Mission Design for the CubeSat OUFTI-1
Mission Design for the CubeSat OUFTI-1 Mission Design for the CubeSat OUFTI-1
CHAPTER 7This rough estimation is extremely useful to have an idea of the maximumintensity of each perturbing couple but, as their directions are unknown, wecannot add them to have the rotation rate of the satellite.We made therefore a simulation for one day of the disturbing couples and wecalculate the cumulated angular momentum. A priori, a longer simulation couldbe possible but the absence of attitude control causes the satellite to turn abouttheir axis and a really small time step is needed the have reliable results: thecomputing time becomes quick huge and difficult to handle.If we accept the hypothesis that the satellite is not turning, we have theresults shown in figures 7.2 and 7.3.Figure 7.2: Gravity gradient couple for one orbit in case of non updated configurationGalli Stefania 68 University of Liège
CHAPTER 7.ATTITUDE CONTROL SYSTEMFigure 7.3: Aerodynamic couple for one orbit in case of non updated configurationGalli Stefania 69 University of Liège
- 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 and 52: CHAPTER 5.MISSION ANALYSISFigure 5.
- Page 53 and 54: 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 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
CHAPTER 7.ATTITUDE CONTROL SYSTEMFigure 7.3: Aerodynamic couple <strong>for</strong> one orbit in case of non updated configurationGalli Stefania 69 University of Liège
Change language