Mission Design for the CubeSat OUFTI-1

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CHAPTER 5Hence, the perigee and apogee radius can be expressed as:r p = r (ϑ = 0) =r p = r (ϑ = π) =p1 + ep1 − e= a (1 − e) (5.9)= a (1 + e) (5.10)We would also like to find a connection between the time and the true anomalyin order to know the necessary time to go from a point to another: if this isextremely simple for a circular orbit where the speed is constant, for an ellipticorbit it’s a bit more complicate.To solve this, Kepler introduced the quantity M, called mean anomaly, whichrepresents the fraction of an orbit period which has elapsed since perigee, expressedas an angle:M − M 0 = n (t − t 0 ) (5.11)where n, called mean motion, is the average angular velocity.But this method gives only an average position and velocity. To have a moreprecise value, we need to define the eccentric anomaly E. Shown in fig.5.9,it’s the angle between the direction of perigee and the current position of thesatellite projected onto the ellipse’s circumscribing circle perpendicularly to themajor axis, measured at the center of the ellipse.Figure 5.9: Eccentric and mean anomalies.It can be connected to the true anomaly with the relation:( ) √ ( )ϑ 1 + e Etan =2 1 − e tan 2(5.12)Once the eccentric anomaly is know, the time comes from the following timelaw:Galli Stefania 36 University of Liège
CHAPTER 5.MISSION ANALYSISt − t 0 =√a 35.2.2 The orbit of OUFTI-1µ(E − esin (E)) (5.13)For the orbital analysis, we used some home-maid Matlab programs and theSTK software.As above mentioned, the following parameters are assigned:• Perigee altitude: r p =350 Km• Apogee altitude: r a =1200 Km• Inclination : i=71 ◦In order to have an idea of the orbit, we represented its ground track infig.5.10 and a tridimentional view in figure 5.11.Figure 5.10: OUFTI-1 orbit representation for 12 hours orbit(STK)Galli Stefania 37 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: CHAPTER 5.MISSION ANALYSIS• the s
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 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
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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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