Grzegorz Brona

10.11.2017 • Exploration of space now (lecture 101)

• How to construct a Polish scientific satellite - example of BRITE constellation (lecture 102)

• How to build a satellite for future polish scientific missions (lecture 103)

• Possible scientific missions and their outreach (lecture 104)

2 Exploration of space now

why ?

3 Space 1.0 Space 2.0

The epoch before space From the Sputnik to flights. The era of great the fall of Soviets. astronomers and naked Constant flow of money eye or telescope but the priotities rather observations. not scientific.

Space 3.0 Space 4.0

Era of dinosaurs based Industry in space, on technic from S 2.0. private capital involved, Space shuttles, Hubble, economic optimisation, ISS but also raise of global services, raise of telecomunication national ambitions in satellites. smaller countries.

4 Paradigms of Space 4.0 era:

• Space should be affordable not only for big countries and big scientific institutes

• A close cooperation between different entities targeting doing research in space, providing new technologies, products and services.

• Better, cheaper launchers:

3000-25 000 USD per kg (existing rockets)

drops to 2000 USD per kg for reusable Falcon-9

drops to 1500 USD per kg for Falcon Heavy

Depending on a mass of a satellite 5 Paradigms of Space 4.0 era:

• Use of cheaper electronic component (commercial of the shelf COTS)

• Miniaturization of electronics, mechanics, removing some redundance

• Outcome: reduction of costs by a factor of hundreds but increase in risk of mission failure

• Risk mitigated by redundant units (still cost much lower)

• Raise of small satellites operating in space

• Problem of space debris

6 Nanosatellite • Open standard • 1-10 kg • 30-50% for instrument • Good for education, Total mass of all objects send some science, testing to space each year

Microsatellite • 10-150 kg • 30-50% for instrument • Good for science, constelations (earth observation, telco) and some military

Standard satellite • >150 kg • LEO or GEO • Military, big science, telecomunication, EO with great precission 7 Annual SmallSat conference in USA: • 1987 -> 60 participants • 2017 -> 2550 participants • >350 students • >140 lectures • >50 universities represented • Many scientific missions presented

Titles of some proceedings:

- EQUULEUS: Mission to Earth - Moon Lagrange Point by a 6U Deep Space CubeSat - INCA (Ionospheric Neutron Content Analyzer) - Overview of the TRYAD Project: A Fleet of Two 6U CubeSats for Research on Terrestrial Gamma Ray Flashes - Calibrating the Swarm: Networked Small Satellite Magnetometers for Auroral Plasma Science - Tracking the Untraceable, Keeping the Earth Cool - Fugitive Methane Detection from Microsat Constellations - Sun Radio Interferometer Space Experiment (SunRISE) Proposal: Status Update - The Asteroid Probe Experiment (APEX) Mission

The topic of small satellites attracts a lot of attention worldwide.

8 How to construct a Polish scientific satellite – example of BRITE constellation (input from T. Zawistowski, M. Stolarski, A. Pigulski)

9 BRIght Target Explorer (BRITE)

• Constellation of 6 nanosatellites • Size 20x20x20 cm • Mass 7 kg • Equiped with a telescope of 3 cm diameter • With uncooled CCD • In space from 2013-2014

BRITE - PL

LEM HEWELIUSZ 10 To study bright variable stars • Photometry from the orbit – no atmospheric distortions • Bright stars – easy comparison with existing spectroscopic results • In case of combination of spectroscopic and photometric results for binary systems -> masses and radii available • For bright stars light extinction not important • 3 satellites use red filter, 3 satellites use blue filter

11 A constellation of 5 nanosatellites:

BRITE-Austria (BAb) 25.02.2013 UniBRITE (UBr) 25.02.2013

Lem (BLb) 21.11.2013 Heweliusz (BHr) 19.08.2014

BRITE-Montréal (BMb) 19.06.2014 Failed BRITE-Toronto (BTr) 19.06.2014

10 000 M USD 5 M USD Resonable price for a nanosatellite: 1 M USD

Non-stop coverage of FOV

Bright stars are too bright for big space telescopes eg. Hubble

12 Assembly, integration and Test (AIT) at Space Research Center Subsystems: • On-board computer (OBC) • Magnetometer, sun sensors star tracker - Attitude and orbital control system (AOCS) sensors • Reaction wheels – AOCS actuators • S-Band antenna – tranceiver module (TRxM) system • Solar cells, power distribution system – power dystribution unit (PSU) • Mechanical structure • Harness (cables) • Instruments - payload

13 Star-Tracker: an optical device that measures the positions of stars using a camera.

FOV 15° x 20.2°, Aptina MT9P031, Monochrome 5M CMOS 59 x 56 x 31.5 mm, Mass ~90g,

Up to 5.75 mag, 3746 stars in catalog, 2.1 milion triangles

On-board computer (OBC): a brain of a satellite with main tasks: • Receive and respond to commands from the ground station as well as handle the general housekeeping of the satellite. • Collect the telemetry data, format and encode the data for transmitting to the ground station. • Attitude determination and control using data from sensors. • Monitors temperature of all subsystems and maintains the satellite in specified temperature. • Store payload and telemetry data during non-visible period for transmission during visibility.

Based on CPU ARM 7 Texas Instruments. 20MIPS. 32MB RAM (EDAC), 256MB Flash. 14 Payload - telescope CCD chip: KODAK KAI-11002-M 11 Mega pixels with organisation 4008x2672

Telescope electronics CCD chip Set of lenses

Blende and filters

Support mechanics

Reaction wheels: for attitude control without using fuel for rockets or other reaction devices. They are particularly useful when the spacecraft must be rotated by very small amounts, such as keeping a telescope pointed at a star.

3 orthogonal reaction wheels from Sinclaire Interplanetary: 5x5x4cm, masa 185g, nominal power 100mW

Other device magnetorquer - built from electromagnetic15 coils 1 step: virtual model of the satellite, including information on cabling

2 step: flat-sat or a satellite on a board, testing all subsystems interactions

3 step: integration of the satellite according to long and boring procedures, no failure acceptable

16 1 test: shaking tests, checking if the satellite will survive start of the rocket, shaking can unscrew screws.

Each rocket has its own set of critical frequencies and accelerations:

2 test: vacuum thermal tests (termal vacuum chamber – the only one in Poland in SRC!).

What will happen if there is some air in the material structure of the satellite – outgasing!

Where the heat goes in the vacuum environment?

3 test: what is the best idea to test star-tracker? 17 Dragon: orbital deployer for BRITE-PL HEWELIUSZ

Designed and build at SRC in Poland

Securs the rocket from problems with the satellite

Safely delivers satellite to orbit LEM was launched on DNIEPR rocket (21.11.13), former balistic missile which retired after START II treaty (DubaiSat-2, STSAT-3, SkySat1, WNISAT-1, ApizeSat-7, AprizeSat-8, UniSat-5, Delfi-n3xt, Dove 3, Dove 4, Triton 1, KHISat-1, KHUSat-2, CubeBug2, GOMX-1, NEE-02, FUNCube-1, HINCube, ZACube, Icube-1, HumSat-D, PUCPSat-1, Pocket-PUCP, UWE-3, BeakerSat1, QubeScout1, WREN, 50Sat, First-Move, Velox-P2, OPTOS, BPA-3)

HEWELIUSZ was lunched on Long March rocket (19.08.14)

18 For HEWELIUSZ:

Low Earth Sun-synchronous orbit (a nearly polar orbit around Earth in which the satellite passes over any given point of the planet's surface at the same local solar time)

630 km with orbit period 101 minutes

Ground control station:

In Canada near Toronto,

In Austria near Graz

On the roof of Nicolaus Copernicus Astronomical Center in Warsaw 19 BRITE field:

• „Naked eye” astronomy: brightness < 6.5 mag

• The faintest star observed: 6.98 mag

• Brightest star: -0.73 mag (Canopus)

• FOV approximately 25°

• Fields observed: 24

• Average number of stars per field: 27

• Total number of stars observed: 500

• Typical observation time: 5.5 months

• Change treshold: 0.1-0.2 mmag

6 • All data points: > 34 x 10 20 β Cephei type stars: variable stars that exhibit small rapid variations in their brightness due to pulsations of the stars' surfaces, thought due to the unusual properties of iron at temperatures of 200,000 K in their interiors.

123 stars of this type observed.

New modes detected for almost all observed stars: eg. for β Centauri 19 new modes are found with BRITE Data.

New β Cephei-type stars have been found: eg. α Cru, δ Pic, π Sco

Data on intenal rotation of the stars and internal structure

Astro-seismography

Pigulski (2016) al. et Pigulski 21 • More than 202 of the stars analysed are spectroscopic binaries stars (spectral lines in the light emitted from each star shifts first towards the blue, then towards the red, as each moves first towards us, and then away from us).

• More than 256 are members of visual binary systems (for some visual orbits available).

• More than 32 are eclipsing binaries systems (for these data from BRITE provide excelent photometry). New eclipsing binaries found: τ Lib Some of the binary stars have

also pulsating component Pigulski al. et Pigulski

eclipsing: δ Pic, V Pup, π Sco, λ Sco, spectroscopic: V389 Cyg, α Cru, β Cru, β Cen visual: β Cen, ζ Ori 22 How to build a satellite for future polish scientific missions

23 • BRITE constellation proved that small satellites can deliver useful data

• Construction of nanosatellites and microsatellites are in the reach of polish entities

• What shall be the next step? HyperSat platform, a multifunction and multimission satellite platform for future space missions.

• The basic module dimension 30x30x10 cm

• The basic module mass 10 kg

• All subsystems prepared during subsystems project

• Compatible with all possible future scientific polish missions

• Compatible with small future European Space Agency missions

24 1 HU (HyperSat Unit) 3 HU 6 HU (the largest platform)

6 HU – with a bigger payload Comparision with the nanosatellite standard

25 • Platform will be fully open

• Attract universities/institutes/students to propose future payloads and subsystems for the platform

• The first open satellite platform in the world

• Much cheaper in use, better tuned for science missions

• Faster preparation of missions (no problems with intelectual property)

• The rules of openes are based on my long cooperation with CERN in the scope of CERN Open Hardware

• Full documentation of the project will be published 26 The project is planned for 3 consecutive years

Time in year quarter Project phase Name of the phase Analyse of the needs and blueprints Laboratory model Engineer model Tests of the engineer model

01.09.17 01.09.20 Financial resources already granted from the Ministry of Science and Higher Education and from private sources. The team of 25 people in total started to work on the project

27 Looks a bit complicated but… 28 Electronics in Space VPX standard 4 baterries

Reaction wheels

Other subsystems accomodated by the structure:

1. 6 Sun sensors (one per each wall) 2. Star-tracker 3. Magnetometer

4. Magnetorquers (induction coils) 29 Separation mechanism will be based on the concept of Marman clamp (used previously for the separation of Cassini spacecraft) – these are three rings plus pirotechnic mechanism.

Addidtional springs will be used to make a push from the rocket structure.

System will be fully scalable with mass and size.

Mass of 2-3 kg. 30 On-board computer (OBC): • OBC is composed of FPGA unit and CPU unit • OBC can control the data flow in the HyperSat communication bus • OBC includes fast FLASH memory • OBC dedicated to different mission will be compatible at the level of hardware abstraction • OBC will be reconfigurable from Earth at the level of software and gateware

On-board data handling (OBDH) • OBDH provides diagnostics of the whole system. • Applies commands from telecomunication modem. • Gathers, stores, process and sent to Earth data from payload. Two possible choices: 1. cFS – core Flight System already tested by NASA based on C/C++. 2. NanoSat Mission Operation Framework (ESA) – based on JAVA, will be tested at 31 OPS-SAT 2018. Modification of the SpaceVPX standard: power supply unit connected with power distribution unit

Power supply bus: • 28 V (nonstabilized) • 5 V (for logic units) • 3.3 V (low efficient, management units)

Minimal power 50 Watts

32 Deployable solar panels Dwa niezależne TRX dla pasm S oraz X; TwoTRXM1,independent TRXM2 transmission bands: •- S-Softwareband: 2-4 Defined GHz Radio + RF • X-FrontEndband: 8-12.5 GHz - Data Rate X-band: do 50Mbit/s Software defined radio on board Zagadnienia: In- X-bandWspólna up to lub 50 osobna Mbit/s antena dla TX/RX; zastosowanie dipleksera Compensation- TRX i modem:for Doppler razem vs. effect osobno - Dodatkowy RX lub TRX do telemetrii (SDR w trybie RX to 20- 30W) - 4 tory (2xRX, 2xTX) vs. 2 tory (TDD - problem przy dużych prędkościach, Doppler)

33 Mission Control System (Slow Control): • Compatible with the ESA SCOS-2000 system controlling all ESA satellites • Fully reconfigurable for different missions (floating dashboard, adding and removing controls) • Special module for the redundant systems • Including encryption

Satellite monitoring: • Displaying satellite 3D model with all the components • Displaying satellite position on orbit • Monitoring of all the parameters • Logs, alarms, histograms of historic data • On-line parameters monitoring • Archivization of all the commands

34 Mission Control System (Slow Control): • Compatible with the ESA SCOS-2000 system controlling all ESA satellites • Fully reconfigurable for different missions (floating dashboard, adding and removing controls) • Special module for the redundant systems • Including encryption

Satellite control: • Sending commands on-line • Off-line commands (scheduler) • Sending files and receiving files • Changing the FPGA software • Adding applications to the OBC • Reseting subsystems of the satellite (eg. clock settings)

35 • The bus will be based on SpaceVPX standard • SpaceVPX adresses interoperability 3U card: 160x100x20mm 6U card: 160x230x20mm and is single point fault tolerant Payload, OBC, Bus Payload, OBC, • Point-to-point connections, failure Controller,… Bus Controller,… on one module does not affect the full system • Uses SpaceWire standard of communication introduced for spacecrafts by ESA • Standard supported by NASA and by space sector in USA – high compatibilty of the components 36 • PAY (it is not only true payload): •OBC (computer) •TRXM (communication) •SAB (sensors and actuators boards) •Satellite Payload • CNTRL: • Clock distribution • Utility communication (I2C) • Control communication (SpW or UART) • PSX & PSU: • Power supply (solar & battery) • Power distribution 37 38 39 Possible scientific missions and their outreach

40 HyperSat platform is design to suport variouse instruments as payloads: - observation, visible spectrum, UV, IR - microwave sensors - synthetic aperture radar (SAR) - rotating sensors - biological experiments - electronics and material testing

Parameters of the payload - up to 15-25 kg - up to 35W consumed by payload - downlink: from single kbits/s up to 10Mbit/s

41 • In 2016 a feasibility study on a construction of Polish scientific satellite observing stars in the UV spectrum was performed

• Two options were proposed: 1) Stars UV photometry (50 kg) 2) Stars UV spectroscopy (130 kg)

• At the moment no space telescope in UV spectrum is on orbit (except fot Hubble)

• Previously 1978-96 the International Ultraviolet Explorer was on orbit

• Many observation on hot stars, accrection disks and active galactic nuclei were performered. Also SN1987A.

• Know-how in Poland exists on UV astronomy 42 (Warsaw and Wroclaw) Photometer: Spectrometer: Dual telescope with large FOV: Dual telescope with small FOV: 1) UV centered at 250 nm 1) UV width 100-200 nm and width 60-100 nm 2) VIS width 200-300 nm 2) VIS centered at 550 and FOV: 30 min width 60-100 nm Diameter: 20-40 cm FOV: 100 min Diameter: 5-12 cm

43 • Strong know-how in SRC on the X-ray spectrometers construction

• Solar Photometer in X-rays SPHinX built at SRC was flighing in 2009 at CORONAS-photon probe, designed for the flares monitoring, 1-15 keV with 0.5 keV resolution

• X-ray Spectrometer/Telescope STIX will fly at Solar Orbiter mission, 4-150 keV

• The X-ray measurements determine the intensity, spectrum, timing, and location of accelerated electrons near the Sun – understanding the electrons acceleration process near Sun and their propagation through space

44 • It could be a good time for Polish project Overview of the experiment: - Two Silicon Drift Detectors for solar X-ray measurements - Very high dynamic range - Good spectral resolution - Low mass 1-3 kg - Low power consumption - Compact size - Cost effective

Data quality:  High temporal resolution up to 1 ms.  Energy band 1-15 keV, 1024 channels with energy resolution better than 1 keV.  Possibility of extending energy band up to 150 keV

45 From Szymon Gburek: Centrum Badań Kosmicznych PAN Zakład Fizyki Słońca Space Research Centre PAS Solar Physics Division Mission planned for 2018 at 6U CubeSat (NASA): ● Demonstrate new radar technologies in Ka- band (35.75 GHz). ● Demonstrate a Ka-band precipitation radar on a 6U CubeSat. ● Identify and burn down technical risks for radar payload at small satellites. ● Enable precipitation profiling Earth science missions. Instrument data quality: the radar will collect vertical precipitation profiles between 0 and 18 km altitude above Earth's surface, with a horizontal resolution <10 km, vertical resolution <250 m With a constelation observation of the short time evolution of the weather processes.

Eva Peral, Simone Tanelli, Ziad Haddad, Ousmane Sy, Graeme Stephens, Eastwood Im, "RaInCube: A proposed constellation of Precipitation Profiling Radat in CubeSat," Proceedings of the IGARSS (International Geoscience46 and Remote Sensing Symposium) 2015, Milan, Italy, July 26-31, 2015 Quantum Experiments at Space Scale (QUESS): • a proof-of-concept mission designed to facilitate quantum optics experiments over long distances • demonstrator of a quantum key distribution at a distance of 1200 km and then between China and Vienna • Two entangle photons generated on board of a satellite • Experiments will be followed by deploying by year 2030 global quantum key secured communication network

• In pararell European experiment was proposed to test an uplink communication (source of entangled photons stay on Earth), and a satellite has a weight 5-20 kg. • This will allow to test variouse cryptography protocols Earth-space.

D. K. Oi, A. Ling, G. Vallone, P. Villoresi, S. Greenland, E. Kerr, M. Macdonald, H. Weinfurter, H. Kuiper, E. Charbon, and R. Ursin, EPJ Quantum Technology 2016 3:1 4, 6 (2017)

47 • A new era of space exploration (Space 4.0) is on the rise

• Hundreds of small satellites will be deployed in the next 10 years

• Poland has an experience in developing smallsat scientific missions

• An open satellite platform is under construction and will be ready by year 2021

• A cost effective way to perform scientific experiments on low Earth orbit

• First possible payloads are being defined, hopefully more will come

• The budget for scientific programm is now being discussed 48