Mission Design for the CubeSat OUFTI-1

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AcronymsAARACRACSADADCSASIAVUMBOLCCRCSGCSLD-STAREIRPEOLESAESTECFOVGENSOGSEIAAISSJARLLARESLEODIUMOUFTIPMACSPODRDSEBSELArea Access RateArea Coverage RateAttitude Control SystemApplicable DocumentAttitude Determination and Control SystemAgenzia Saziale Italiana (Italian Space Agency)Attitude and Vernier Upper ModuleBeginning of LifeCorner Cube ReflectorCentre Spatial Guyanaise (Guyana Space Centre)Centre Spatial de Liège (Liège Space Center)Digital Smart Technology for Amateur RadioEffective Isotropic Radiated PowerEnd Of LifeEuropean Space AgencyEuropean Space Technology Research CentreField Of ViewGlobal Educational Network for Satellite OperationsGround Support EquipmentInstantaneous Access AreaInternational Space StationJapan Amateur Radio LeagueLAser RElativity SatelliteLancement En Orbite de Démonstations Innovantesd’une Université Multidisciplinaire(Launch into Orbit of Innovative Demonstrationsof a Multidisciplinary University)Orbiting Utility For Telecommunication InnovationPassive Magnetic Attitude Control SystemPicosatellite Orbital DeployerReference DocumentSingle Event BurnoutSingle Event Latchup117
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Space is probably the main symbol o
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CONTENTS1 Introduction 132 The LEOD
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LIST OF FIGURES4.1 A typical 1-unit
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LIST OF TABLES5.1 Comparison betwee
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CHAPTER2THE LEODIUM PROJECTThe LEOD
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CHAPTER3THE FLIGHT OPPORTUNITYThe E
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CHAPTER 44.1 The CubeSat conceptDur
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CHAPTER 4have to be smooth and thei
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CHAPTER5MISSION ANALYSISThe mission
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CHAPTER 5.MISSION ANALYSIS5.1.1 Typ
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CHAPTER 5.MISSION ANALYSISIt can be
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CHAPTER 5.MISSION ANALYSISFigure 5.
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CHAPTER 5.MISSION ANALYSIS5.2 The o
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CHAPTER 5.MISSION ANALYSIS• the s
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CHAPTER 5.MISSION ANALYSISt − t 0
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CHAPTER 5.MISSION ANALYSISIn figure
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CHAPTER 5.MISSION ANALYSIS• if m
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CHAPTER 5.MISSION ANALYSIS5.3.3 The
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CHAPTER 5.MISSION ANALYSISwhere ϑ
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CHAPTER 5.MISSION ANALYSISA four ye
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CHAPTER 66.1 Pumpkin structureThe s
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CHAPTER 6Figure 6.2: ISIS structure
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CHAPTER 6Figure 6.3: P-POD: deploym
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CHAPTER 77.1 Inertia propertiesBefo
Page 66 and 67: CHAPTER 7I x = I x,cube + I x,M + I
Page 68 and 69: CHAPTER 7This rough estimation is e
Page 70 and 71: CHAPTER 7Otherwise, an orbit simula
Page 72 and 73: CHAPTER 7only slow down the rotatio
Page 74 and 75: CHAPTER 8order to prevent any failu
Page 76 and 77: CHAPTER 8We have now the vector ˆN
Page 78 and 79: CHAPTER 8Here we add an important h
Page 80 and 81: CHAPTER 8Figure 8.5: Total power pr
Page 82 and 83: CHAPTER 8Figure 8.8: Total power an
Page 84 and 85: CHAPTER 88.4 Battery and operating
Page 86 and 87: CHAPTER 99.1 Passive thermal-contro
Page 88 and 89: CHAPTER 99.3 Nodes modelThe CubeSat
Page 90 and 91: CHAPTER 9where c p is the material
Page 92 and 93: CHAPTER 9We have now all the parame
Page 94 and 95: CHAPTER 9A typical layout of a Ther
Page 97 and 98: CHAPTER10COMMUNICATION SYSTEMThe co
Page 99 and 100: CHAPTER 10.COMMUNICATION SYSTEMstre
Page 101 and 102: CHAPTER 10.COMMUNICATION SYSTEM•
Page 103 and 104: CHAPTER 10.COMMUNICATION SYSTEMWe c
Page 105 and 106: CHAPTER11TESTSThe launch and space
Page 107 and 108: CHAPTER 11.TESTSof asking for some
Page 109 and 110: CHAPTER 11.TESTSThe random vibratio
Page 111 and 112: CHAPTER12FUTURE DEVELOPMENTSThe fea
Page 113: CHAPTER 12.FUTURE DEVELOPMENTSspace
Page 118 and 119: CHAPTER 13SEPSEUSPENVISSRSSSOVEGASi
Page 120 and 121: CHAPTER 13[RD1] Stefania Galli, Jon
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Mission Design for the CubeSat OUFTI-1

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