Master Thesis - OUFTI-1

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2.4 Physical properties The physical properties (including CoG and inertia) are of primary importance for the denition of a 3-dimensional body. In addition, other students, like the ones in charge of ADCS [25] or MECH [24] subsystems, need them to perform their simulations. In this section, the Catia software will be used to determine theCoG location and inertia properties of <strong>OUFTI</strong>-1. When a complete engineering model of the satellite will be available, these values can be veried experimentally [31]. 2.4.1 Catia modeling Last year, a detailed model of the satellite was carried out using the Catia software [32]. During this year, this model was rened to obtain the nal conguration of the satellite. This conguration is shown in Figure 2.20. This type of modeling, which is widely used in mechanical industries, presents several advantages: • Firstly, it allows to have an overall view of each component's location within the CubeSat. This is very helpful to verify that a given component could be placed at a specic location or to create an appropriate integration procedure for the satellite [33]. In addition, Catia les are compatible with the Samcef software [34], which is used to perform the FE analysis. So, the two can be combined to take the best of the two worlds (Catia for Computer-Aided Design (CAD) modeling and Samcef for FE analysis) and to facilitate the task of the engineer who is in charge of the structural subsystem. • Then, Catia can calculate several physical properties such as the location of the CoG (which is really helpful in our case considering the reference frame that we use) or the inertia properties. However, to be accurate, Catia requires the denition of each material used to manufacture the several components of the satellite. • Finally, Catia facilitates the creation of technical drawings. 2.4.2 Center of gravity An other requirement imposed by the CubeSat standard is: "The CubeSat center of gravity shall be located within a sphere of 2 cm from its geometric center ". This requirement allows to ensure that each P-POD CoG remains located inside a specic volume. 35
Figure 2.20: Exploded view of <strong>OUFTI</strong>-1 36
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: consider the possibility of oshorin
Page 39 and 40: I xx , I yy and I zz are called the
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 ⇒
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Their study was based on the fact t
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Figure 4.14: Example of spacecraft
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Figure 4.15: Location of measuremen
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Figure 4.18: MAC matrix using the s
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4.3.6 Application of the local mass
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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
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Components Young's moduli (GP a) Po
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Components Young's moduli (GP a) Po
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5.3 Static analysis As described in
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Figure 5.9: Illustration of the com
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Figure 5.11: Maximal Von Mises stre
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Figure 5.12: First mode of OUFTI-1
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Figure 5.15: Precise PSD of Vega [5
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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
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[13] Ph. LEDENT. "Design and Implem
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[40] "Dejond - Aluminum Catalog ".
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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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