Mission Design for the CubeSat OUFTI-1

More documents

Recommendations

Info

CHAPTER 5To conclude, we can say that with a footprint’s length of 3128 Km, OUFTI-1can cover the entire western Europe at once. Anyway, also at 350 Km altitudewith a footprint’s length of 1580 Km, the satellite passing over Paris can keep incontact an amateur radio operator in Lisbon with one in Stockholm. Concerningthe Area Coverage Rate, it depends on the instrument dwell time and for anomnidirectional antenna it hasn’t any meaning.The Area Access Rate is estimated through the following formula:AAR = 1.49 · 108 sin (λ)T5.6 Communication time={11660 Km2s6073 Km2s(1200Km)(350Km)(5.25)Directly connected to the earth coverage, we need to consider the communicationtime with the ground station in Liège. In fact, this is one of the drivingrequirements for the OUFTI-1 design. We are dealing with an amateur radiosatellite: as the community of amateur radio in almost uniformly distributedall around the world, we chose to favor the Belgian amateur radio operators.In this way we also maximize the time available for communication with ourground station in Liège.But the same problem reappears in this case too: we cannot impose the orbitalparameters and specifically the argument of perigee and the right ascension onascending node. Hence we can only analyze the best and the worst situationand verify if the time is enough to satisfy the mission requirements.The worst case is represented in figure 5.6: as the perigee is over Belgium, thespeed of OUFTI-1 passing over the ground station is extremely high and thetime consequently really short.In the worst case we have an access time of 30 min/day. It seems to besufficient but this time is not continuous: the maximum continuous access timein the worst case is about 8 minutes.The best case is instead when the apogee is over Belgium and its representedin figure 5.6: in this case the time available for communication is much higheras the satellite is passing slowly over the ground station.In the best case we have an access time of 104 min/day with a maximumcontinuous time of 17 minutes.Galli Stefania 52 University of Liège
CHAPTER 5.MISSION ANALYSISFigure 5.26: Worst case for communication: the white line represents thesatelite’s access to the ground stationFigure 5.27: Best case for communication: the white line represents the satelite’saccess to the ground stationGalli Stefania 53 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: CHAPTER 5.MISSION ANALYSISFigure 5.
Page 49 and 50: CHAPTER 5.MISSION ANALYSISA four ye
Page 51: CHAPTER 5.MISSION ANALYSISFigure 5.
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
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 and 112:
CHAPTER12FUTURE DEVELOPMENTSThe fea
Page 113:
CHAPTER 12.FUTURE DEVELOPMENTSspace
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?