Design of a Free Space Optical Communication Module for Small Satellites
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1 Design of a Free Space Optical Communication Module for Small Satellites Ryan W. Kingsbury, Kathleen Riesing Prof. Kerri Cahoy MIT Space Systems Lab AIAA/USU Small Satellite Conference August
2 Problem Statement Outline Related work: AeroCube-OCSD System architecture Design parameters & physical layout Optical transmitter Beacon-assisted pointing, acquisition & tracking Current Focus & Expected Results 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 2
3 Problem Statement CubeSatsare performing great science but the downlink bottleneck is common problem amongst operators RF solutions limited by antenna gain Difficult / risky regulatory process Optical transmitters offer narrow beamwidths& higher gain Price: pointing becomes more difficult Recent advances in CubeSat ADCS key enabler for lasercom Reaction wheels, horizon sensors, star trackers Our work addresses implementation gaps that hinder scalability of CubeSat-scale lasercom systems: 1) staged pointing control, 2) compact high-rate transmitter 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 3
4 Aerospace AeroCube-OCSD Pair of 1.5U CubeSats 5 Mbps downlink Stretch goal: 50 Mbps Body-pointing only 1065 nm, 0.35 FWHM 10 W average optical power Fiber amp (YDFA) Custom power solution GPS for precision orbit determination Ground station (Mt. Wilson) 30 cm aperture COTS APD detector operating Pointingaccuracy from 0.7 and 0.1 (mode dependent) Project status: Launch in Summer /6/2014 Kingsbury, Riesing - SSC14-IX-6 4
5 Our System Architecture Design targets typical 3U CubeSat SWaP, ADCS, nominal orbits Most need high-rate downlink Asymmetric link design Low-rate RF link (UL/DL) Optical beacon for acquisition and tracking Two-stage pointing system Coarse: host ADCS Fine: integrated fast-steering mirror Daytime or nighttime operation 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 5
6 Link Parameters Top-Level Design Parameters Link rate 10 Mbps(goal), 50 Mbps (stretch) Uncoded channel rate Bit error rate 10^-4, assumes code will be used Conservative baseline for FEC Range 1000 km ~ km LEO Space Segment Parameters Size, Weight 10 x 10 x 5 cm, 600g 0.5 U CubeSat mid-stack payload Power 10 W (transmit), 1 W (idle) Excludes host ADCS Coarse Pointing +/-5 (3-sigma), 1 /sec slew Host CubeSat ADCS Fine Pointing +/ (3-sigma) Lasercom payload fast-steering mirror Downlink Beam 1550 nm, 0.12 FWHM Radiometric constraint for 10 Mbps Beacon Receiver Uncooled Si focal-plane array 850 nm (TBR) Ground Segment Parameters Apertures RX: 30 cm, beacon: TBD Mount capable of tracking LEO object Acq. Detector InGaAs Camera Informs tip/tilt FSM Comm. Detector COTS APD/TIA Module Cooled module Pointing Coarse: TLE, Fine: tip/tilt FSM Detector size demands fine stage 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 6
7 Physical Layout Top View Side View 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 7
8 Optical Transmitter Design Master-Oscillator Power Amplifier (MOPA) architecture COTS Erbium-doped fiber amplifier (EDFA), space heritage High modulation bandwidths (GHz), high peak-to-average power Expected output: 200 mw(average) at 1550 nm Design challenges: Thermal stabilization of seed laser Extinction ratio (27 db needed for PPM-16) ½ MSA EDFA 9 x 7 x 1.5 cm 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 8
9 Pointing, Acquisition & Tracking Satellite autonomously slews from mission-defined attitude Acquisition sensor stares for beacon signal Centroid algorithm estimates boresight offset ADCS closes loop using beacon offset Integrated fine-steering mechanism rejects residual error Fast mirror steers downlink 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 9
10 Beacon & Detector Design Uplink beacon at near-infrared (850 nm) TLE & orbit propagation sufficient for orbit determination High-resolution focal plane arrays Detector provides largest FOV possible while maintain necessary resolution & SNR 10 full-angle FOV 5 Mpixel resolution actuation-limited Simulated FPA image Atmospheric Fading Ongoing analysis/design activities: Atmospheric fading (multi beam?) Detector noise modeling Focal plane readout performance db time (s) 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 10
11 Staged Control Approach Coarse stage patterned after typical COTS ADCS solutions Staged control alleviates range, resolution and bandwidth limitations inherent to all sensors and actuators Staged control essential for scaling to higher data rates Coarse Stage (host CubeSat) Fine Stage (lasercom payload) Type: Body-pointing/slew Optical steering Range: Full sphere +/ Accuracy: +/- 5 (3σ, pre-acq) +/- 1 (3σ, post-acq) +/ (3σ) (1/10 th our beamwidth) Bandwidth: <0.1 Hz >1 Hz 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 11
12 Fine Steering Mechanism Selection criteria: Field of regard, accuracy, BW SWaP(mirror + driver) MEMS Fast-Steering Mirror 2-axis MEMS tip/tilt mirror Steering range: +/ No integrated feedback sensors 3.6 mm diameter Image: Mirrorcle Technology Inc. Qualification in progress: Positioning repeatability Thermal stability Goal: predictable response across environmental ranges Mechanical mirror tilt ( o ) Differential drive voltage (V) 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 12
13 Single-axis tracking simulation 400 km altitude Post-acquisition Modeled disturbances: Solar radiation Magnetic Gravity gradient Aerodynamic drag Reaction wheels PAT Analysis Future work: Expand to 6 DOF Time to acquire Single Axis Simulation Results Coarse Pointing Accuracy ±0.02 (3-σ) Fine Pointing Accuracy ±0.001 (3-σ) 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 13
14 Closing Remarks First attempts at CubeSat lasercommotivated by: Demand to downlink payload data Advances in CubeSat ADCS Our work will address future implementation gaps: Optical steering mechanism and staged control Compact, scalable optical transmitter Expected results in next 12 months Hardware-in-the-loop PAT demonstration Bench-top end-to-end link demonstration 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 14
15 Prof. Kerri Cahoy (MIT) Acknowledgements Tam Nguyen (graduate student, MIT) NASA JPL Strategic University Research Partnership PI: William Farr NASA Space Technology Research Fellowship Program MIT Lincoln Laboratory 8/6/2014 Kingsbury, Riesing - SSC14-IX-6 15
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