Master Thesis - OUFTI-1

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Figure 5.8: Frame rotation The calculation of the steady state accelerations in the CubeSat frame is presented in Equation 5.3.1. ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ a X, CubeSat 1 0 0 2.4 2.4 ⎝a Y, CubeSat ⎠ = ⎝0 cos (10 ◦ ) −sin (10 ◦ ) ⎠ × ⎝ 2.4 ⎠ = ⎝ −0.1756 ⎠ (5.3.1) a Z, CubeSat 0 sin (10 ◦ ) cos (10 ◦ ) 12.6 −12.8253 Owing to the particular case which is considered, the weight of the two other CubeSats placed inside the P-POD must be added to these acceleration. The maximal acceptable mass for one CubeSat is 1 kg. So, the forces acting on the four feet of <strong>OUFTI</strong>-1 base plate, due to the two CubeSats placed above it, are calculated in Equation 5.3.2. F = m × g × a quasi−static = 2 × 9.81 × 12.8253 = 251.64 N ≈ 252 N (5.3.2) which lead to a force of 63 N on each foot along the Z axis of the CubeSat frame. It is important to note that the accelerations considered in this analysis occured at dierent phases of the ight (the maximal longitudinal acceleration is reached at the third stage's maximal acceleration and maximal lateral accelerations are reached during the lifto and under the ight maximal dynamic pressure). So, the resulting model is conservative, which brings an additional security with regard to the results. An illustration of the complete loading state (in the CubeSat frame) is given in Figure 5.9. 111
Figure 5.9: Illustration of the complete quasi-static loading state of <strong>OUFTI</strong>-1 5.3.2 Boundary conditions To determine the boundary conditions to apply to our CubeSat, its mounting within the P-POD must be known. This one is available in reference [58]. Then, these conditions must be dened as follow: • The CubeSat is placed inside the P-POD with its base plate on the +Z side. So, in the worst case considered here, the end plate's feet are in direct contact with the P-POD. For this reason, these feet will be clamped to simulate this perfectly rigid contact. • In addition, the rails situated in the corners of the CubeSat are in contact with the rails of the P-POD. So, some lockings (along X and Y axes) will be applied on the rails of the CubeSat to represent this linear contact. 5.3.3 Results The results nally obtained are presented in Table 5.7 and in Figures 5.10 and 5.11. Maximal displacement (mm) Maximal Von Mises stress (MP a) 0.0909 101.97 Table 5.7: Results of the static analysis 112
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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
Page 61 and 62: 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: 5.3 Static analysis As described in
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 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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