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Calibration task of experimental device for space technology testing
Lazar, Václav ; Horák, Marek (oponent) ; Mašek, Jakub (vedoucí práce)
The Master thesis deals with an experimental test facility calibration procedure. The thesis focuses on a complex mathematical thermal model proposal, which describes the inner facility thermal processes during the specimen conductance measurements. The first section introduces the test facility, its limits, and the measurement principle. The necessary third version facility upgrades made to secure the prescribed test conditions are covered. The calibration need and reasons also resonate through the first section. The second part aims at the calibration specimens and the Thermal Model designs proposals. The specimens requirements and their final properties are brought forward. The determined heat losses calculations are completed with the defined refining procedure suggestion. The calibration specimens measurements were performed with a new test facility version three. The measured results will serve as calibration inputs for the Thermal Model tuning, necessary for the calibration task completion. The functional model will enable to proceed with the next phase of the test facility experiments.
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Influence of space debris on satellites design
Hláčik, Adam ; Lazar, Václav (oponent) ; Bartoněk, Jaroslav (vedoucí práce)
The bachelor thesis summarizes the space debris problem and its impacts on the uncrewed spacecraft design. The primary goal is to combine theoretical understandings of the space debris topic with the practical implementation of these findings in the "design for debris" strategy. The first chapter of the thesis examines the properties of space. debris. Findings from this chapter must be considered during the mission and spacecraft design phase, alongside other design driving attributes. The practical part demonstrates the "design for debris" approach in a model case study. The design approach is based on the Micro Meteriod and Orbital Debris analysis findings, which characterize the interaction of debris particles with spacecraft during the course of a mission. Alongside characterization of debris population on mission orbit, analysis can detect weak spots of spacecraft design that are vulnerable to debris impact. Risk-reducing modifications based on analysis data and problem understanding can be applied to reduce the possibility of a spacecraft failure. Another analysis iteration can verify the effectiveness of proposed modifications.
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Koncepční návrh habitatu pro extrémní prostředí - návrh skafandru pro Mars
Ponka, Jakub ; Lazar, Václav (oponent) ; Šálený, Vratislav (vedoucí práce)
Předložená bakalářská práce se zabývá koncepčním návrhem skafandru pro podmínky na Marsu. Koncepce vychází z rešeršní části, v níž jsou popsány současné modely skafandrů jednotlivých vesmírných agentur a extrémní podmínky, které na Marsu převládají. V samotném návrhu je kladen důraz na snížení váhy za použití materiálů jako jsou titan nebo karbonová vlákna. Dále je využita technologie na výrobu kyslíku z atmosférického oxidu uhličitého a digitalizování uživatelského rozhraní skafandru. Nakonec se práce zabývá problematikou odvodu metabolického tepla z vnitřní atmosféry skafandru do okolního prostředí.
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Design proposal of thermo-vacuum chamber for space segment testing
Udatný, Martin ; Mašek, Jakub (oponent) ; Lazar, Václav (vedoucí práce)
Scope of the thesis is thermo-vacuum testing of space segment devices and the design of the thermo-vacuum chamber in which the tests are performed. The theoretical part describes the tests and their requirements, especially the requirements based on ECSS standards. Furthermore, the chamber elements and subsystems commonly used in practice are described. In the practical part, conceptual designs of the thermal vacuum chamber are created, consisting of three alternative design solutions. These solutions are subsequently compared, and based on the defined parameters the most optimal solution is selected. The chosen solution is further developed by conducting Finite Element Analysis (FEA) for structural analysis and selecting the main components to meet the specified requirements. The main outputs of this work are the CAD model of the thermal vacuum chamber and the subsystem infrastructure diagram. These outputs can serve as a basis for the complete design of the thermal vacuum chamber.
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Design proposal and modal analysis of fixture for CubeSat vibration tests
Pospíšil, Jakub ; Bartoněk, Jaroslav (oponent) ; Lazar, Václav (vedoucí práce)
The CubeSat movement is currently growing in popularity, mainly due to the possibility of involving a wider range of institutions in space research. This interest is also driven by the need to conduct mechanical tests of CubeSats before they can be launched into space. This master’s thesis deals with the issue of mechanical testing of CubeSats and the performance of their vibration tests. Based on this research, the design of a 6U size fixture is performed including modal analysis and manufacturability verification.
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Návrh termo-vakuové komory pro testování CubeSatů
Jalůvka, Jiří ; Mašek, Jakub (oponent) ; Lazar, Václav (vedoucí práce)
Práce se zaměřuje na vývoj termo-vakuových komor pro měření CubeSatů. V rámci toho byl proveden průzkum dostupných termo-vakuových komor v České republice. Další část práce se věnuje definování požadavků na testování CubeSatů v termo-vakuovém prostředí. S ohledem na tyto požadavky bylo provedeno srovnání existující komory na Leteckém ústavu VUT a byly navrženy různé varianty řešení pro jednotlivé problémy. Konkrétně byly navrženy tři inovativní přístupy do komory, termální systémy a způsoby uchycení satelitu v komoře. Práce tedy nejen popisuje ideální podobu termo-vakuové komory s veškerými systémy, ale také přináší konkrétní návrhy pro optimalizaci stávající komory na Leteckém ústavu, pro možnost úspěšného testování CubeSatů.
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Proposal of the modular support equipment for the CubeSat integration
Kukla, Ondřej ; Lazar, Václav (oponent) ; Vaverka, Jan (vedoucí práce)
The aim of this diploma thesis is to create a design of Mechanical Ground Support Equipment for CubeSat integration. In the text below, CubeSats are generally introduced together with commercially available products for their integration. The final design was chosen based on a comparison of parameters and results from the market research. The design itself was successfully created, 3D data and drawings are attached to the work.
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Design proposal of the 12U CubeSat structure
Kopecký, Matěj ; Lazar, Václav (oponent) ; Junas, Milan (vedoucí práce)
CubeSats are nowadays highly popular topic, due to their price and simplicity. Lately, their use is mainly concentrated in commercial sphere of market, where number of companies providing wide spectrum of services for CubeSat missions, are being founded. One of these companies is also Czech Aerospace Research Centre (VZLÚ), which recently began development of series of 1U – 3U CubeSat structures. This master´s thesis is written in collaboration with VZLÚ. It is focused upon creation of information platform, including market research and following design with its analysis and check of 12U CubeSat structure as a continuation in the scope of further development of series of 6U – 12U structures.
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Design proposal and analysis of the 3D printed 1U CubeSat frame
Kilián, Ondřej ; Jetela, Václav (oponent) ; Lazar, Václav (vedoucí práce)
This thesis contains the process of design and subsequent FEM analysis of a CubeSat class satellite with accordance to the “CubeSat Design Specification” from Californian Polytechnic State University revision 14. The software used for the design and generation of supportive materials is the Autodesk Inventor Pro 2020, generation of the G-code for printing is done in the PrusaSlicer 2.4.1. software and the analysis are done in the MSC Pantran and MSC Nastran software package. The overall design is considered as successful as it meets all the criteria, and the analysis shows that it can withstand the loads present in the launch process to the earth’s orbit.
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