Master Thesis - OUFTI-1

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Chapter 1 Introduction 1.1 The CubeSat program 1.1.1 The concept The OUFTI-1 project takes place in the CubeSat program initiated approximately 10 years ago jointly by California Polytechnic State University (CalPoly) and Stanford University. This program aims to provide an easier access to space by creating a standard based on the following features: • The mass of the satellite must be less than 1 kg (1.33 kg in the last version of the CubeSat Design Specication (CDS) [1], but this version stands not for the Vega Maiden Flight on board which OUFTI-1 will be launched). • The shape of the satellite must be a cube of 10 × 10 × 10 cm. This standard allows to create satellites in a short development time. In addition, owing to their small size, CubeSats can take place in a space launcher as secondary payloads, which is less expensive. For all of this reasons, the CubeSat program meets a great success with universities and industries. At the moment, the project involves more than 100 universities, high schools or private rms all over the world developing CubeSats containing scientic, private and governments payloads. All these developers are linked together by a great community spirit, and each one benets from the sharing of information between the several teams [1]. However, it is important to note that, owing to constraints listed above, the development of a CubeSat is a technical challenge, even if it is faster and cheaper than the development 13
of larger satellites. So, the CubeSat philosophy is quite dierent. Indeed, the leitmotiv of several CubeSat teams is KISS: "Keep It Simple, Stupid (and Short)". This philosophy is based on the fact that, if two dierent solutions are available to realize the same task with the same eciency, the best one is the simplest one. This explains that CubeSats projects use Commercial-O-The-Shelf (COTS) components instead of space-qualied ones. It is a particularity of these projects and, for this reason, the ocial requirements must be lightened for this type of mission. The denition provided here is a general one. All the technical requirements that a nanosatellite has to respect to be validated as a CubeSat are available in reference [1]. 1.1.2 The Pumpkin's CubeSat kit In order to answer to the request which grows incessantly, some industries have decided to develop structures that respect these requirements. Among all these commercial structures, the most popular remains the CubeSat Kit (CSK) from Pumpkin [2]. This structure is available in three dierent formats (as shown in Figure 1.1). For OUFTI-1, the goal was to create a 1 unit CubeSat. So, after a long hesitation between the Pumpkin's structure and an other one provided by ISIS, it was decided to buy the 1 unit skeleton from Pumpkin. The decision of buying a commercial structure was chosen because the development of a space structure is a complicated problem. Indeed, requirements imposed to spacequalied devices are so restrictive that the development of a space-qualied structure is too ambitious for ULg, which had absolutely no experience in satellite development before this project. 14
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: Thesis outline This thesis focuses
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
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
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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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