nishinaga no. 1 b199/mapld2004 reconfigurable communication equipment on smartsat-1 nozomu nishinaga...

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


Outline

Motivation SmartSat-1 Reconfigurable Communication Equipment Onboard software defined radio Heavy Ion test results of Vertex II pro Conclusion


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


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


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


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?)


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







Software-Defined-Radio method Many multi-rate MODEMs Simple redundant system Test procedure very simple Payload not so heavy


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


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 ]


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)


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


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


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


Triple modular redundancy mode

TMR voter implemented on controller FPGA


Daisy chain mode


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.


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


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)


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


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° )


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. 1 b199/mapld2004 reconfigurable communication equipment on smartsat-1 nozomu nishinaga...

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