Ranging and Optical Communication R&D for Deep Space Missions

Transcription

1 National Institute of Information and Communications Technology 14th BroadSky Workshop Ranging and Optical Communication R&D for Deep Space Missions October 18, 2016 Hiroo Kunimori *1) and Hayabusa2 LIDAR team *2) *1) National Institute of Information and Communications Technology (NICT) *2) JAXA/ISAS, NAO, PERC, university institutes, NICT and Australian Space Environment Research Center (SERC). 1

2 National Institute of Information and Communications Technology Contents Background of Japanese Space Mission and ICT Optical Communication Rationale and Current Activities Development of Single Photon Detector and Evaluation Test Optical Link to Hayabusa2 using Ranging Instrumentation Conclusions 2

3 National Institute of Information and Communications Technology Background Table1 Japanese SPACE Policy Categories and Mission Plan Mission Current 2034 Positioning QZS1~ QZS2&3 > 7 satellites system Remote Sensing Land, Marine Meteorological CO2/H2O, others IGS(Radar and Optical) ALOS3, Advanced Radar series Himawari series COSAT/ GCOM, Shizuku, etc. Communications/ Broadcasting Next Generation ETS / Optical Data Relay X band Defense Launching Vehicle System H2A/B, Ipsiron, H3 SSA Ground system construction plan Science Deep Space X ray Others Hayabusa2,BepiColumbo(to Mercury) Hitomi (braked up) Geospace, Small sat series ISS Field of Application Summarized by authors based on 3

4 NICT Space Related ICT Activities Laser tracking and communication Orbit Determination Small Optical Laser Transponder Onboard Space communication & Very Long Baseline Interferometry Synthesized Aperture Interferometry 4

5 Background: Optical Comm. Band SPECTRUM of Electromagnetic Wave 5

6 Advantages of space based-laser communications Large communication capacity 80Gbytes data transmission: Optical: 16 sec. (40Gbps) RF: 13 min. (800Mbps) Amount of data: 50 times wider area can be observed. 10km x 10km Small and Low Power /bit Example: antenna diameter: -Optical: ~10 cm -RF: ~1.3 m Laser 70km x 70km RF Google Highly secure wireless communication Beam divergence angle: -Optical: ~0.001 degrees -RF: ~0.2 degrees Footprint of the beams (LEO case): -Optical: ~18m -RF: ~3.5 km No regulation Quantum key distribution 1000km ~3.5km RF LEO Low probability of intercept/low probability of detection (LPI/LPD) ~18m Laser Size comparison JAXA 6

7 Theory: Transmission rate v.s. Power for various modulations DEEP SPACE Comm. Distance:1AU Waseda, et. al, J. Opt Commun. Netw. 3(6) 514,

8 Current Project: Next generation HTS communication system International site diversity gateway stations Gateway stations Optical feeder links (~10Gbps class) Ka-band feeder links High Throughput Satellite Near Earth - 100Mbps class mobile satellite communications at Ka-band - Flexible traffic control for beam and frequency flexibilities. Coverage: EEZ + half hemisphere Fixed beams Scanning beams Oceans Broadband Airborne broadband Disaster communications 8

9 Current Activities Near Earth Down link using Optical Terminal (SOTA) on a small Satellite A high sensitivity new SSPD detector test by communication satellite 1um Ranging to debris tracking system engineering

10 Current Activities: Prototyped Pulse Position Transceiver MOD (Tx) DEM (Rx) Specifications: M array M: 2,4,16,256 Clock(=Slot)Rate: 2.5[GHz] expandable to 10GHz Degenerated Clock Order :4,8,16,32,64,128 Interval Time between Pulses: 12.86ns~ [μs] Frame Length: 8~256[Byte] OGS at Koganei 1.5m telescope Coude Room 10

11 Development of Single Photon Detector and Evaluation Test 11

12 Requirements of Receiver for Optical Space Communication Photon Detection Efficiency( =1550nm) > 50% Low Dark Count Timing Jitter < 100 ps PSF of received signal at focal point of receiver Through atmosphere Effective Receive Area > Φ 0.1 mm Max Count rate > 1 GHz Trade off Single Pixel SSPD Small Turbulence Large Limit to Satisfy The current status: Received Area: 15 x 15 m Max Count rate: ~20 MHz Requirements! 12

13 Why Arrayed SSPD? Benefits by arrayed detectors: a. Expansion of Communication Bandwidth by Merger of each pixel signal to reduce recovery time to accept another photon arrival after one. b. Less complexity of collecting Optics by larger receive area to increase coupling efficiency to a multimode fiber c. Angle information obtained by each pixel to feed back to PAT(acquisition, pointing and tracking) sub system. Single Pixel SSPD Drawback: d. Increasing noise by readout for larger pixels > overcome by Low noise Single Flux Quantum(SFQ) circuit in superconducting state. Interleaved 4 elements 13

14 Receiving Photon from Satellite by SSPD Test Bed Satellite Terminal SOTA 1.5um 10Mbps Taper Fiber um Optical Interface Nasmyth Table MMF 200um SMF VariableATT Taper Fiber 50 9um 2inch dia. Power meter APD Received Power 1.5m Telescope Power Meter SOTA Receiver 1:1 Coupler MMF200um Cryostat1 Single Pixel SSPD 1:1 Coupler Cryostat2 4 Pixels SSPD Counter SR400 Data I/O Process 15

15 Test Bed configurations Config-1 Optical Pulse Generator Var ATT Counter Config-2 PPM Transmitter SSPD Var ATT Oscilloscope Config-3 SOTA-EM 装置 Var ATT Temp Monitors Config-4 SOTA Optical Power PPM Receiver Meter 1.5m Telescope 16

16 SSPD : Trade off SDE v.s DC for bias current 100dBm =1MHz x1photon@1550nm E+08 DE 1.E+07 Detection efficiency (%) Single_Pixel SSPD Ch1: λ=1550nm DC 1.E+06 1.E+05 1.E+04 1.E+03 1.E+02 1.E+01 1.E+00 1.E 01 Dark count rate (cps) 1.E Bias current (ua)=10xvoltage(v) 1.E 03 17

17 Photon counting by SSPD recorded with associated PD/APD power sensors SR400 Counter at 1.5m telescope Counts SSPD2 SSPD Obs time (sec) 18

18 National Institute of Information and Communications Technology Optical Link to Hayabusa2 using Ranging Instrumentation 19

19 View of Hayabusa2 and LIDAR Courtesy of JAXA LIDAR located at view from this side 20

20 LIDAR on HAYABUSA2 Courtesy of JAXA 21

21 Hayausa2 Laser Altimeter LIDAR (Mizuno+, SSR 2016) Ranging/Otical Link/Dust Detection mode Gain min(1)/low(2)/middle(4)/high(8) 22

22 Distance of Hayabusa-2 from Earth Before and After the Earth Swing-By Operation TimeWindow North Hemisphere TimeWindow South Hemisphere Cruize to An Asteroid October November December 2015 days Sun-Probe-Earth (SPE) 23

23 Hayabusa2: Ranging and Optical Link Mode 1 2 Aiming to 1. Check LIDAR is Healthy by real operation 2. Measure unknown Boresight Error after Launch 3. Record a longer distance ranging and optical link 2 1 Ryugu 24

24 Specifications of the ground stations Koganei OGS Mt.Stromlo OGS Laser Wavelength [nm] Energy [J] Pulse width [nsec] Beam divergence [arcseconds] Repetition rate [Hz] Receiver Diameter [m] Detector InGaAs APD array IR enhanced Si APD 25

25 Photons Received in a Search Pattern Coordinates in Hayabusa2 R.A towards the Earth. 0.5 deg UPLINK Telemetry on Hayabusa2 Decri. Towards the Earth 0.5 deg

26 Optical Link Experiment using LIDAR and Debris Tracking Station

27 Optical link between Space Probe and the Earth Successful Record Messenger 24 million km 2Way Mars Global Surveyor 80 million km 1Way Lunar Reconnaissance Orbiter 0.4 million km 2Way.Lunar Laser Communication Demonstration 0.4 million km 622Mbps Hayabusa2 LIDAR 6.6 Million km 1Way Down link could not be successful due to a week link budget and weather opportunity Health of LIDAR on orbit confirmed Alignment of relationship between satellite body and LIDAR established for science observation at asteroid (RYUGU) approach in

28 National Institute of Information and Communications Technology Conclusions Report of background of Japanese Space Communication Mission and current activities for Optical Communication in NICT where near Earth and Deep space use a common optical ground station infrastructure. The activities focused on High Sensitivity Detector : Development of Array SSPD and its evaluation test bed Continue to develop a high power ranging system integrated to communication for the next generation deep space missions and optical link. 30