Mission Design for the CubeSat OUFTI-1

More documents

Recommendations

Info

CHAPTER 12All these tasks will be accomplish with a tight cooperation between universityand industries: in particular, Thales-Alenia Space ETCA in Charleroi for theelectrical power subsystem, the Liège Space Center for the thermal control andthe choice of future payloads, Spacebel in Liège for the on board data handling,LuxSpace for the mission analysis, Open-Engineering in Liège for the attitudecontrol and V 2 i in Liège for the structure and configuration subsystem.Anyway, all these future developments need more information on the payload,not available at the moment. A satellite is in fact its payload and, withoutit, it hasn’t any reason to exist. All the design has to be conducted on thebase of payload’s requirements and in order to give him the best conditions toaccomplish its mission. The first and more important step is therefore to havea precise configuration of the D-STAR system and to know its limits. Only inthis way, we will be able to evaluate if the power produced is enough, if thedoppler effect without attitude control is too high and how much we need toshield the payload from radiations.12.1 Possible payloadsThe foreseen payloads of the future missions of LEODIUM Project deserve aseparate treatment. In fact, mass and power available on a CubeSat make thisevaluation quite complicate.Among the university departments, the interest is mainly concentrated on Micro-Electro-Mechanical Systems (MEMS) and on granular material. The former isparticularly suitable for a nanosatellite: so small actuators and sensors can infact be used to control the satellite and we can in this way test their behaviorin space and their resistance to external environment before employing them onmore ambitious missions.The ideal target for a CubeSat mission is in fact a technology demonstrationor testing a recently developed element. The project is cheap and its goal ismainly educational to give students hand-on experience: placing on a CubeSatnon space-tested elements that risk to cause the satellite failure is much lessdramatic than chance loosing a bigger mission. In fact, even if the mission fails,students have taken advantage of the acquired experience.Among the possible technology demonstration payloads, the most interestingseems to be some MEMS for attitude control system’s sensors and actuators,active antennas and thermal sensors and magnetometers.Also testing into space some active damping systems seems interesting: one ofthe main problems in space is in fact that the viscous damping of a structuredisappears and only the structural damping remains. As a result, structuresthat on the earth are sufficiently damped, in space need some added dampersto avoid excessive vibrations as well as damping systems are less effective intoGalli Stefania 112 University of Liège
CHAPTER 12.FUTURE DEVELOPMENTSspace. This kind of test has already been done into space: in particular ProfessorPreumont of Bruxelles University placed an active vibration damper on theSpace Shuttle to test it. Testing a miniaturized version of the same system ona CubeSat would have probably been much less expensive.The test of advanced solar cells is also a kind of mission target that perfectlyfits a CubeSat: their effective efficiency in orbit can be determined as well astheir hardness to radiations.Some nanosatellite missions are also used for testing micropropulsors but theycannot be launched using a Pico Orbital Deployer and finding a launch becomesmore complicate.Last but not least, a CubeSat can be equipped just like all the other satelliteswith a scientific payload on board. In this case, the most difficult task is to finda suitable instrument. Placing a camera and taking pictures of the earth is certainlya good idea on the educational point of view as the mission design wouldbe exactly like the one of a bigger satellite with all the requirement of pointingprecision and stability, but the scientific result wouldn’t be innovative: manyother satellites do the same thing but they employ cameras with much higherresolution. Depending on the orbit, the study of earth radiation environmentor of the gravitational and magnetic fields can also be interesting. Formationflight is another possibility but it demands much more resources as multiplesatellites are launched at the same time.Finally, a CubeSat is suitable for many different payloads but they need tohave compatible dimensions and weight: a dedicated design phase is thereforenecessary.Galli Stefania 113 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 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 47 and 48:
Page 49 and 50:
CHAPTER 5.MISSION ANALYSISA four ye
Page 51 and 52:
Page 53 and 54:
Page 55:
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
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
Page 111: CHAPTER12FUTURE DEVELOPMENTSThe fea
Page 117 and 118: AcronymsAARACRACSADADCSASIAVUMBOLCC
Page 119 and 120: BIBLIOGRAPHY[1] Wiley J. Larson, Ja
Page 121: AcknowledgmentsI would like to than
show all

Mission Design for the CubeSat OUFTI-1

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?