Mission Design for the CubeSat OUFTI-1

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CHAPTER 4have to be smooth and their edges rounded• the use of Aluminium 7075 or 6061-T6 is suggested for the main structure.If others materials are used, the thermal expansion must be similar to thatof the deployment system material (Aluminium 7075-T73) and approved.This prevents the CubeSat to conk out because of an excessive thermaldilatation.• no electronic device may be active during launch. Rechargeable batterieshave to be discharged or the CubeSat must be fully deactivated• at least one deployment switch is required• antennas can be deployed only 15 minutes after ejection into orbit whilebooms and solar panels after 30 minutes• it has to undergo qualification and acceptance testing according to thespecifications of the launcher: at least random vibration testing at a levelhigher than the published launch vehicle envelope and thermal vacuumtesting. Each CubeSat has to survive qualification testing for the specificlauncher. Acceptance testing will also be performed after the integrationinto the deployment system.4.1.1 Amateur Radio and D-STAR systemBefore proceeding with the description of OUFTI-1, a brief introduction of thesatellite’s payload, represented by its communications system, is necessary.D-STAR, which stands for Digital Smart Technology for Amateur Radio, isan open ham radio protocol recently developed by the Japan Amateur RadioLeague (JARL). Its main features are the simultaneous transmission of voiceand data, the complete routing capacity (including roaming), the cross-bandcapability and the possibility of passing through the internet.It works over three possible frequencies and data rates:• 144 MHz ( 2m, VHF ), 4.8 Kbit/s• 440 MHz ( 70 cm, UHF ), 4.8 Kbit/s• 1.2 GHz ( 23 cm, SHF ), 4.8 Kbit/s or 128 Kbit/sPresently, in Europe only the first two frequencies are available.The D-STAR technology is in fact really developed in the United States, wheremany repeaters are operational, but it’s quickly extending in Europe: the firstrepeater in Belgium is at the University of Liège and it has been installed withinthe OUFTI-1 project.Galli Stefania 22 University of Liège
CHAPTER 4.THE CUBESAT OUFTI-1The idea of using a satellite for amateur radio communication is not new: thefirst ham radio satellite OSCAR-1 has been launched in 1961 and OSCAR-7,launched in 1974, is still operational. Many satellites for radio amateurs arein low earth orbit and guarantee the communications all around the world:even on the International Space Station (ISS) there is a amateur radio stationand a new one has been recently added on the Columbus module. The reasonis simple: in normal atmospheric conditions the zone of visibility of a radiorepeater is around 50 Km, while the footprint of a satellite is much wider (orderof thousands Km): a satellite allows in this way the communication between twousers far away from each other and, even more important, it offers a repeaterto those who are to far away from any ground repeaters to have a traditionalair link.As a drawback, both the two users have to be in the satellite footprint and thetime for communicate could be short.During the last months, OUFTI-1 has been presented to the amateur radiocommunity and to other CubeSats developers [RD4] and it has been greetedenthusiastically.Galli Stefania 23 University of Liège
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Page 7 and 8: CONTENTS1 Introduction 132 The LEOD
Page 9 and 10: LIST OF FIGURES4.1 A typical 1-unit
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Page 15 and 16: CHAPTER2THE LEODIUM PROJECTThe LEOD
Page 17: CHAPTER3THE FLIGHT OPPORTUNITYThe E
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Page 25 and 26: CHAPTER5MISSION ANALYSISThe mission
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Page 31 and 32: CHAPTER 5.MISSION ANALYSISFigure 5.
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Page 35 and 36: CHAPTER 5.MISSION ANALYSIS• the s
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Page 41 and 42: CHAPTER 5.MISSION ANALYSIS• if m
Page 43 and 44: CHAPTER 5.MISSION ANALYSIS5.3.3 The
Page 45 and 46: CHAPTER 5.MISSION ANALYSISwhere ϑ
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CHAPTER 7only slow down the rotatio
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CHAPTER 8order to prevent any failu
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CHAPTER 8We have now the vector ˆN
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CHAPTER 8Here we add an important h
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CHAPTER 8Figure 8.5: Total power pr
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CHAPTER 8Figure 8.8: Total power an
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CHAPTER 88.4 Battery and operating
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CHAPTER 99.1 Passive thermal-contro
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CHAPTER 99.3 Nodes modelThe CubeSat
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CHAPTER 9where c p is the material
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CHAPTER 9We have now all the parame
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CHAPTER 9A typical layout of a Ther
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CHAPTER10COMMUNICATION SYSTEMThe co
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CHAPTER 10.COMMUNICATION SYSTEMstre
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CHAPTER 10.COMMUNICATION SYSTEM•
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CHAPTER 10.COMMUNICATION SYSTEMWe c
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CHAPTER11TESTSThe launch and space
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CHAPTER 11.TESTSof asking for some
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CHAPTER 11.TESTSThe random vibratio
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CHAPTER12FUTURE DEVELOPMENTSThe fea
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CHAPTER 12.FUTURE DEVELOPMENTSspace
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AcronymsAARACRACSADADCSASIAVUMBOLCC
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BIBLIOGRAPHY[1] Wiley J. Larson, Ja
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AcknowledgmentsI would like to than
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Mission Design for the CubeSat OUFTI-1

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