Mission Design for the CubeSat OUFTI-1

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CHAPTER 5Figure 5.11: OUFTI-1: orbit’s tridimentional view. Optimum case: the subsatellitepoint at apogee is at the same latitude as Liège.Given a perigee of 350 Km and an apogee of 1200 Km altitude, we calculatedall the above mentioned parameters:• semi-major axis: a = 7153.14Km• eccentricity: e = 0.0594• angular momentum: h = 5.33 · 10 4 Km2s• orbit parameter: p = 7127.7Km• energy: E = −27.8 Km2s 2• period: T = 6020.8s = 100.35min• perigee speed: v p = 7.922 Kms• apogee speed: v a = 7.034 Kms• mean motion: n = 14.35 revdayGalli Stefania 38 University of Liège
CHAPTER 5.MISSION ANALYSISIn figure 5.12 the true, eccentric and mean anomaly are represented: as theorbit is elliptic, they have different evolutions.Figure 5.12: OUFTI-1 orbit: true, eccentric and mean anomaly as a functionof time over a periodJust to have an idea of the possible circular orbit at 350 Km altitude, acomparison is reported in table 5.1.Table 5.1: Comparison between the two possible orbits350x1200 Km 350x350 KmSemi-major axis a (Km) 7153.14 6728.14Eccentricity e 0.0594 0Energy E(Km 2s 2 ))-27.8 -29.6(Perigee speed v Kmp(7.922 7.697sApogee spped v Km)a 7.034 7.697sPeriod T (min) 100.35 91.53The most important difference between the two orbit is the speed: in fact,in order to have a good communication, we would like to have a satellite passingover the ground station as slowly as possible. This reduces in fact the dopplereffect and, even more important, increases the time during which the satelliteis in the the ground station’s field of view.As the link budget guarantees a sufficient signal-to-noise level at 1200 Km altitude(seechapter 10), we prefer the elliptic orbit with the apogee over thenorthern hemisphere at the mission’s beginning.Galli Stefania 39 University of Liège
Page 3: Space is probably the main symbol o
Page 7 and 8: CONTENTS1 Introduction 132 The LEOD
Page 9 and 10: 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: CHAPTER 5.MISSION ANALYSISt − t 0
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 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
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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
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Page 80 and 81: CHAPTER 8Figure 8.5: Total power pr
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Page 84 and 85: CHAPTER 88.4 Battery and operating
Page 86 and 87: 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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