Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying
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1 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: 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 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
2 Fredrik Sjöberg Project Manager SATELLITE SYSTEMS Full Electric Mission to Moon (SMART-1) and Technologies: Electric propulsion, rendez-vous, formation flying Presentation to the 44 th Space Congress
3 SATELLITE SYSTEMS OHB Sweden A small innovative space company in a small country
4 Heritage and achievements From pioneering small satellite builder in Swedish Space Corporation... EARLY SATELLITES Small scientific satellites in 1980 th and 90 th Viking (1986) Freja (1992) Astrid 1 (1995) Astrid 2 (1998) HIGH-PRECISION INTERPLANETARY FORMATION-FLYING Precise 3-axis attitude control for astronomy and Earth observation Still operated by OHB Sweden. Odin (2001) First ESA Lunar mission. Low-thrust transfer to lunar orbit SMART-1 (2003) Demonstration of Formation-Flying & Rendezvous using GPS, Vision-Based, and RF-navigation. PRISMA (2010) Page 3
5 ... to Technology specialists in the OHB group A small, flexible, innovative team with high technical knowhow 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 Orion PQM Innosat Solar Orbiter Page 4
6 SATELLITE SYSTEMS Electric Propulsion and SMART-1
7 Electric propulsion: From lunar mission SMART-1 to future telecom /19 Launch SMART-1 Landing From GTO to Lunar orbit Testing of EP and satellite technology for interplanetary missions High radiation environment through radiation belts Development AIT Launch SGEO Chemical propulsion from GTO to GEO EP for station keeping in operations (15 years) Development AIT Launch ELECTRA Full EP (transfer + GEO) Cost efficient EPPS & AOCS architecture Page 6
8 SMART-1: First to the moon from Europe... 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
9 SMART-1: Accommodation of the EP system Pressure regulation panel (BPRU) EP Power Unit (PPU) Xe-tank (49 litres / 82 kg ) System Unit Heatpipes 2-axis Thruster Orientation Mechanism Thermal insulation EP thruster
10 Spiralling out to the moon over 15 months
11 SMART-1: A tough journey through the radiation belts
12 Worst possible weather conditions! Massive solar storms Oct/Nov 2003 Immense increase (x10 5 ) of solar protons
13 Star tracker hot spots Stars visible in star tracker during normal operations After passage through the radation belts
14 SMART-1 flight experience: 200 μm coverslides, 8% loss of S/A power before reaching hp=10,000 km
15 Around moon pictures were taken by SMART-1
16 Search for Peak of eternal sunlight Jan 2005 Lunar North Pole from 5000 km
17 Deemed to end... Decending orbit due to earth and sun influence
18 Calculation of point of impact
19 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,
20 Impact on the moon Sep 03, 2006, UT Canada-France-Hawaii Telescope (CFHT) 3.6m telescope, Mauna Kea DUST CLOUD OF 20 X 80 KM
21 SGEO Small GEO Europe s first geostationary All-EP satellite Hall Effect Thrusters for east-west and north-south station keeping EP Thruster Assembly EPTA 1 HET XFC C1 C2 HET 2 XFC C1 C2 HET 3 System Communication Bus MIL-STD-1553 System Power Bus Discrete signals SMU XFC XFC PPU\TSU Ext.TSU C1 C2 C1 C2 HET 6 HET 7 2nd port Node Xenon Tank Assembly C Xenon Tank HP Node Propellant Supply Assembly Pressure Regulation Mechanism LP Node EPTA 2 HET XFC C1 C2 HET 1 XFC XFC C1 C2 C1 C2 HET 4 HET 5 C Xenon Tank Support and Control Electronics XFC PPU\TSU C1 C2 HET 8 Ext.TSU Thermistors Heaters SMU Cold Gas Thruster Assembly Cold Gas Conditioning System Cold Gas Actuator Drive Electronics NOM RED CGT 1 CGT 2 CGT 3 CGT 4 CGT 5 CGT 6 CGT 7 CGT 8 Page 20
22 Electra Electra: Europe's Full EP satellite 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 days depending on launch scenario Page 21
23 Electra Electra: An innovative Electric propulsion system 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 Electra EP thrusters arrangement showing OR mode (left) and SK mode (right). Page 22
24 SATELLITE SYSTEMS PRISMA A test bench for future scientific and exploration missions
25 PRISMA Mission Background: Why? Needs of future exploration missions Autonomous Formation Flying Large apertures and antennas for science missions, stereoscopic or phased imaging. Autonomous Rendezvous In Orbit Inspection, Servicing, or debris removal. PRISMA MISSION IDEA: Demonstrate maneuvering techniques and sensor technology for Autonomous Formation Flying and Rendezvous Page 24
26 The PRISMA Satellites Tango 3-axis stabilized Solar Magnetic control 40 kg launch mass FFRF, GPS, Inter-satellite link 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 Page 25
27 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
28 PRISMA Mission Summary PRISMA Rendezvous Reconstruction and Video from Orbit OHB Sweden OHB SWEDEN AB Page 27
29 Formation keeping demonstration Formation pointing to the Moon for 5 hours (5 cm positioning accuracy)
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