Mission Design for the CubeSat OUFTI-1

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CHAPTER 6Figure 6.2: ISIS structureIn table 6.2 the mass balance is reported: the primary structure is composedby the chassis and the side frames, the secondary one by all the internal stacksand spacers.Table 6.2: ISIS structure massMass [g]Primary structure 171Secondary structure 35Total 206The mass is much higher than in the previous case: 206 g versus 166 g. Themain reason is that the ISIS structure is completely solid-walls. If we considerthe solid-walls structure of Pumpkin we see that the ISIS one is lighter: thisprobably comes from having used everywhere the same material with a betterratio between density and mechanical properties.Anyway, in our case this structure is not advantageous respect to the skeletonizedone of CubeSat-Kit.As said in the previous paragraph, the fact that the the ISIS structure has neverbe sent into orbit make us decide to buy the Pumpkin structure.Galli Stefania 60 University of Liège
CHAPTER 6.STRUCTURE AND DEPLOYMENT6.3 Deployment SystemThe deployment system is designed to provide a standard secondary payloadinterface between the CubeSats and the launch vehicle. Its key features are, onthe one hand, to protect the launch vehicle and its main passenger from anymechanical, electrical or electromagnetic interference from the CubeSats in theevent of a catastrophic picosatellite failure and, on the other hand, to releasethe CubeSats with a minimum spin and without any collision.The fact that the structure for a CubeSat is fixed allows the development of standarddeployment systems, usually called Picosatellite Orbital Deployer (POD).Currently there are four different deployment system:• P-POD: Poly-Picosatellite Orbital Deployer. Developed by the StanfordUniversity (Stanford, CA, USA) and the California Polytechnic Institute(San Luis Obispo, CA, USA), it holds three single CubeSats stacked ontop on each other• T-POD: Tokyo-Picosatellite Orbital Deployer. Developed by the TechnicalUniversity of Tokyo (Japan), it holds a single CubeSat• X-POD: eXperimental-Push Out Deployer. Developed by the Space FlightLaboratory (SFL) of the University of Toronto Institute of AeroSpace(UTIAS) (Canada), it’a custom, independent separation system for threeCubeSats and can be tailored for satellites of different size• SPL: Single-picosatellite Launcher. Developed by Astrofein (Berlin, Germany)it’a a custom deployment system for a single CubeSatAs explained in [RD2], the deployment system for the Vega maiden flight issupplied by the Educational Office of the European Space Agency. Among thepossible choices, they selected the two standard flight-proven POD of the CaliforniaState University (P-POD) and of Toronto University (X-POD). Each oneof them can carry three CubeSats fastened with an electrically activated springloadedmechanism. After a signal is sent from the launch vehicle to release themechanism, the spring-loaded door is open and the CubeSats are pushed out bythe main spring along guidance rails, ejecting them into orbit with a separationspeed of few m/s. The door open anywhere between 90 ◦ and 260 ◦ , measuredfrom its closed position, depending on how the POD is mounted. The two foreseenPOD have the only main difference that the X-POD has an independentrelease mechanism for the spring deployer and feedback to indicate that thedeployment has taken place.The POD is a rectangular box made of high-strength Aluminium 7075-T73.It’s also coated Teflon-impregnated anodization to prevent cold-welding andGalli Stefania 61 University of Liège
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Space is probably the main symbol o
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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 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
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 and 108: CHAPTER 11.TESTSof asking for some
Page 109 and 110: 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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