Master Thesis - OUFTI-1

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calculated, and their fulllment of all requirements imposed by ESA, was veried. Chapter 3 developed the complete battery support design, from the initial idea to the manufacturing of this support. The reasons that led to modify the last year's design, were also presented. This design included: • The selection of the several components which had to be incorporated inside the support, including: batteries, thermal control's devices such as thermostats, heaters and thermal insulator, was performed. • Then, the material which was used to manufacture the support, was selected. This material has to fulll several physical, mechanical and thermal requirements. This step is really important because the thickness of the dierent parts that must prevent the batteries' bulge, was determined in relation to the properties of the selected material. • Once the material and the components were selected, the design phase was presented. The procedure was introduced step by step, just like it progressed during the whole year. • Finally, the design was validated by several calculations, such as the mass budget, and FE analysis, including static and dynamic analysis. Chapter 4 exposed a general procedure to create an accurate FE dynamic model of electronic cards. Firstly, several existing methods were presented and their accuracy was studied. Then, these methods were applied to the particular case of the homemade OBC of OUFTI-1. A homemade method, based on the fact that several methods can be applied to particular categories of components soldered on a same PCB, was also created. This method is the one which presented the best results and so, it is the one that was applied to each electronic card of OUFTI-1. Finally, some sensitivity analysis with regard to several parameters which strongly inuence the PCB dynamic response, were carried out. Finally, chapter 5 consisted in a complete FE analysis of the satellite. Firstly, the modeling strategy used to represent each component of the satellite in the FE model, was described accurately. Then, a static analysis was performed, and the results obtained ensure that OUFTI-1 withstands well the quasi-static loads which will be applied to it during the launch phase. The modal analysis led also to results that fulll all ESA requirements. Finally, the procedure to realize a random vibration analysis was presented and all necessary les were created. Throughout this thesis, we have tried to develop a detailed and rigorous description of the approach followed during all our progression. To realize this, a theoretical basis was 121
provided for each method used. We have also tried to express clearly the several reasons which led us to use these particular methods, as well as the assumptions to respect for applying them, because we see in these assumptions one of the cornerstones for the success of a rigorous scientic work. 6.2 Perspectives This section intends to give some guidelines for the future student who will be in charge of the structural subsystem. In the summary of each chapter, the problems encountered were highlighted. This section is here to remind these problems and to highlight them once again. Concerning the general ight system conguration, most of the problems were solved. The order of the electronic cards was conrmed and xed. The radiance diagram of the antennas was realized by the RF subsystem, which allowed to denitely conrm the location of the permanent magnet (in accordance with the requirements of the ADCS subsystem). This allowed also to dened the location of the four hystereric bars inside the CubeSat. The next problem will be to realize a complete integration procedure for the ight model of OUFTI-1. A basic procedure for the integration of the engineering model was already composed this year [33], but it must be completed by several information (how to include the cables inside the satellite, how to connect the several subsystems together, ...). The mass budget must also be denitely conrmed by weighting the components which still present some uncertainties about their mass. Concerning the battery support, the manufacturing has to be nalized. Then, thermal and structural tests must be performed to be correlated with the models created this year. This step will allow to denitely validate this design and to ensure its structural integrity during all the CubeSat lifetime. Concerning the electronic cards, an other experimental test will have to be performed, following advice given in chapter 4, to denitely validate the fact that the homemade method is the one which gives the best results. The physical properties of all components, such as the Young's modulus, can also be determined to allow to model them using global or local smearing methods which include the stiness contributions of these components. Finally, the experimental modal survey of OUFTI-1 in its hard-mounted version, will have to be performed and correlated to the FE model presented in the last chapter of this thesis. In addition, the random vibration analysis and tests for the launch phase must also be performed to qualify OUFTI-1 for its travel to space. 122
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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
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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 and 120: Figure 5.15: Precise PSD of Vega [5
Page 121: Chapter 6 Conclusions This master t
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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