Mission Design for the CubeSat OUFTI-1

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CHAPTER 6Figure 6.3: P-POD: deployment system for three CubeSatsto provide a smooth guiding surface for the CubeSats during deployment. Adeployment sensor send telemetry data to the launcher: the switch is wired asa normally closed circuit and, when the door is open, the circuit opens. Thisguarantees that the door remains close until the CubeSats are deployed.Currently negotiations are going on between the Educational Office and thePOD suppliers: the final choice has’t been communicated yet but this doesn’tchange anything in the CubeSat development as both meet the same standard.Galli Stefania 62 University of Liège
CHAPTER7ATTITUDE CONTROL SYSTEMThe Attitude Control System (ACS) stabilizes the spacecraft and orients it indesired directions despite to the external disturbing forces acting on it. Actually,it’s part of a more complex system: the Attitude Determination andControl System (ADCS) but, in the case of OUFTI-1, speaking about attitudedetermination is inappropriate as it won’t be on board.An ADCS needs in fact sensors and actuator with the consequent mass andpower needed: this is often incompatible with a CubeSat.The incompatibility with OUFTI-1 doesn’t come much from the mass requirementas we expect to fulfill it but from the power. As explained in chapter 10,the power produced in orbit is low because of the limited solar arrays surfaceand just enough to guarantee a good communication when the satellite is atthe apogee. Furthermore, we intend to provide OUFTI-1 with omni-directionalantennas: in this context, it does not need a priori to point in a specific directionand may gently tumble about all three axes. Therefore we opt for twopossible solutions: not having any kind of ACS or have a totally passive ACSwith the goal of slowing down its rotation rate due to disturbing torques and ofguaranteeing an acceptable equilibrium position.63
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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
Page 11: LIST OF TABLES5.1 Comparison betwee
Page 15 and 16: CHAPTER2THE LEODIUM PROJECTThe LEOD
Page 17: CHAPTER3THE FLIGHT OPPORTUNITYThe E
Page 20 and 21: CHAPTER 44.1 The CubeSat conceptDur
Page 22 and 23: CHAPTER 4have to be smooth and thei
Page 25 and 26: CHAPTER5MISSION ANALYSISThe mission
Page 27 and 28: CHAPTER 5.MISSION ANALYSIS5.1.1 Typ
Page 29 and 30: CHAPTER 5.MISSION ANALYSISIt can be
Page 31 and 32: CHAPTER 5.MISSION ANALYSISFigure 5.
Page 33 and 34: CHAPTER 5.MISSION ANALYSIS5.2 The o
Page 35 and 36: CHAPTER 5.MISSION ANALYSIS• the s
Page 37 and 38: CHAPTER 5.MISSION ANALYSISt − t 0
Page 39 and 40: CHAPTER 5.MISSION ANALYSISIn figure
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
Page 49 and 50: CHAPTER 5.MISSION ANALYSISA four ye
Page 55: CHAPTER 5.MISSION ANALYSISFigure 5.
Page 58 and 59: CHAPTER 66.1 Pumpkin structureThe s
Page 60 and 61: CHAPTER 6Figure 6.2: ISIS structure
Page 64 and 65: 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
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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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