National Repository of Grey Literature 37 records found  1 - 10nextend  jump to record: Search took 0.00 seconds. 
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.
Rebuilding of VUT 051 RAY into twin-engine conception
Jílek, Jan ; Mališ, Michal (referee) ; Píštěk, Antonín (advisor)
The master’s thesis is dealt with the design of rebuilding of VUT 051 RAY which is equipped electric powerplant to twin-engine conception named VUT 051 RAY-DUO. In the thesis was verified the range of centre of gravity position of VUT 051 RAY-DUO then powerplant in ducted fan configuration was designed, performances of the airplane were appointed and controllability during fail one of the engines was analysed. The design of new powerplant was verified by strength analysis and then costing calculation was established.
Design of the Aircraft VUT 001 MARABU Modification Powered by Hydrogen Fuel Cells and Batteries
Bencalík, Karol ; Píštěk, Antonín (referee) ; Hlinka, Jiří (advisor)
The main topic of this thesis is a design of VUT 001 airplane fuel transformation by means of fuel cells and storage batteries. A list of components available on the market was drawn up, their building in the airplane and the engineering design for mounting the electric motor into the structure. The thesis also includes the mass and centering analysis of flight performance and stability control.
Airplane Cooling System Optimization
Lajza, Ondřej ; Fiľakovský, Karol (referee) ; Horák, Aleš (referee) ; Píštěk, Antonín (advisor)
Dissertation thesis is focused on the aircraft cooling system optimization. The knowledge of the pressure loss is necessity for design of an optimal system. In the beginning of the thesis, the different designs of piston engine cooling systems are described for both aircrafts and automobiles. Other sections outline the determination of the coolers characteristics and describe the different test sections applicable for the characteristics measurement. The test section built at the Institute of the aerospace engineering is described as well. Practical part of the thesis describes the calibration of the test section. The measurements of the specific coolers were compared with the CFD simulation of two models - the simplified cooler model and cooler element model. Additionally, the measurements were compared with results obtained at specialized coolers testing facility.
Rebuilding an airplane Z 142 with a LYCOMING power unit
Šurkala, Martin ; Horák, Marek (referee) ; Píštěk, Antonín (advisor)
The aim of this master´s thesis is to replace the current engine M 337AK of the aeroplane Zlin 142 for the engine of Lycoming type with an appropriate propeller. Another purpose of the study is the installation of a nose undercarriage of VUT 100 type. The first part of the thesis examines the alternatives of replacement engines. Here the individual engines are compared with regard to their flight characteristics (climbing etc.). The next part presents the calculation of new CG positions, flight envelopes and the load affecting the engine mount. Finally, the last part focuses on the constructional plan for the engine installation and the structural analysis.
Reconstruction of middle part of the fuselage Z 143 aircraft using semi- monocoque frame
Zamazal, Jakub ; Mališ, Michal (referee) ; Píštěk, Antonín (advisor)
The thesis is focused on reconstruction of middle part of fuselage Z 143 aircraft from truss frame to semi-monocoque frame. In the thesis there is a conceptual design of semi-monocoque middle part of fuselage. The spars of centre wing section are strength controlled. In thesis there is weight analysis according to use the semi-monocoque middle part of fuselage. In second half of the thesis there is a study of retractable landing gear. The thesis shows weight savings according to use a semi-monocoque frame. The thesis also shows that semi-monocoque frame allows other option to upgrade Z 143 aircraft. This thesis can serve as a feasibility study of the reconstruction of the middle part of the fuselage Z 143 aircraft.
Airplane Cooling System Optimization
Lajza, Ondřej ; Píštěk, Antonín (advisor)
Dissertation thesis is focused on the aircraft cooling system optimization. The knowledge of the pressure loss is necessity for design of an optimal system. In the beginning of the thesis, the different designs of piston engine cooling systems are described for both aircrafts and automobiles. Other sections outline the determination of the coolers characteristics and describe the different test sections applicable for the characteristics measurement. The test section built at the Institute of the aerospace engineering is described as well. Practical part of the thesis describes the calibration of the test section. The measurements of the specific coolers were compared with the CFD simulation of two models - the simplified cooler model and cooler element model. Additionally, the measurements were compared with results obtained at specialized coolers testing facility.
Airplane Cooling System Optimization
Lajza, Ondřej ; Píštěk, Antonín (advisor)
Dissertation thesis is focused on the aircraft cooling system optimization. The knowledge of the pressure loss is necessity for design of an optimal system. In the beginning of the thesis, the different designs of piston engine cooling systems are described for both aircrafts and automobiles. Other sections outline the determination of the coolers characteristics and describe the different test sections applicable for the characteristics measurement. The test section built at the Institute of the aerospace engineering is described as well. Practical part of the thesis describes the calibration of the test section. The measurements of the specific coolers were compared with the CFD simulation of two models - the simplified cooler model and cooler element model. Additionally, the measurements were compared with results obtained at specialized coolers testing facility.
Design of light four-seater aircraft
Mikulášek, Miloš ; Vaněk, František (referee) ; Píštěk, Antonín (advisor)
This master‘s thesis is focused on the design of four-seat metal aircraft with low take-off weight in accordance with CS-23. Main dimensions of aircraft are designed, weight analysis, aerodynamic characteristics and flight performance are calculated in this thesis. In conclusion, the estimated costs of development and production are determined.
Adaptive parameterization for Aerodynamic Shape Optimization in Aeronautical Applications
Hradil, Jiří ; Rudolf, Pavel (referee) ; Růžička, Pavel (referee) ; Píštěk, Antonín (advisor)
Cílem mé disertační práce je analyzovat a vyvinout parametrizační metodu pro 2D a 3D tvarové optimalizace v kontextu průmyslového aerodynamického návrhu letounu založeném na CFD simulacích. Aerodynamická tvarová optimalizace je efektivní nástroj, který si klade za cíl snížení nákladů na návrh letounů. Nástroj založený na automatickém hledání optimálního tvaru. Klíčovou částí úspěšného optimalizačního procesu je použití vhodné parametrizační metody, metody schopné garantovat možnost dosažení optimálního tvaru. Parametrizační metody obecně používané v oblasti aerodynamické tvarové optimalizace momentálně nejsou připravený na komplikované průmyslové aplikace vyskytující se u moderních dopravních letounů, které mají šípová zalomená křídla s winglety a motorovými gondolami, přechodové prvky spojující např. trup s křídlem atd.. Existuje tedy potřeba nalezení obecné parametrizační metody, která bude aplikovatelná na širokou škálu různých geometrických tvarů. Free-Form Deformation (FFD[1]) parametrizace může, vzhledem ke svým schopnostem při zacházení s geometrií, být odpovědí na tuto potřebu. Adaptivní parametrizace by se měla být schopna automaticky přizpůsobit danému tvaru tak, aby byly její kontrolní body vhodně rozmístěny. Což umožní dostatečnou kontrolu deformací objektu, která zaručí možnost vytvoření optimálního tvaru objektu a splnění geometrických omezení. Primární aplikací takové parametrizační metody je deformace tvaru objektu. Dalším navrhovaným cílem je modifikace FFD parametrizační metody pro současné deformace tvaru objektu a CFD výpočetní sítě, umožnující velké deformace objektu při zachování kvality výpočetní sítě.

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