Master Thesis - OUFTI-1

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2.3.1 Skeleton The skeleton of OUFTI-1 corresponds to the 1U structure of Pumpkin's CSK. This structure comprises three main parts: • A chassis, with a thickness of 1.27 mm. • A base plate, with a thickness of 1.52 mm, that is screwed on the chassis with 6 M3 × 4 mm stainless steel screws. It supports one normal foot, two spring plunger feet and one deployment switch foot. These special feet are used to deploy the CubeSats from the P-PODs when they are placed in orbit. • An end plate, with a thickness of 1.52 mm, that is screwed on the chassis with 4 M3 × 4 mm stainless steel screws. It supports four normal feet. The skeleton is made of Aluminum (Al) 5052 H32 and the feet are made of Al−6061 T 6. A surface treatment is also performed on the structure. The rails (situated on the corners of the chassis) and the feet are hard-anodized to prevent galling when they are in contact with the P-POD. The rest of the structure is alodined, which is an electrically-conductive surface nish [22]. This last fact is very important because the structure will be used as the reference electrical mass for the CubeSat. The kit also includes a Flight Module (FM) 430 (used as main On-Board Computer (OBC) in OUFTI-1: OBC 1). It is important to note that all the functions available on this card are not used for OUFTI-1 (e.g., the MHX transceiver). This fact will turn out to be a crucial information for the nal conguration (see section 2.3.3). Figure 2.3 shows the devices of the CubeSat kit bought by ULg. Figure 2.3: CSK structure with the FM 430 23
2.3.2 Solar panels The armor panels of OUFTI-1 are made of Al − 7075 T 73. Their role is to protect all the equipments of the satellite against the harsh space environment: cosmic radiations, debris, thermal variations, ... Last year, a simulation of the OUFTI-1 orbit was performed to obtain the Total Irradiation Dose (TID) at which the satellite is submitted during one year [6]. The TID is the addition of the eects of the trapped electrons and protons within the radiation belts, the solar protons and the Bremsstrahlung eect. The results are presented in Figure 2.4, where the TID is considered as a function of equivalent aluminum shielding thickness. Figure 2.4: Dose depth curve for OUFTI-1 orbit [6] In the case of OUFTI-1, the thickness of these panels was chosen to 1.5 mm, which corresponds to an equivalent aluminum shielding thickness of 1.95 mm for the entire satellite. The complete study that led to this particular choice is available in reference [15]. There are ve panels mounted on the OUFTI-1 skeleton: • Two panels, one on the base plate and the other on the end plate, with external dimensions of 90 × 96 mm 2 . • Three panels placed on the faces +X and +/ − Y of the chassis, with external dimensions of 82 × 96 mm 2 24
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: Figure 2.2: Product tree of OUFTI-1
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
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
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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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