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Design of single seat aiirplane by the UL - 2 regulation
Kövér, Ondřej ; Schoř, Pavel (referee) ; Píštěk, Antonín (advisor)
Bachelor´s thesis solves conceptual design of oneseater aircraft by the UL-2 regulations, that is up to 300 kilograms of take-off weight. In the first part of the thesis, there is survey of similar aircrafts and summary of their important characteristics. In further section are possible conceptions and the best choice of them outlined. Afterwards are characteristics of carrier surfaces, load calculation and flight envelope mentioned. The last part deals with calculation and design of engine mounting.
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Sandwich structure analysis using Finite Element Methods
Bucňák, Ondřej ; Schoř, Pavel (referee) ; Mališ, Michal (advisor)
This bachelor’s thesis focuses on the analysis of material model core sandwich structures. The behavior of the sandwich core is simulated using Finite Element Method (FEM) in programs MSC.Patran/Nastran. The first part deals with describing the properties of sandwich structures and its components. There are presented examples of the application of sandwich structures. The next section describes the elementary material models. In the last part of bachelor’s thesis is performed FEM analysis of material model sandwich foam core and comparison to the results with the four-point bending test.
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Development and use of non-motorized aircraft
Bečka, Pavel ; Schoř, Pavel (referee) ; Zablatzký, Jiří (advisor)
The object of this bachelor thesis is history, development and use of non-motorized aircraft. The first part dedicate of history this aircraft industry in the Word and Czechoslovakia. The second part dedicate about construction of this machines. The Thirst part dedicate of materials, which are using in this part of aeronautical production. And finally fourth part dedicate ways for starts of this aircrafts.
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Load State of an Aircraft with an Elastic Wing
Schoř, Pavel ; Daněk, Vladimír (referee) ; Slavík, Svatomír (referee) ; Píštěk, Antonín (advisor)
V této práci je navržena metoda výpočtu zatížení letadla s netuhým křídlem, založená na spojení panelové metody prvního řádu dle Katz and Plotkin, Low-Speed Aerodynamics, 2001 s metodou stukturální analýzy dle Píštěk et al., Pevnost a životnost letadel I, 1988 a Lebofsky,Numerically Generated Tangent Stiffness Matrices for Geometrically Non-Linear Struc- tures, 2013. Panelová metoda poskytuje přasná data pro výpočet zatížení křídla od vzdušných sil za předpokladu že lze dané proudění aproximovat po- mocí potenciálního proudění, Narozdíl metod založených na interakci s CFD metodami lze navrženou metodu používat i na bežném počítači.
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Gliders in Today's Aviation
Schoř, Pavel ; Zikmund, Pavel (referee) ; Šošovička, Róbert (advisor)
The introduction of this bachelor`s thesis deals with a brief history of gliders. Second chapter explains basic principles of unpowered aircraft flight, including the principle, how an unpowered glider can climb. Commonly used take-off methods are also mentioned. In all chapters, the examples are explained on Standard Cirrus glider, because it is very widespread in Czech Republic and is financially well affordable. Third chapter describes natural principles, which are used by glider pilots to gain an altitude. An extra attention is paid to gaining an altitude in thermals. In fourth chapter, the gliders are divided according to their purpose and sporting category. Short description of glider construction is mentioned, including a description of instruments, which are necessary for a cross country flight. The description of cross country flight is mentioned at end of this chapter. Last chapter compares Standard Cirrus glider with SZD 56-2, which is one of the today`s best 15m gliders. The main purpose is to illustrate the progress in glider designing, which was achieved during last 40 years, in the light of previous chapters.
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Comparison of panel codes for aerodynamic analysis of airfoils
Bilčík, Adam ; Schoř, Pavel (referee) ; Popela, Robert (advisor)
Cieľom tejto práce bolo vytvorenie prehľadu v súčasnosti používaných implementácií panelových metód pre aerodynamické výpočty charakteristík 2D profilov. Základný popis princípu panelovej metódy, porovnanie jednotlivých implementácií a zhodnotenie ich možností (presnosť, aplikovateľnosť) na typické úlohy. V práci boli použité tri rôzne panelové programy: Xfoil, JavaFoil a XFLR5. Práca bola obohatená o meranie v aerodynamickom tuneli.
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Load State of an Aircraft with an Elastic Wing
Schoř, Pavel ; Daněk, Vladimír (referee) ; Slavík, Svatomír (referee) ; Píštěk, Antonín (advisor)
V této práci je navržena metoda výpočtu zatížení letadla s netuhým křídlem, založená na spojení panelové metody prvního řádu dle Katz and Plotkin, Low-Speed Aerodynamics, 2001 s metodou stukturální analýzy dle Píštěk et al., Pevnost a životnost letadel I, 1988 a Lebofsky,Numerically Generated Tangent Stiffness Matrices for Geometrically Non-Linear Struc- tures, 2013. Panelová metoda poskytuje přasná data pro výpočet zatížení křídla od vzdušných sil za předpokladu že lze dané proudění aproximovat po- mocí potenciálního proudění, Narozdíl metod založených na interakci s CFD metodami lze navrženou metodu používat i na bežném počítači.
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