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1 W I S S E N T E C H N I K L E I D E N S C H A F T
www.tugraz.at
ESA’s OPS-SAT Nanosatellite Mission
A Laboratory in the Sky O.Koudelka, P.Romano, M.Unterberger, R.Zeif,
R.Finsterbusch, M.Binder, F.Teschl TU Graz
Manfred Wittig
MEW Aerospace
David Evans European Space Agency
2 2 Contents • Introduction • Satellite Bus • Satellite Payload • Experiments • Summary
3 3 3 Background & Motivation (1)
• New ideas are generated by ESA and European industry for evolving mission control
• Patents, studies, prototypes & breadboards are produced
• But the majority do not make it near a real mission
• Why …. • Has never flown - will never fly problem • Risk aversion: healthy when dealing with large
missions but not good for innovation
4 4 Background & Motivation (2) • In 2011 ESOC‘s Advanced Operations Concepts Office
had an idea to change the current situation • A low cost, in-orbit demonstrator for mission control
based on a COTS CubeSat bus - OPS-SAT • In January 2012 a CDF Study funded by GSP (with
CNES participation) declared the idea feasible • In May 2013 an Open Call for OPS-SAT Experiments
was run by ESA • Over 100 experiment ideas from 17 ESA member states • OPS-SAT Open Day in June 2013 attracted 100+ guests
• Phase A/B1 study in 2013, completed in early 2014 • Phase B2/C/D/E1 Contract awarded in Feb 2015
5 5 A Quiz
6 6 A Quiz
7 7 OPS-SAT Mission Statement
“OPS-SAT is a safe, hard/software laboratory, flying in a LEO orbit, reconfigurable at every layer from channel coding upwards, available for authorised experimenters to demonstrate innovative new mission operation concepts.“
8 8 OPS-SAT
3 U CubeSat 5 kg mass
9 9
UHF Transceiver
OBC Coarse ADCS
GPS
Control
CCSDS Engine
Attitude Sensors/
Magnetorquer
EPS Solar Cells
4 x SoM
SDR Front-end
HD Camera
Optical Receiver
X-Band Receiver
Fine ADCS
S-Band Transceiver
UHF antenna
S-Band antennas X-band antenna
SDR antenna
Bus Payload
10 10 Satellite Bus
• Nanomind OBC • TM/TC processing • Coarse ADCS processing • Housekeeping data acquisition • Communication with ground • Novatel GPS module
• NanoCOM AX100 Transceiver
• UHF half-duplex communication, 9.6 kbps • ISIS Deployable Antenna
• Polarisation: circular • 2 antennas (dipole) for UHF TRX • 2 antennas (dipole) for SDR
11 11 EPS and Solar Arrays • Two Gomspace Nanopower • Two redundant power lines • Li-Ion batteries (5200 mAh)
• 2 Clydespace double-folded solar arrays
• up to 30 W
12 12 OPS-SAT Payload
• Core Payload • Processing Platform • CCSDS Engine • S-Band Transceiver
• Payload Peripherals • Fine ADCS • HD camera • GPS receiver
• Payload of Opportunity • X-Band Transmitter • Optical Receiver • Software Defined Radio Front-End • Corner Reflector
13 13 Core Payload Processing Platform
• Satellite Experimentators Processing Platform (SEPP)
• Four systems in cold redundancy • Altera Cyclone V SX SoC
• Dual Core ARM Cortex-A9 • Running up to 800 MHz • FPGA Fabric
• Memory • 1 GB DDR3 RAM (+ ECC!)
• External Mass Memory: 8 GB • ~5W power consumption (Linux)
14 14 Core Payload: CCSDS Engine
• At least one configuration representative of an ESA mission
• Compatibility with ESTRACK • CCSDS Engine based on ESA IP-Core • Decode/Encode CCSDS frames • Direct Commands • Bypass feature
15 15 Core Payload: S-Band Transceiver
• Syrlinks Transceiver • CNES funded • Uplink: 256kbit/s • Downlink: 1 Mbit/s
• Diplexer for full duplex operations • Patch antennas by TUG
16 16 Payload Peripherals: Fine ADCS
• BST iADCS: „ADCS for the experimenters“ • MEMS sensor • Gyro • Accelerometer • Magnetometer • 1 star tracker • 6 reaction wheels • 3 magnetorquers
• Full Set of Attitude Control Algorithms • Att. Knowledge: 30 arcsec • Pointing Accuracy: << 1°
17 17 Payload Peripherals: HD Camera
• BST HD Camera • Based on IMS-100 star tracker camera • Specifications:
• Optics: 25mm • Ground Resolution: 60 m
18 18 Payloads of Opportunity: X-Band Transmitter
• Syrlinks
• Data rate up to 50 Mbps • Real-time video download • RF output power: 27 to 33 dBm • Modulation: Filtered QPSK • Coding: Convolutional, CR = 1/2 • Power consumption: 7 W for 30 dBm
19 19 Payloads of Opportunity: Software Defined Radio (SDR) Frontend • Field programmable RF IC • Freq. Range: 300 MHz – 3.8 GHz • Max. Bandwidth: 14 MHz • Interfaces with the Processor Core
• Interference level monitoring (UHF) • Radio signal monitoring (e.g. ADS-B)
20 20 Payloads of Opportunity: Optical Receiver
• Single-photon counter module
• Optical uplink experiments
• pulse position modulation • Upload of cryptographic keys
21 21 Payload of Opportunity: Optical Retroreflector
• Coated Fused Silica Corner Cube Retroreflectors • Height: ~ 10 mm
• Mounted on the –z plane • Tracking of spacecraft
22 22 Ground Segment
• Use of small low-cost ground station (NGS-1 at ESOC) • S-Band and UHF
• File-based operations based on CFDP (first ever) • MO services ground-space protocol (first ever) • Full automation • Used every day
23 23 Experiments Evaluation • 93 Experiments evaluated
OPS-SAT Final Presentation
1 3
5
9 10 11
43 11
Experiment Category
Magnetic FieldMonitoringProtocol & Software
ADCS
Ground Applications
Camera
Scheduling &AutonomyOn-BoardApplicationsRadio &Communication
1 1 1 1 1 1 1 1 1 1 1
2 5
6 6
10 10 10
11 22
0 5 10 15 20 25
EgyptUSA
CanadaPolandIreland
SloveniaHungaryGreece
Czech RepublicBulgaria
ItalyNetherlands
BelgiumFrance
SwitzerlandSpain
UKESA/ESOC
AustriaGermany
No. of Experiments per country
24 24 Summary • OPS-SAT offers a unique opportunity to test, demonstrate and validate novel operational concepts in flight
• Experimenters will have the possibility to change
flight/ground software and reconfigure flight/ground hardware during this mission
• We have designed a mission that can allow this to take
place with minimal risk and at minimal cost
• SDR and optical communications experiments demonstrates new opportunities for small satellite missions
24
25 25 Consortium
26 26
Thank you for your attention!