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Flight control system design for modern sailplane
Kocour, Petr ; Šplíchal, Jan (referee) ; Dubnický, Lukáš (advisor)
The thesis focuses on flight control mechanisms used in sailplanes or alternatively ultralight airplanes. The research done shows basic demands put on the flight control mechanisms and the different solutions that can be used to fulfill these demands. The research summary then compares the alternative solutions to each other. In the following chapter, the wing in subject is introduced, including its main parameters. Following is a description of the chosen variants for the flight control mechanism initial design, with explanations of why those variants were chosen. The result is a flight control mechanism initial design, which incorporates the selected properties, including for example automatic connection of separate mechanisms, differentiation of aileron deflection, different ratios of aileron to flap deflection for the inner and outer flaperon segments or placement of the summary mechanism into the wing itself. To check the suitability of the initial design, a stress calculation was carried out on what was approximated to be the part of the mechanism subjected to the most stress. The results of the FEM calculation suggested eligibility of the mechanism, showing the Von-Mises stress of 61 MPa, well below the yield strength of common aluminum alloys.
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Design of composite aeroplane wing-fuselage joint
Sadovský, Hynek ; Šplíchal, Jan (referee) ; Juračka, Jaroslav (advisor)
This master's thesis deals with design, strength calculation and technological solution of wing-fuselage joint for composite four-seater aeroplane certificated by CS-23. Design is focused on optimal space utilization, low weight and simple manufacturing and assembly. Main output is technical documentation consisting of drawings and technological lay-ups. Conceptual design was chosen after analysis and weight estimation. With strenght calculation for composite materials it was possible to design composition of primary parts and also specify manufacture processes. Assigment was solved by unusuall conceptual design, which claims higher precision manufacturing, but it saves weight.
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Design of new konception of the structural design of the main wing hinges of the Z 242
Hála, Aleš ; Augustin, Petr (referee) ; Píštěk, Antonín (advisor)
This diploma thesis deals with modernization of the Z 242 L aircraft wing. The main emphasis is given to the connection of the wing and fuselage. The new concept of both main and rear wing spar is designed together with integral fuel tank. The strength of the structure is evaluated analytically and numerically by use of Finite element analysis. Wide range of milling operations is implemented into manufacturing process as well. This thesis shows how to innovate current aircraft with respect to feasibility of the design in case of future project realization.
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Design VUT 022 Aircraft with Jet Engine according to CS-22 Regulation
Matěják, Vladimír ; Popela, Robert (referee) ; Juračka, Jaroslav (advisor)
The diploma thesis deals with the design, load calculation and stress analysis of a composite wing construction of an airplane based on the construction of the airplane VUT 001 Marabu in order to fulfil conditions of CS-22 specifications. As a part of the thesis are basic mass, moment and aerodynamic characteristic of the airplane analyzed. Also the modification of the center part of the fuselage is designed in order to enable a jet engine instalation inside the construction.
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Wing High Lift Devices
Rakovský, Kristián ; Weis, Martin (referee) ; Horák, Marek (advisor)
This bachelor’s thesis deals with wing high lift devices. Thesis states the purpose of high lift devices, their division, a brief overview of their history and a detailed description of particular devices with mentioning their advantages, disadvantages and usage in aviation. A part of the thesis also contains a short statistic, which compares wing high lift devices of high capacity transport aircraft.
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Design of Wing and Landing gear for TST 14 MC Glider
Štěpánek, Jan ; Šošovička, Róbert (referee) ; Juračka, Jaroslav (advisor)
Modification of TST-14 MC glider, calculation of flight envelope, distribution of lift on the wing, calculation of loading cases of the wing, strength check of choosen construction nodes, design of the landing gear retraction mechanism, setting up loading of landing gear according to ULKM, strength check of landing gear
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Wing system design of competition aircraft
Mahdal, Vít ; Hájek, Tomáš (referee) ; Katrňák, Tomáš (advisor)
This bachelor’s thesis deals with the wing system design of competition aircraft. The thesis consists of five main parts. The first part is an introduction to the competition – Air Cargo Challenge, and the mission of UAV. The second part details the compilation of flight envelope and loads acting on the aircraft. Part three describes stress analysis of the old fabric method of wing construction. Part four of the thesis gives suggestions of a new wing system design, and its stress analysis. The final part of this bachelor’s thesis describes the advantages and disadvantages of the new system design, and compares them to the old version.
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Wing structure
Kaňák, Ondřej ; Weis, Martin (referee) ; Jebáček, Ivo (advisor)
This bachelor’s thesis deal with the wing structure of small aeroplanes. Step by step we are discovering different kinds of constructions and their usage in aerospace industry. Characteristic signs (shape, geometric,load), advantages and disadvantages construction types are shown in this work.
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Competition aircraft F1A wing design
Jurina, Marek ; Pejchar, Jan (referee) ; Hájek, Tomáš (advisor)
This thesis deals with wing design of competition category glider F1A. Flight modes are analyzed. The following part deals with aerodynamic design of wing with the use of XFLR5 software. Maximum load is defined and its distribution along wing span. Thesis also include design of internal layout with the selection of materials. Stress analysis is executed by analytic method.
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Aircraft Flight Controls Actuator - Modeling and Control
Kolář, Bohumil ; Kopečný, Lukáš (referee) ; Pohl, Lukáš (advisor)
The aim of this bachelor thesis is to compile and control the actuator model, which approximates the behavior of a real actuator under load. The work describes individual types of actuators and their properties. The mathematical model of the actuator is also described. This model consists of a motor and a load. The mathematical model is applied in the Simulink environment where a control structure was designed and added. The work also describes the construction of the real actuator and its subsequent testing in the ControlDesk. The results of the individual test are in the form of step responses.
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