Mission Design for the CubeSat OUFTI-1

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7 Attitude Control System 637.1 Inertia properties . . . . . . . . . . . . . . . . . . . . . . . . . . 647.2 Disturbing torques . . . . . . . . . . . . . . . . . . . . . . . . . 667.3 Attitude control hardware . . . . . . . . . . . . . . . . . . . . . 718 Power system 738.1 Eclipse’s duration . . . . . . . . . . . . . . . . . . . . . . . . . . 748.2 Configuration and solar cells . . . . . . . . . . . . . . . . . . . . 778.3 Power produced . . . . . . . . . . . . . . . . . . . . . . . . . . . 798.3.1 Elliptic orbit with starting orbital elements . . . . . . . . 798.3.2 Elliptic orbit with orbital elements after one year missionand circular orbit . . . . . . . . . . . . . . . . . . . . . . 818.3.3 Parametric study . . . . . . . . . . . . . . . . . . . . . . 828.4 Battery and operating modes . . . . . . . . . . . . . . . . . . . 849 Thermal-control system 859.1 Passive thermal-control . . . . . . . . . . . . . . . . . . . . . . . 869.2 Analytic temperature determination . . . . . . . . . . . . . . . . 879.3 Nodes model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 889.3.1 Representation . . . . . . . . . . . . . . . . . . . . . . . 889.3.2 Equivalent resistances . . . . . . . . . . . . . . . . . . . 899.3.3 Hot and cold case . . . . . . . . . . . . . . . . . . . . . . 939.4 Thermal results for OUFTI-1 . . . . . . . . . . . . . . . . . . . 9310 Communication system 9710.1 Communication hardware . . . . . . . . . . . . . . . . . . . . . 9810.2 Link budget . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9910.3 Backup telemetry and ground station . . . . . . . . . . . . . . . 10311 Tests 10511.1 Test philosophy and facilities . . . . . . . . . . . . . . . . . . . . 10611.2 Mechanical tests . . . . . . . . . . . . . . . . . . . . . . . . . . 10711.3 Environmental tests . . . . . . . . . . . . . . . . . . . . . . . . . 11012 Future Developments 11112.1 Possible payloads . . . . . . . . . . . . . . . . . . . . . . . . . . 11213 Conclusions 115References 1198
LIST OF FIGURES4.1 A typical 1-unit CubeSat structure . . . . . . . . . . . . . . . . 215.1 Vega launcher . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2 Vega typical mission profile: altitude . . . . . . . . . . . . . . . 275.3 Vega typical mission profile: relative speed . . . . . . . . . . . . 275.4 Vega performances: payload mass . . . . . . . . . . . . . . . . . 285.5 Vega: spacecraft preparation and checkout phase . . . . . . . . 295.6 Vega: spacecraft hazardous operations phase . . . . . . . . . . . 305.7 Vega: combined operations phase . . . . . . . . . . . . . . . . . 315.8 Orbital Parameters . . . . . . . . . . . . . . . . . . . . . . . . . 345.9 Eccentric and mean anomalies. . . . . . . . . . . . . . . . . . . 365.10 OUFTI-1 orbit representation for 12 hours orbit(STK) . . . . . 375.11 OUFTI-1: orbit’s tridimentional view. . . . . . . . . . . . . . . 385.12 OUFTI-1 orbit: true, eccentric and mean anomaly . . . . . . . . 395.13 Earth oblateness and not uniform mass effect . . . . . . . . . . 415.14 Aerodynamic drag acceleration for the first day mission. . . . . 425.15 Solar pressure acceleration for the first day mission . . . . . . . 445.16 Orbit variation over a year. . . . . . . . . . . . . . . . . . . . . 455.17 Semi-major axis variation over a year. . . . . . . . . . . . . . . . 455.18 Eccentricity variation over a year. . . . . . . . . . . . . . . . . . 465.19 Perigee and apogee altitude variation over a year. . . . . . . . . 465.20 Inclination variation over a year. . . . . . . . . . . . . . . . . . . 475.21 Right ascension of ascending node variation over a year . . . . . 475.22 Argument of perigee variation over a year . . . . . . . . . . . . 485.23 Evolution altitude until the end of life for the elliptic orbit . . . 485.24 Evolution of altitude until the end of life for the circular orbit . 495.25 Field of view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 515.26 Worst case for communication . . . . . . . . . . . . . . . . . . . 535.27 Best case for communication . . . . . . . . . . . . . . . . . . . . 535.28 Radiation dose for the OUFTI-1 elliptical orbit . . . . . . . . . 555.29 Radiation dose for the OUFTI-1 circular orbit . . . . . . . . . . 556.1 CubeSat-Kit structure skeletonized and solid-walls . . . . . . . . 589
Page 3: Space is probably the main symbol o
Page 7: CONTENTS1 Introduction 132 The LEOD
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.
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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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