Mission Design for the CubeSat OUFTI-1

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CHAPTER 44.1 The CubeSat conceptDuring the last years, a complex process is taking place in the space industry: onthe one hand, there is a growing tendency for satellite to become larger, on theother hand, many miniaturized satellites are designed. In fact, from the hugespacecraft of Hubble Space Telescope launched in 1990 which weighed morethan 11 tons, there is an actual trend to reduce at most the size of the satellite:this reduces not only the costs connected to the launch but also those directlyimplied in the design and construction of the spacecraft. The miniaturizedsatellite can be classified according to their ’wet’ mass (including fuel) :• Minisatellite: wet mass between 100 Kg and 500 Kg. They are usuallysimple but they use the same technology as the bigger satellites and theyare often equipped with rockets for propulsion and attitude control.• Microsatellite: wet mass between 10 Kg and 100 Kg. The miniaturizationprocess begins to be important but sometimes they still use some kind ofpropulsion.• Nanosatellite: wet mass between 1 Kg and 10 Kg. Every component hasto be reduced in terms of mass and volume and no kind of propulsion isusually foreseen. They can be launched ’piggyback’, using excess capabilityon larger launch vehicle.• Picosatellite: wet mass between 0.1 Kg et 1 Kg. The miniaturizationprocess is maximum and many new technologies have to be used in orderto accomplish the requirements. They are launched ’piggyback’ with somepeculiar deployment system.These miniaturized satellites go toward many technical challenges, especiallyconcerning the attitude control and the electronic equipment, including thecommunication system: they need indeed to use more up-to-date technology,which often needs to be carefully tested and modified in order to be space hardenedand resistant to the outer space environment.The CubeSat design is an example of a Picosatellite with dimensions of10x10x10 cm and typically using commercial off-the-shelf electronic components.The concept was originally developed by the California Polytechnic StateUniversity and by the Stanford University, with Professor Robert Twiggs, andafterward it widely circulates among the academic world . At the moment, over60 University, high schools and industries are involved in the development ofCubeSats. Some of them are designing double and triple CubeSats: they can fitin the traditional deployment system but they can have more mass and volume.As a matter of fact, a CubeSat represents the best way to give some experienceGalli Stefania 20 University of Liège
CHAPTER 4.THE CUBESAT OUFTI-1Figure 4.1: A typical 1-unit CubeSat structureto students during their education: it can fit into the university’s budget and itcan be designed, tested and launched in two year, allowing student to participateto all the mission’s phases.Until some years ago, the most complex achievement for a CubeSat was to obtaina launch as the providers were often distrustful of a small satellite designedby students which was launched inside the same fairing as a much more expensivemission and which risked to damage the main satellite. More recently,thanks to the great success of CubeSat project among the universities all aroundthe world, some safe interfaces for CubeSats have been developed and the launchproviders are definitely favorable to use the free space to set into orbit this kindof Picosatellite. In fact, all the main launchers dispose now of a special interfacefor the ’piggyback’ launches. In order to fit into the deployment system and toguarantee the preservation not only of the main satellite but also of the otherCubeSat, the structure has to fulfills many requirements as explained in [AD4].The key requirement for a CubeSat are here summarized:• its dimensions must be 10x10x10 cm• it may not exceed 1 Kg mass• its center of mass must be within 2 cm of its geometric center• the CubeSat must not present any danger to neighboring CubeSats, to thelaunch vehicle or to the primary payload: all parts must remain attachedduring launch, ejection and operation and no pyrotechnics are allowed• whenever possible, the use of NASA or ESA approved material is recommended:this allow a reduction of out-gassing and contamination.• rails have to be anodized to prevent cold-welding and provide electricalisolation between the CubeSat and the deployment system. They alsoGalli Stefania 21 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 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
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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 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
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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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