Mission Design for the CubeSat OUFTI-1

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6.2 ISIS structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.3 P-POD: deployment system for three CubeSats . . . . . . . . . 627.1 Example of OUFTI-1 configuration . . . . . . . . . . . . . . . . 647.2 Gravity gradient couple in case of non updated configuration . . 687.3 Aerodynamic couple in case of non updated configuration . . . . 697.4 Gravity gradient couple in case of updated configuration . . . . 707.5 Gravity gradient couple in case of updated configuration . . . . 708.1 Reference sistems . . . . . . . . . . . . . . . . . . . . . . . . . . 748.2 Sun rays direction on the ecliptic plane . . . . . . . . . . . . . . 758.3 Sun rays direction projected on the orbit plane. . . . . . . . . . 768.4 Eclipse duration as a function of earth anomaly . . . . . . . . . 778.5 Total power produced: simulation over one year orbit. . . . . . . 808.6 Integrated power: simulation over one year orbit . . . . . . . . . 808.7 Total power and integrated power for the orbital parameters afterone year mission . . . . . . . . . . . . . . . . . . . . . . . . . . . 818.8 Total power and integrated power for the circular orbit with Ω =0 and ω = 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 828.9 Total power and integrated power for Ω = 90 ◦ and ω = 0 ◦ . . . . 838.10 Total power and integrated power for Ω = 0 ◦ and ω = 90 ◦ . . . . 838.11 Total power and integrated power for Ω = 90 ◦ and ω = 90 ◦ . . . 839.1 Nodes model for thermal analysis . . . . . . . . . . . . . . . . . 899.2 Equilibrium for radiative heat exchange . . . . . . . . . . . . . . 909.3 Radiative equivalent resistance . . . . . . . . . . . . . . . . . . . 919.4 Typical Thermal Excel layout: operating case whit black coating 9410.1 Communication system block diagram . . . . . . . . . . . . . . 9810.2 Detailed link budget for the satellite at the apogee, 5 ◦ elevation 10210.3 Downlink link budget . . . . . . . . . . . . . . . . . . . . . . . . 10311.1 Qualification level test for sinus vibrations . . . . . . . . . . . . 10811.2 Qualification level for random vibrations . . . . . . . . . . . . . 10911.3 Shock Response Spectrum . . . . . . . . . . . . . . . . . . . . . 10910
LIST OF TABLES5.1 Comparison between the two possible orbits . . . . . . . . . . . 396.1 CubeSat Kit mass . . . . . . . . . . . . . . . . . . . . . . . . . . 596.2 ISIS structure mass . . . . . . . . . . . . . . . . . . . . . . . . . 608.1 Solar cells mechanical properties . . . . . . . . . . . . . . . . . . 788.2 Solar cells electrical and thermal properties . . . . . . . . . . . . 788.3 Elliptic orbit with orbital parameters after one year . . . . . . . 818.4 Operating modes . . . . . . . . . . . . . . . . . . . . . . . . . . 849.1 Surface thermal properties . . . . . . . . . . . . . . . . . . . . . 879.2 Equilibrium temperatures . . . . . . . . . . . . . . . . . . . . . 879.3 Structure properties . . . . . . . . . . . . . . . . . . . . . . . . . 929.4 Temperatures . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9410.1 Communication system parameters . . . . . . . . . . . . . . . . 10110.2 Link budget at 1200 Km altitude, 5 ◦ elevation . . . . . . . . . . 10111.1 Thermal vacuum qualification test for the PFM. . . . . . . . . . 11011.2 Thermal cycling qualification test . . . . . . . . . . . . . . . . . 11011
Page 3: Space is probably the main symbol o
Page 7 and 8: CONTENTS1 Introduction 132 The LEOD
Page 9: LIST OF FIGURES4.1 A typical 1-unit
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
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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
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CHAPTER 7I x = I x,cube + I x,M + I
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CHAPTER 7This rough estimation is e
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CHAPTER 7Otherwise, an orbit simula
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CHAPTER 7only slow down the rotatio
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CHAPTER 8order to prevent any failu
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CHAPTER 8We have now the vector ˆN
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CHAPTER 8Here we add an important h
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CHAPTER 8Figure 8.5: Total power pr
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CHAPTER 8Figure 8.8: Total power an
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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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