Master Thesis - OUFTI-1

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In our case, this requirement can be easily veried considering our particular reference frame. The results obtained for OUFTI-1 in its nal conguration are listed in Table 2.1. Axes Coordinates (in mm) X -0.139 Y -2.558 Z 0.691 Table 2.1: Coordinates of the OUFTI-1 CoG So, the distance between the geometric center of OUFTI-1 and its CoG can be calculated using Equation (2.4.1). √ d = x 2 CoG + y2 CoG + z2 CoG = 2.6533 mm (2.4.1) Therefore, the requirement is respected. 2.4.3 Inertia For a continuous rigid body, the inertia tensor is given by Equation (2.4.2). ⎛ ⎞ I xx I xy I xz I = ⎝I yx I yy I yz ⎠ (2.4.2) I zx I zy I zz where: I xx = ∫ (y 2 + z 2) dm (2.4.3) I yy = ∫ (x 2 + z 2) dm (2.4.4) I zz = ∫ (x 2 + y 2) dm (2.4.5) ∫ I xy = I yx = − ∫ I xz = I zx = − ∫ I yz = I zy = − (x y) dm (2.4.6) (x z) dm (2.4.7) (y z) dm (2.4.8) 37
I xx , I yy and I zz are called the moments of inertia while the other elements are called the products of inertia. This tensor can be calculated from any point of the structure. However, to facilitate its calculation, it is preferable to dene it from the CoG. Thus, the inertia tensor linked to our reference frame is given in Equation (2.4.9). ⎛ 2.104 6.025 10 −2 1.69 10 −2 ⎞ I CoG = ⎝6.025 10 −2 1.757 −9.641 10 −2 ⎠ × 10 6 g mm 2 (2.4.9) 1.69 10 −2 −9.641 10 −2 2.019 In addition, the principal moments of inertia can be calculated, as well as the principal axes, to completely dene the inertia properties of OUFTI-1. They are given in Equations (2.4.10) to (2.4.12) and (2.4.13) to (2.4.15) respectively. M 1 = 1.715 × 10 6 g mm 2 (2.4.10) M 2 = 2.05 × 10 6 g mm 2 (2.4.11) 2.5 Mass budget M 3 = 2.114 × 10 6 g mm 2 (2.4.12) ⎛ ⎞ −0.159 A 1 = ⎝ 0.938 ⎠ (2.4.13) 0.307 ⎛ ⎞ −0.042 A 2 = ⎝ 0.305 ⎠ (2.4.14) −0.952 ⎛ ⎞ 0.986 A 3 = ⎝0.164⎠ (2.4.15) 0.009 As already mentioned on chapter 1, one of the general constraints for a CubeSat is: "Each single CubeSat shall not exceed 1 kg mass ". To ensure that OUFTI-1 respects this requirement, each component of the CubeSat was weighted. However, at the end of this year, some of them are not yet nished. For 38
Page 1 and 2: University of Liège Faculty of App
Page 3 and 4: Abstract OUFTI-1, standing for "Orb
Page 5 and 6: 3.4 Initial idea . . . . . . . . .
Page 7 and 8: List of Figures 1.1 The Pumpkin's C
Page 9 and 10: 4.18 MAC matrix using the simple me
Page 11 and 12: List of Acronyms ADCS Al AlNiCo ASI
Page 13 and 14: Thesis outline This thesis focuses
Page 15 and 16: of larger satellites. So, the CubeS
Page 17 and 18: 1.2 OUFTI-1 project 1.2.1 Genesis O
Page 19 and 20: • XatCobeo (Vigo - Spain): Develo
Page 21 and 22: Chapter 2 OUFTI-1: Flight system co
Page 23 and 24: Figure 2.2: Product tree of OUFTI-1
Page 25 and 26: 2.3.2 Solar panels The armor panels
Page 27 and 28: • We do not want to drill or manu
Page 29 and 30: In our case, because of the limited
Page 31 and 32: Figure 2.13: Magnetic eld obtained
Page 33 and 34: Figure 2.17: Pictures of the ADCS c
Page 35 and 36: consider the possibility of oshorin
Page 37: Figure 2.20: Exploded view of OUFTI
Page 41 and 42: Subsystem: Structure & Conguration
Page 43 and 44: Subsystem: Thermal Control Parts Co
Page 45 and 46: Chapter 3 Design of a new support f
Page 47 and 48: Figure 3.3: Batteries during and af
Page 49 and 50: The concept is the following one: F
Page 51 and 52: A test under vacuum conditions was
Page 53 and 54: Thermal Expansion (CTE) of the mate
Page 55 and 56: Figure 3.9: Classication by density
Page 57 and 58: The last property to determine is t
Page 59 and 60: • 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
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According to this particular shape,
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This is due to the fact that this c
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environment. Then, this model is ex
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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
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Figure 5.15: Precise PSD of Vega [5
Page 121 and 122:
Chapter 6 Conclusions This master t
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provided for each method used. We h
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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
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Appendix B Schemas of electronic ca
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Appendix C Fixations of the endless
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Appendix D Datasheet of the battery
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Master Thesis - OUFTI-1

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