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Nishinaga No. 1 B199/MAPLD2004
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. 2 B199/MAPLD2004
Outline
Motivation SmartSat-1 Reconfigurable Communication Equipment Onboard software defined radio Heavy Ion test results of Vertex II pro Conclusion
Nishinaga No. 3 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
andRegenerative 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. 4 B199/MAPLD2004
Bent-pipe relay system
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
Low NoiseAmplifier
RX Antenna
DownConverter
LocalOscilator
High PowerAmplifier
TX Antenna
UPConverter
LocalOscilator
RF signal RF signal RF signal RF signalIF signal
Basestation
Basestation
Nishinaga No. 5 B199/MAPLD2004
Regenerative Relay + Onboard Switching
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
Low NoiseAmplifier
RXAntenna
DownConverter
LocalOscilator
High PowerAmplifier
TXAntenna
UPConverter
LocalOscilator
RF signal
RF signal RF signal
RF signalIF signal
Basestation
Basestation
OnboardDemodulator
Baseband Switch
OnboardModulator
IF signal
Nishinaga No. 6 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. 7 B199/MAPLD2004
Issues (2)
Traditional method Many fixed-rate MODEMs Huge redundant system Test procedure complicated Heavy payload
IF Sw
itch Matrix
MOD for 64kbps
MOD for 128kbps
MOD for 256kbps
MOD for 512kbps
MOD for 1.5Mbps
MOD for 10Mbps
MOD for 45Mbps
MOD for 100Mbps
IF Sw
itch Matrix
DEM for 64kbps
DEM for 128kbps
DEM for 256kbps
DEM for 512kbps
DEM for 1.5Mbps
DEM for 10Mbps
DEM for 45Mbps
DEM for 100Mbps
IF Sw
itch Matrix
Multi rate MOD
IF Sw
itch Matrix
Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Multi rate MOD Multi rate DEM
Software-Defined-Radio method Many multi-rate MODEMs Simple redundant system Test procedure very simple Payload not so heavy
Nishinaga No. 8 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. 9 B199/MAPLD2004
SmartSat-1
Twin 150-kg class experimental satellites
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 ]
[ SmartSat-1a ]
Nishinaga No. 10 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. 11 B199/MAPLD2004
OSDR: Breadboard model
Designed and manufactured in 2002
Dual XCV100s+ 1 XCV 100 (for controller)
Normal operation mode (full spec. filtering) and degeneracy mode (half throughput)
Designed and manufactured in 2004
1st generation2nd generation
Nishinaga No. 12 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. 13 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. 14 B199/MAPLD2004
Triple modular redundancy mode
TMR voter implemented on controller FPGA
Nishinaga No. 15 B199/MAPLD2004
Daisy chain mode
Nishinaga No. 16 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. 17 B199/MAPLD2004
Readback issues
System requirements:
3.0M-bit data for FPGA
18M-bit data for 6 FPGAs
Need 54M-bit datafor Readback operation (including MSK and RBB)
On-the-fly compression/decompression
Nishinaga No. 18 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,” Single-Event Upset Susceptibility Testing of the Xilinx Virtex II FPGA,” MAPLD2002, paper P29)
Nishinaga No. 19 B199/MAPLD2004
Radiation test result (1)
Block RAM region
1.E-11
1.E-10
1.E-09
1.E-08
1.E-07
1.E-06
0 10 20 30 40 50 60 70
LET(MeV cm2/mg)
Cro
ss S
ectio
n (c
m2 /b
it)
V2-Pro
V2
Nishinaga No. 20 B199/MAPLD2004
Radiation test result (2)
Configuration Memory region
1.0E-11
1.0E-10
1.0E-09
1.0E-08
1.0E-07
0 10 20 30 40 50 60 70LET [Mev cm2/mg]
Cro
ss S
ecti
on[c
m2 /b
it]
V2-Pro
V2 (iMPACT)
V2 (FIVIT)N Ne Kr Kr( 35° )
Nishinaga No. 21 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