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!