Master Thesis - OUFTI-1

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1.1.3 The P-POD Figure 1.1: The Pumpkin's CubeSat family The P-POD, which stands for "Poly-Picosatellite Orbital Deployer ", is the standardized CubeSat deployment system developed by CalPoly (shown in Figure 1.2). It is a rectangular box with a door (situated on the right side in Figure 1.2). It serves as the interface between CubeSats and the Launch Vehicle (LV). Three CubeSats can be placed within one P-POD. When the launcher is in orbit, the P-PODs deploy the CubeSats using a spring mechanism to push CubeSats along a series of rails and eject them into orbit. Further detail can be found in reference [3]. Figure 1.2: Poly-Picosatellite Orbital Deployer (P-POD) 15
1.2 OUFTI-1 project 1.2.1 Genesis OUFTI-1, standing for "Orbital Utility For Telecommunication Innovation ", is the rst nanosatellite developed by the University of Liège (ULg) 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 started in 2007 when Mr. Luc HALBACH, an engineer of Spacebel, suggests the idea of testing a new amateur radio digital technology in space on board a CubeSat: the D-STAR protocol. This idea has catched the attention of several academic members from ULg and, within a few weeks, a team was created to work on the project: OUFTI-1 was born. This team includes two students from ULg, Stefania GALLI and Jonathan PISANE, who realized the mission design of OUFTI-1 [4] and the design and implementation of the rst telecommunication elements of OUFTI-1 [5] respectively. Last year, it was a great team composed of 13 students coming from three dierent schools (University of Liège, Gramme Institute and ISIL Institute), who developed the project to the state at which this thesis starts (references [6] to [18]). 1.2.2 The launch opportunity OUFTI-1 will be launched on board the new european launcher: Vega (shown in Figure 1.3) for free, which is an incredible opportunity. This launcher was developed by Arianespace jointly to the Italian Space Agency (ASI) and European Space Agency (ESA). Further detail can be found in reference [19]. The main payload of the Vega Maiden Flight is the LARES system (an articial satellite provided by ASI with a spherical body and covered by corner cube reectors). The secondary payloads includes 9 CubeSats, plus the satellite ALMASat-1 from the University of Bologna. Figure 1.3: The new European launcher: Vega 16
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: of larger satellites. So, the CubeS
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
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
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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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