Master Thesis - OUFTI-1

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Acknowledgments I wish to acknowledge all the people who helped me, during the whole year, to carry out this master thesis. First of all, I would like to express my gratitude to my advisor Professor Gaëtan KER- SCHEN for his precious advice and support, and for giving me the opportunity to take one's rst steps in the fascinating world of space industries. I am deeply indebted to Professor Jean-Claude GOLINVAL who opened me the doors of his laboratory and gave me his condence to use his precious material. I would like to thank Professors Jean-Claude GOLINVAL and Pierre ROCHUS, but also Daniel SIMON and Amandine DENIS for accepting to serve on the examination commitee of this master thesis. I am pleased to acknowledge all the members of the OUFTI team, who created a pleasant working atmosphere. This year will remain a wonderful experience for me that I will never forget. Last but not least, I thank my family for encouraging and supporting me, not only during this academic year, but during my entire studies. 1
Abstract OUFTI-1, standing for "Orbital Utility For Telecommunication Innovation ", is the rst nanosatellite developed by the University of Liège as well as the rst one which was ever developed in Belgium. This name, which is a typical expression from the city of Liège showing surprise or amazement, was chosen to point up the origin of the satellite. The project takes place within the framework of a long-term program called LEODIUM (which means Liège in Latin). The main goal of this program is to open a new window on scientic careers and space-related activities. OUFTI-1 will be equipped of three payloads: • A D-STAR repeater. OUFTI-1 will be the rst satellite to use this new digital amateur radio communication protocol in space. • A digitally-controlled electrical power system developed in collaboration with Thales Alenia Space ETCA. • High-eciency solar cells from Azur Space. OUFTI-1 will be launched on board the new european launcher: Vega. This present thesis focuses on the structural design and dynamic analysis of OUFTI- 1. The design part covers essentially the creation of a reliable support for the batteries in accordance with several requirements. It includes also some changes in the general conguration of the satellite. The analysis part is based on the creation of an accurate nite element modeling procedure for electronic cards. Then, this procedure is applied to each electronic card and several FE analysis are performed to ensure the structural integrity of the satellite. Finally, a random vibration analysis is presented. The goal of this analysis is to demonstrate the ability of OUFTI-1 to survive at the launch phase. 2
Page 1: University of Liège Faculty of App
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 and 38: Figure 2.20: Exploded view of OUFTI
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
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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
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3.10 Summary Through this chapter,
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Chapter 4 Electronic cards dynamic
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Figure 4.1: Example of manufacturin
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Figure 4.4: Illustration of the exp
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Figure 4.5: MAC between the two mod
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• Global mass/stiness smearing me
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4.2.6 Modeling of the chassis A gen
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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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