Sjöberg, Fredrik

English

Embry-Riddle Aeronautical University

The Space Congress® Proceedings 2016 (44th) The Journey: Further Exploration for Universal Opportunities May 25th, 10:45 AM Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying Fredrik Sjöberg OHB Sweden, Stockholm Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Sjöberg, Fredrik, "Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying" (2016). The Space Congress® Proceedings. 16. https://commons.erau.edu/space-congress-proceedings/proceedings-2016-44th/presentations-2016/16 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact commons@erau.edu. SATELLITE SYSTEMS Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying Presentation to the 44th Space Congress Fredrik Sjöberg Project Manager SATELLITE SYSTEMS OHB Sweden – A small innovative space company in a small country Heritage and achievements Page  3 FORMATION-FLYING  Demonstration of Formation-Flying & Rendezvous using GPS, Vision-Based, and RF-navigation. PRISMA (2010) EARLY SATELLITES  Small scientific satellites in 1980th and 90th     Freja (1992) Astrid 1 (1995) Astrid 2 (1998) Viking (1986) HIGH-PRECISION  Precise 3-axis attitude control for astronomy and Earth observation  Still operated by OHB Sweden. Odin (2001) INTERPLANETARY  First ESA Lunar mission. Low-thrust transfer to lunar orbit SMART-1 (2003) From pioneering small satellite builder in Swedish Space Corporation...    • A small, flexible, innovative team with high technical know-how focussing on new developments • Total company staff 70 people • Specialized in Propulsion and AOCS • Still small satellite capability through new Innosat platform: • Innovative low cost microsatellite 40 kg  • First launch planned 2017 with climate research mission •   ... to Technology specialists in the OHB group Page  4 Orion PQM Innosat  Solar Orbiter  SATELLITE SYSTEMS Electric Propulsion and SMART-1 Electric propulsion: From lunar mission SMART-1 to future telecom SMART-1 SGEO ELECTRA • Chemical propulsion from GTO to GEO • EP for station keeping in operations (15 years) • Full EP (transfer + GEO) • Cost efficient EPPS & AOCS architecture Launch                  “Landing”   Development   AIT             Launch 2003   2004   2005    2006    2007    2008    2009    2010    2011    2012    2013    2014    2015    2016   2017  2018/19 Development AIT   Launch  • From GTO to Lunar orbit • Testing of EP and satellite technology for interplanetary missions • High radiation environment through radiation belts  Page  6 • ESA Technology mission to demonstrate use of low thrust for future interplanetary space journeys  • Developed and built in short time by Swedish Space Corporation (today OHB Sweden) using Small Satellite methods   • European Hall Effect Thruster fuelled by Xenon gas  • 15 months orbit transfer with 70 mN (7 gram) thrust  • <80 kg Xenon for full earth-lunar transfer SMART-1: First to the moon – from Europe...  EP thruster Thermal insulation 2-axis Thruster Orientation Mechanism Xe-tank (49 litres / 82 kg ) Pressure regulation panel (BPRU) EP Power Unit (PPU) Heat-pipes System Unit SMART-1: Accommodation of the EP system Spiralling out to the moon over 15 months SMART-1: A tough journey through the radiation belts   Worst possible weather conditions!   Massive solar storms Oct/Nov 2003  Immense increase (x105 ) of solar protons  Stars visible in star tracker during normal operations Star tracker hot spots After passage through the radation belts SMART-1 flight experience:  200 μm coverslides, 8% loss of S/A power before reaching hp=10,000 km Around 50 000 moon pictures were taken by SMART-1 Jan 2005    Lunar North Pole from 5000 km  Search for ”Peak of eternal sunlight ” Deemed to end... Decending orbit due to earth and sun influence  Calculation of  point of impact Smart-1 Impact SMART-1 IMPACT ON THE MOON Courtesy of Mark R Rosiek  USGS Astrogeology Team, Planetary Geomatics Group and Dr Anthony C.Cook, School of Computer Science and IT,University of Nottingham,  DUST CLOUD OF 20 X 80 KM Sep 03, 2006, 05.42.22 UT Canada-France-Hawaii Telescope (CFHT) 3.6m telescope, Mauna Kea  Impact on the moon   Small GEO Europe’s first geostationary”All-EP”satellite Hall Effect Thrusters for east-west and north-south station keeping SGEO Pressure Regulation MechanismSupport and Control ElectronicsPropellant Supply AssemblyHP NodeLP NodeCold Gas Thruster AssemblyCold Gas Actuator Drive ElectronicsCold Gas Conditioning System CGT 1CGT 4ThermistorsEP Thruster AssemblySystem Power BusSystem Communication Bus MIL-STD-1553CGT 2CGT 3CGT 5CGT 8CGT 6CGT 7NOMREDEPTA 2 – HETXenon TankAssemblyXenonTankPPU\TSUXFC HET 1HET 4HET 5HET 8C1C2XFC C1C2XFC C1C2XFC C1C2SMUCXenonTankCHeatersExt.TSUDiscrete signals SMU2nd port NodeEPTA 1 – HETPPU\TSUXFC HET 2HET 3HET 6HET 7C1C2XFC C1C2XFC C1C2XFC C1C2Ext.TSUPage  20 Electra  Electra:  Europe's Full EP satellite   Page  21 • Public private partnership with ESA, satellite operation SES and OHB group • Combines EP transfer knowledge from SMART-1 with station keeping knowledge from SGEO • Orbit transfer in 80- 200 days depending on launch scenario   Electra Electra: An innovative Electric propulsion system Page  22 Electra EP thrusters arrangement showing  OR mode (left) and SK mode (right). • Newly developed  4.5 kW/270 mN HET thruster for both orbit transfer and station keeping • Xenon storage capacity up to 800 kg in new developed tank • Optimized thruster configuration with four thrusters for all EP operations • Newly developed robotic THOR boom for thruster reorientation • High flexibility in COG position allows big variation in payload size   SATELLITE SYSTEMS PRISMA – A test bench for future scientific and exploration missions PRISMA Mission Background: Why? Autonomous Formation Flying Autonomous Rendezvous Needs of future exploration missions PRISMA MISSION IDEA: ”Demonstrate maneuvering techniques and sensor technology for Autonomous Formation Flying and Rendezvous” Large apertures and antennas for science missions, stereoscopic or phased imaging. In Orbit Inspection, Servicing, or debris removal. Page  24 The PRISMA Satellites Mango • 3-axis stabilized • Attitude Independent Orbit Control • 145 kg launch mass • FFRF, GPS, VBS, DVS, Inter-satellite link • 3 propulsion systems, >200 m/s Delta-V  Tango • 3-axis stabilized • Solar Magnetic control • 40 kg launch mass • FFRF, GPS, Inter-satellite link Page  25 Three (!) Propulsion systems on Mango  Hydrazine Six 1N thrusters Green propellant Two 1N thrusters MEMS Micropropulsion Two thrusters pods OHB SWEDEN AB  /  PRISMA and IRIDES Page  26 PRISMA Mission Summary Page  27 OHB SWEDEN AB PRISMA Rendezvous Reconstruction and Video from Orbit © OHB Sweden Formation keeping demonstration Formation pointing to the Moon for 5 hours (5 cm positioning accuracy) Visit www.ohb-sweden.se for more information 

Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying

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Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying

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