga No. 9 B199/MAPLD2004 Reconfigurable Communication Equipment Onboard software-defined radio (OSDR), IF components, RF components, and two antennas for reception and transmission Weight: 16 kg (TBD); Power consumption: 80 W (TBD) Nishinaga No. 10 B199/MAPLD2004 OSDR: Breadboard model 1st generation 2nd generation Designed and manufactured in 2002 Dual XCV100s+ 1 XCV 100 (for controller) Normal operation mode (full spec. filtering) and degeneracy mode (half throughput) Nishinaga Designed and manufactured in 2004 No. 11 B199/MAPLD2004 The second generation OSDR BBM Dual FPGA banks (1,2,3 and 4,5,6) , each bank includes 3 2VP4s. The Control FPGA will be replaced with an Anti-fuse type FPGA. Triple modular redundancy mode and daisy chain mode Nishinaga No. 12 B199/MAPLD2004 Onboard SDR Multi-rate and Multi-modulation support 2 kbps–1 Mbps QPSK (16QAM) Forward error correction not implemented yet Two service classes Highly reliable operation (triple modular redundancy mode) High-throughput operation (daisy-chain mode) (Degeneracy mode) New function loadable New configuration data uploadable by itself Readback inspection Nishinaga No. 13 B199/MAPLD2004 Triple modular redundancy mode TMR voter implemented on controller FPGA Nishinaga No. 14 B199/MAPLD2004 Daisy chain mode Nishinaga No. 15 B199/MAPLD2004 Degeneracy mode Modulation and encoding require lower computational complexity than demodulation and decoding, respectively. A bank including a failure FPGA is assigned a modulation/encoding function. Nishinaga No. 16 B199/MAPLD2004 Readback issues System requirements: 3.0M-bit data for FPGA 18M-bit data for 6 FPGAs Need 54M-bit data for Readback operation (including MSK and RBB) On-the-fly compression/decompression Nishinaga No. 17 B199/MAPLD2004 Radiation test of Virtex II Pro Virtex II pro (XC2VP7-5FG456) Test carried out in November 2003 at TIARA in Takasaki, Japan Heavy Ions (N, Ne, and Kr) Result compared with that of Virtex II. (Gary Swift, Candice Yui, and Carl Carmichael,” SingleEvent Upset Susceptibility Testing of the Xilinx Virtex II FPGA,” MAPLD2002, paper P29) Nishinaga No. 18 B199/MAPLD2004 Radiation test result (1) Block RAM region Cross Section (cm2/bit) 1.E-06 1.E-07 1.E-08 1.E-09 V2-Pro 1.E-10 V2 1.E-11 0 Nishinaga 10 20 30 40 LET(MeV cm2/mg) No. 19 50 60 70 B199/MAPLD2004 Radiation test result (2) Configuration Memory region 1.0E-08 2 Cross Section[cm /bit] 1.0E-07 1.0E-09 1.0E-10 V2-Pro V2 (iMPACT) N Kr Ne V2 (FIVIT) Kr( 35°) 1.0E-11 0 10 20 30 40 50 60 70 2 LET [Mev cm /mg] Nishinaga No. 20 B199/MAPLD2004 Summary Overview and development status of reconfigurable communication equipment on SmartSat-1 Result of Vertex II pro radiation test: No obvious difference performance compared with that of Virtex Issues Configuration data compression Online health checking Nishinaga No. 21 B199/MAPLD2004