Master Thesis - OUFTI-1

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Figure 5.10: Displacements of OUFTI-1 In Figure 5.10, it can be seen that the maximal displacements of OUFTI-1 are along the Z axis, which is the longitudinal direction of the P-POD. More particularly, it is the center of electronic cards which presents the greatest displacement. This is in complete accordance with the loading state. Indeed, the structure supports the greatest acceleration along this particular axis. In addition, it can be noted that the base and end plates present some deformations at the feet location, which are due to the boundary conditions and to the loads applied to them. In Figure 5.11, it can be seen that the maximal Von Mises stress appears around the feet of the end plate. This is, once again, in accordance with the conditions applied. Indeed, these feet are clamped, which is a the strongest restrictive constraint. 113
Figure 5.11: Maximal Von Mises stress inside OUFTI-1 According to the reference [59], it is possible to dene a MoS for the entire satellite. This calculation is performed in Equation 5.3.3. where: MoS = allowable load (applied load) − SF − 1 (5.3.3) • allowable load: Allowable load under specied functional conditions (e.g., yield, buckling, ultimate) • applied load: Computed or measured load under dened load condition (design loads) • SF : Safety factor applicable to the specied functional conditions including the specied load conditions (e.g., yield, buckling, ultimate) For OUFTI-1, the maximal Von Mises stress appears in the end plate, which is made of Al − 5052 H32. This material has a yield stress of 162 MP a, the maximal applied stress is 101.97 MP a and the SF used for this study is 2. So, the value nally obtained for the MoS is 0.5887. It means that OUFTI-1 can support a loading case 58.87% higher than the one used during this analysis. It also means that our CubeSat fullls well the ESA requirement, which stipulates that all MoS must be positive. This last result marks the end of our static analysis. Now, a modal analysis will be performed to estimate the global dynamic response of OUFTI-1. 114
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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.
Page 63 and 64: • Then, the thermostats, that wil
Page 65 and 66: Figure 3.23: Schematics of the cove
Page 67 and 68: • 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: Figure 5.9: Illustration of the com
Page 117 and 118: Figure 5.12: First mode of OUFTI-1
Page 119 and 120: Figure 5.15: Precise PSD of Vega [5
Page 121 and 122: Chapter 6 Conclusions This master t
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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