Mission Design for the CubeSat OUFTI-1

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CHAPTER 11• Acoustic vibrations at very high frequency (f
CHAPTER 11.TESTSThe random vibrations are performed with the intensity indicated in figure11.2: it has to be applied along each of three axis.Figure 11.2: Qualification level for random vibrationsThe test duration is 4 minutes.The shock test, and its equivalent sinus test, is performed with the ShockResponse Spectrum (SRS) shown in figure 11.3 at severity level 2 for the amplificationfactor Q=10, corresponding to a damping ξ = 0.05. It has to beexecuted three times along each of three axis.Figure 11.3: Shock Response Spectrum for Q=10.qualification is the severity level 2The level prescripted forGalli Stefania 109 University of Liège
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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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Page 58 and 59: CHAPTER 66.1 Pumpkin structureThe s
Page 60 and 61: CHAPTER 6Figure 6.2: ISIS structure
Page 62 and 63: CHAPTER 6Figure 6.3: P-POD: deploym
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: CHAPTER 11.TESTSof asking for some
Page 111 and 112: CHAPTER12FUTURE DEVELOPMENTSThe fea
Page 113: CHAPTER 12.FUTURE DEVELOPMENTSspace
Page 117 and 118: AcronymsAARACRACSADADCSASIAVUMBOLCC
Page 119 and 120: BIBLIOGRAPHY[1] Wiley J. Larson, Ja
Page 121: AcknowledgmentsI would like to than
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Mission Design for the CubeSat OUFTI-1

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