Master Thesis - OUFTI-1
Master Thesis - OUFTI-1 Master Thesis - OUFTI-1
ITD Ibrahim Time Domain ITR Interface Technical Review JARL Japan Amateur Radio League KISS Keep It Simple, Stupid (and Short) LEODIUM Low Earth Orbit Demonstration In University Mode Li Lithium LV Launch Vehicle MAC Modal Assurance Criterion MECH Mechanism MLI Multilayer Insulation MoS Margin of Safety OBC On-Board Computer OBC 1 Pumpkin's On-Board computer (FM 430) OBC 2 Homemade On-Board Computer OUFTI Orbital Utility For Telecommunication Innovation P-POD Poly-Picosatellite Orbital Deployer PCB Printed Circuit Board PGA Pin Grid Array PSD Power Spectral Density QFP Quad Flat Pack RBF Remove Before Flight RF Radio Frequency SDR Software-Dened Radio SF Safety Factor SMT Surface Mount Technology SSI Stochastic Subspace Identication STRU Structure & Conguration THER Thermal Control T i Titanium TID Total Irradiation Dose TML Total Mass Loss UCL Catholic University of Louvain-la-Neuve UHF Ultra High Frequency UHMWPE Ultra High Molecular Weight Polyethylene ULg University of Liège VCD Verication Control Document VHF Very High Frequency xEPS Experimental Electrical Power Supply 11
Thesis outline This thesis focuses on the structural design of a new support for the batteries and dynamic analysis of the nanosatellite OUFTI-1, developed at the University of Liège (ULg). This work will be divided into 6 parts: • Firstly, a brief introduction about the project and its history will be presented. • Then, the general conguration of the satellite will be discussed. The requirements and constraints which led to the nal conguration, will be introduced subsystem by subsystem to bring an overall view of the project. • In the third chapter, the design of a new support for the batteries will be studied. The reasons that led to change the support created last year, will be exposed and the development phase will be discussed step by step. • After this structural design part, we will focus on dynamic analysis. The rst step will be to create a dynamic modeling procedure for the electronic cards. The dierent methods that already exist to realize an accurate Finite Element (FE) model will be discussed. Then, the best one will be applied to the Homemade On-Board Computer (OBC 2) of OUFTI-1. • Applying this procedure to each electronic card of OUFTI-1, complete static and dynamic analysis will be performed. Random vibration analysis will also be presented to demonstrate the structural integrity of the satellite during the launch phase. • Finally, the conclusions of this thesis will be drawn and perspectives for future works will be highlighted. 12
- 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: List of Acronyms ADCS Al AlNiCo ASI
- 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
- 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.
ITD Ibrahim Time Domain<br />
ITR Interface Technical Review<br />
JARL Japan Amateur Radio League<br />
KISS Keep It Simple, Stupid (and Short)<br />
LEODIUM Low Earth Orbit Demonstration In University Mode<br />
Li Lithium<br />
LV Launch Vehicle<br />
MAC Modal Assurance Criterion<br />
MECH Mechanism<br />
MLI Multilayer Insulation<br />
MoS Margin of Safety<br />
OBC On-Board Computer<br />
OBC 1 Pumpkin's On-Board computer (FM 430)<br />
OBC 2 Homemade On-Board Computer<br />
<strong>OUFTI</strong> Orbital Utility For Telecommunication Innovation<br />
P-POD Poly-Picosatellite Orbital Deployer<br />
PCB Printed Circuit Board<br />
PGA Pin Grid Array<br />
PSD Power Spectral Density<br />
QFP Quad Flat Pack<br />
RBF Remove Before Flight<br />
RF Radio Frequency<br />
SDR Software-Dened Radio<br />
SF Safety Factor<br />
SMT Surface Mount Technology<br />
SSI Stochastic Subspace Identication<br />
STRU Structure & Conguration<br />
THER Thermal Control<br />
T i Titanium<br />
TID Total Irradiation Dose<br />
TML Total Mass Loss<br />
UCL Catholic University of Louvain-la-Neuve<br />
UHF Ultra High Frequency<br />
UHMWPE Ultra High Molecular Weight Polyethylene<br />
ULg University of Liège<br />
VCD Verication Control Document<br />
VHF Very High Frequency<br />
xEPS Experimental Electrical Power Supply<br />
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