Overview of the Small Optical TrAnsponder (SOTA) Project
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1 Overview of the Small Optical TrAnsponder (SOTA) Project Space Communications Laboratory Wireless Networks Research Center National Institute of Information and Communications Technology (NICT)
2 Satellite mass v.s Data rate of Satellites ever launched 1.0E+12 Data rate for Earth observation satellites [bps] 1.0E E E+03 Micro satellites TerraSAR-X WorldView1 EROS-B Formosat2 GeoEye-1 Orbview3 Kompsat2 ALOS Orbview4 JERS1 EOS-PM1 Ikonos2 Radarsat1 TopSat QuickBird2 Lewis ERSEnvisat1 Landsat ADEOS Spot UK-DMC2 RazakSat-1 MOS 1B MOS 1A Terra UK-DMC1 EROS-A IRS-1A,1B,1C AS1000 AlSat Orbview2 TRMM MicroLabSat EarlyBird Cute-1.7 PRISM TOMS-EP Cute-I Satellite mass [kg] 2
3 Laser-Communication Infrastructure for Micro-Satellites Short-term space verification by micro satellites (2~3 years) High-end communications by mid/small satellites (5~ years) Data rate for Earth observation satellites [bps] 1.0E E E E+03 New area covered by SOCRATES/SOTA Cute-I Cute-1.7 Optical ~Mbps Micro satellites RF ~kbps PRISM WorldView1 EROS-B Formosat2 GeoEye-1 Orbview3 Kompsat2 ALOS Orbview4 JERS1 EOS-PM1 Ikonos2 Radarsat1 TopSat QuickBird2 ~100Mbps Lewis ERSEnvisat1 Landsat ADEOS Spot UK-DMC2 RazakSat-1 MOS 1B MOS 1A Terra UK-DMC1 EROS-A IRS-1A,1B,1C AS1000 AlSat Orbview2 TRMM MicroLabSat Mid/small satellites Gbps EarlyBird TOMS-EP TerraSAR-X Quasi-real-time data transmission via site diversity Offline transmission only Satellite mass [kg] 3
4 Research Activities on Space Laser Communications in NICT ETS-VI (KIKU6) GEO-GND OICETS (KIRARI) LEO-GND GEO-LEO ETS-IX 2021 GEO-GND SOCRATES RISESAT with Tohoku Univ. LEO-GND 2017? LEO-GND 4
5 Overview of SOTA SOTA: Small Optical TrAnsponder Data rate : 1 10 Mbps Wavelength : Tx 0.8 / 0.98 / 1.55 µm Rx µm Beam pointing : Az - El mount + Fine-pointing mirror SOCRATES 衛星に組み込まれた SOTA Mass : 6.2 kg (including optical and control part) One of the smallest optical-communication terminals for spacecraft equipment 5
6 Development of SOTA Project started PDR CDR Launch End of operation QKD lasers Coarse sensor Fine sensor Checkout Experiments SOTA Workshop Receiver Transmitting Laser BBM model Mass: 5.3 kg, Power: 22.8 W Size: W149xD188xH160 PFM model Mass: 6.2 kg, Power: 39.5 W Size: W65xD114xH138 6
7 Major Specifications of SOTA SOTA-OPT Mass Power consumption Gimbal range Link range Wavelength Data Rate 5.9 kg (incl. both the optical part & electric part) Sleep Standby Tx2,3, Tx1 mode 4 1.7W 2.0W 15.7W 12.6W Az: >±50deg, El: -22deg~+78deg Less than1000 km Tx1: 976 nm Tx2 and Tx3 : 0.8 μm Tx4 : 1549 nm Rx: 1064 nm, Acquisition/Tracking: 1064 nm 1Mbps / 10Mbps (selectable) Photograph and Layout of SOTA-PFM optics (Proto Flight Model) 7
8 Small Satellite SOCRATES Satellite bus developed by AES SOTA Solar Paddle Size W496 x D495 x H485 mm Mass : 48kg AES Attitude control : 3-axis stabilization 8
9 Optical Ground Station in Koganei (1-m Diameter) - 1-m diameter reflective telescope - Improved tracking ability for LEO satellites - Focus availability: 5 ports (Cassegrain, Nasmyth, Coude ) Koganei Major specification Mount Altazimuth Focus Classical Cassegrain Diameter f1000 mm D/f F12 Tracking accuracy LEOs < 10 arcsec Stars < 0.4 arcsec (EL > 30 deg.) Stars < 1 arcsec (EL=15~30 deg.) Angle coverage Azimuth ±270 deg. Elevation 15~88 deg. Total mass 7.5 t Tube mass 1.3 t Nasmyth payload mass 1 t (max) 9
10 Launch 24th of May, 2014 Piggyback satellite of the ALOS-2 DAICHI-2 Advanced Land Observing Satellite Orbit : Sun-synchronous sub-recurrent orbit Altitude : 628km 10
11 - Configuration of SOTA Experiment - Ground system 3) Beacon laser Small satellite system Optical ground station (OGS) (NICT Koganei) 4) Tx laser Small Optical TrAnsponder (SOTA) Direct Comm. Small camera 1) Parameters 6) Telemetry TT&C station 2) Commands TT&C 5) Telemetry data Data & control signals Image data & control Small satellite bus *TT&C: Tracking, Telemetry and Control 11
12 Schedule of Conducted Experiments Date Event May 24, 2014 SOCRATES Launch ~ July Check out of the satellite ~ Oct. Check out of the OGS and the SOTA Nov. ~ May, 2015 ~ Spring, 2016 ~ Experiments for the NICT Start of international experiment campaign Resumption of international experiment campaign 12
13 Statistics of Total 184 Passes Satellite Trouble 2 passes 26% Both Uplink Downlink Established 47 passes Bad Weather Forecast 67 passes No Go 38 % Go 62 % 21% Only Uplink Established 21 passes Failed (due to Satellite) 17 passes Failed (due to OGS) 30 passes 13
14 Success Criteria No. Experiment items Contents Status Minimum success M1 Start-up check of Demonstration of COTS parts equipment Done M2 Confirmation of optical Demonstration of COTS parts sensors etc. Done Success S1 Tracking test Confirmation of orbit, bus attitude control and mounted equipment Done S2 Acquisition of the received signal, data acquisition at Propagation data different wavelengths (Uplink: 1064nm / Downlink: acquisition TX1, TX4) Done S3 BER measurement Downlink: TX1, TX4 Done Full success F1 Data transmission Confirmation of data transmission functions ( Data: experiment CAM / PRBS / Sample image ) ( Downlink: TX1, TX4) Done F2 Error correcting code LDGM and RS codes Done E1 E2 Polarization measurement International experiment Extra success Weak coherent pulses are measured by single photon counting detectors (SPCMs). Experiment with other international optical ground stations (OGSs) except for Koganei OGS. Done Done 14
15 Site-Diversity Technology Weather-monitoring stations Whole-sky monitor camera Optical communication satellite Cloud Laser beam OGS control center OGS 15
16 Optical Ground Stations Network Koganei 1m Koganei 1.5m Okinawa 1m Kashima 1m 16
17 Overview of In-orbit Experimental Results with SOTA Overview of the SOTA project NICT s New OGS In-orbit performance of SOTA Atmospheric-turbulence analysis BER measurement Data-transmission experiment Error-correcting code experiment QKD-related experiments LEO-satellite optical observation with NICT portable telescope Optical detection for SOTA downlink experiment using SSPD International joint-experiment campaign 17
18 Summary (1) Space-to-ground laser-communication experiments with the SOTA terminal have been successfully conducted. (2) Almost all of the success criteria from minimum- to extra-success have been done, including international experiments. (3) World first lasercomm technology for a 50-kgclass micro-satellite was verified with several international partners globally, which has opened the door to a variety of applications to be exploited soon with the rise of mega-constellations. 18
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