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Tail Units
Dula, Jan ; Mališ, Michal (referee) ; Urík, Tomáš (advisor)
In this bachelor´s thesis is created a survey of constructive solutions and lay-out of horizontal tail unit, solutions of horizontal stabilizer attachment and ways to control the elevator. In the introductory part the term which is used in this thesis are briefly explained. In the following part the possible configurations of the tail units are listed. From these configurations, some solutions are selected and they are closely classified. Any of these solutions provides a short description of the elevator control, the advantages and the disadvantages of this solution, an overview of selected horizontal stabilizer attachment and their detailed description.
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Sandwich panels analysis under compressive load using finite elements methods
Seman, Matúš ; Löffelmann, František (referee) ; Mališ, Michal (advisor)
Bachelor thesis deals with possibilities of numerical modeling failure mechanism in sandwich panels using final element methods. The first part of the thesis presents theoretical introduction to requirements of sandwich structures and either mathematic formulation of constitutive relations. The purpose of the thesis was to set suitable approcahes of formulation instability problems with applying on laboratory samples. The analysis was done using nonlinear solvers in programes Patran/Nastran and the results have been properly evaluated with experimental work and analytical approach.
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Design of a aircraft for towing and basic acrobtics
Loutocký, Jiří ; Šošovička, Róbert (referee) ; Mališ, Michal (advisor)
This master thesis solves conceptual design of aerotow airplane and airplane for basic aerobatics. Airplane is designed by using of specification CS-23. The first part of the thesis solves conceptual design. Especially possible concepts and choice the best one according to requests. Next part deals with flight performance of aerotow airplane in normal flight and also in aerobatics. The third part is engaged in main flight performance in aerotow. 3D system model of whole aircraft and compact disk with mentioned 3D model and electronic version of thesis is also added.
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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.
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Design of an aircraft for towing according to CS-VLA
Marek, Ondřej ; Urík, Tomáš (referee) ; Mališ, Michal (advisor)
The topic of the thesis is a design of an aicraft for towing of gliders. Based on the background research of the towing aircrafts currently used by the Czech aeroclubs and the analysis of the required characteristics of these aircrafts the design of the new airplane has been created. Moreover, the load of engine mount has been determined according to the CS-VLA directive (a certification guidelines for the Very-light aircrafts). Its construction design as well as strength calculation have been elaborated. The part of the thesis is a 3D model of the aircraft and the engine mount.
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Numerical simulations of low velocity impact on composite panels
Odehnal, Ondřej ; Šplíchal, Jan (referee) ; Mališ, Michal (advisor)
This master thesis focuses on modelling and simulation of impact tests of composite panels. Simulations and analysis were made by using Finite Element Method in software MSC Patran and Dytran. The first part of the thesis deals with describing the properties of composite panels during impact testing and other cases of impacts on composite structures. Next part deals with the used models and results from Dytran. These results are compared with experimental data from real low-velocity impact tests. Part of the thesis is devoted to impact on panels with the stacking sequences which is supposed to be used for design of air duct for airplane Aero L-39NG.
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