Master Thesis - OUFTI-1

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5.6 Summary Through this chapter, a complete FE analysis of OUFTI-1 was performed. First, the modeling strategy used to represent each component of the satellite in the FE model, was described accurately. Then, a static analysis was performed. This analysis allows to conclude that OUFTI-1 withstands the quasi-static loads imposed by Vega in the worst case conguration. So, the structural integrity of the satellite in static state is ensured. The modal analysis led to results which satisfy ESA requirements on the dynamic behavior of the Vega payloads, and showed that the most critical parts of the satellite are its electronic cards, which are strongly excited in the rst modes. Next year, several tests will have to be performed to validate this model. Finally, the procedure to realize a random vibration analysis was drawn. Each step of this analysis was presented and resolved. However, due to an unsolved problem encountered with the Samcef software, this analysis could not be realize for this thesis. Once this analysis will be performed and when a complete engineering model of the satellite will be availble, qualication tests will have to be performed (strictly following the ESA procedure [61]) to denitely validate the satellite and to send them to Kourou for its launch. 119
Chapter 6 Conclusions This master thesis developed the structural design and dynamic analysis of OUFTI-1. The main objectives were to design a new reliable support for the batteries, which fullls all the requirements imposed by several subsystems, and to create an accurate FE dynamic modeling procedure for the electronic cards. Through this chapter, the results obtained during all the year, will be summarized. Then, perspectives for future works will be highlighted. Finally, the parallel activities linked to the project, will be briey exposed. 6.1 Summary of the accomplished work The rst chapter of this thesis consisted in a general presentation of the project. The CubeSat concept was introduced to allow to the profane to understand what is a CubeSat and what are the principal requirements and restrictions which are imposed to this particular type of satellite. Then, the genesis of the OUFTI-1 project was presented to expose the guideline of the project from its starting point to the level at which this thesis started. The launch opportunity oered by the ESA, was also discussed. Finally, the mission payloads and the OUFTI team were described to nalize this overall view of the OUFTI-1 project. Chapter 2 presented the general ight system conguration. The reference frame used to locate precisely each component of the CubeSat, was dened. Then, each part of OUFTI-1 was presented in a global understanding approach. The technical constraints which led to this particular organization, were highlighted, and the methods which will be used to x the dierent components together, were exposed. Finally, general physical and mechanical properties, including: the CoG location, the inertia properties and the mass budget, were 120
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University of Liège Faculty of App
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Abstract OUFTI-1, standing for "Orb
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3.4 Initial idea . . . . . . . . .
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List of Figures 1.1 The Pumpkin's C
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4.18 MAC matrix using the simple me
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List of Acronyms ADCS Al AlNiCo ASI
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Thesis outline This thesis focuses
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of larger satellites. So, the CubeS
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1.2 OUFTI-1 project 1.2.1 Genesis O
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• XatCobeo (Vigo - Spain): Develo
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Chapter 2 OUFTI-1: Flight system co
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Figure 2.2: Product tree of OUFTI-1
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2.3.2 Solar panels The armor panels
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• We do not want to drill or manu
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In our case, because of the limited
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Figure 2.13: Magnetic eld obtained
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Figure 2.17: Pictures of the ADCS c
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consider the possibility of oshorin
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Figure 2.20: Exploded view of OUFTI
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I xx , I yy and I zz are called the
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Subsystem: Structure & Conguration
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Subsystem: Thermal Control Parts Co
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Chapter 3 Design of a new support f
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Figure 3.3: Batteries during and af
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The concept is the following one: F
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A test under vacuum conditions was
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Thermal Expansion (CTE) of the mate
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Figure 3.9: Classication by density
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The last property to determine is t
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• So, it was decided to use two t
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is to prevent the batteries' bulge.
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• Then, the thermostats, that wil
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Figure 3.23: Schematics of the cove
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• Other components, including the
Page 69 and 70: 3.9.3 Dynamic behavior Finally, it
Page 71 and 72: 3.10 Summary Through this chapter,
Page 73 and 74: Chapter 4 Electronic cards dynamic
Page 75 and 76: Figure 4.1: Example of manufacturin
Page 77 and 78: Figure 4.4: Illustration of the exp
Page 79 and 80: Figure 4.5: MAC between the two mod
Page 81 and 82: • Global mass/stiness smearing me
Page 83 and 84: 4.2.6 Modeling of the chassis A gen
Page 85 and 86: Q = ω k = 1 ω b − ω a 2 ζ ⇒
Page 87 and 88: Their study was based on the fact t
Page 89 and 90: Figure 4.14: Example of spacecraft
Page 91 and 92: Figure 4.15: Location of measuremen
Page 93 and 94: Figure 4.18: MAC matrix using the s
Page 95 and 96: 4.3.6 Application of the local mass
Page 97 and 98: ρ P C 104 connector = 10.12 × 10
Page 99 and 100: According to this particular shape,
Page 101 and 102: This is due to the fact that this c
Page 103 and 104: environment. Then, this model is ex
Page 105 and 106: 5.2.4 Antenna support For the anten
Page 107 and 108: Components Young's moduli (GP a) Po
Page 109 and 110: Components Young's moduli (GP a) Po
Page 111 and 112: 5.3 Static analysis As described in
Page 113 and 114: Figure 5.9: Illustration of the com
Page 115 and 116: Figure 5.11: Maximal Von Mises stre
Page 117 and 118: Figure 5.12: First mode of OUFTI-1
Page 119: Figure 5.15: Precise PSD of Vega [5
Page 123 and 124: provided for each method used. We h
Page 125 and 126: last versions of the Verication Con
Page 127 and 128: [13] Ph. LEDENT. "Design and Implem
Page 129 and 130: [40] "Dejond - Aluminum Catalog ".
Page 131 and 132: Appendix A Schemas of solar panels
Page 133 and 134: Appendix B Schemas of electronic ca
Page 135 and 136: Appendix C Fixations of the endless
Page 137 and 138: Appendix D Datasheet of the battery
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Master Thesis - OUFTI-1

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