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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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Competition aircraft wing tips
Zima, Martin ; Koutník, Tomáš (referee) ; Doupník, Petr (advisor)
This bachelor thesis deal with wing tip design of airplane for competition. Airplane named FabricK I is design for Air Cargo Challenge competition. The first part of bachelor thesis is focused on description of competition and flight aircraft modes. Hereafter are compared the types of wing tips. Most suitable wing tip is then applied on FabricK I.
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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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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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Wing design for single-engine four-seat aircraft
Rybka, Slavomír ; Juračka, Jaroslav (referee) ; Jebáček, Ivo (advisor)
The content of the thesis is familiarization with the aircraft TL4000 and technical parameters wings. The work includes calculation of flight envelopes as prescribed CS 23 in three weight configurations and load calculation for all points of the envelope. The work is carried out structural design wings and its elements. The stress analysis of individual design elements wing is designed to specific parts of the reserve factor. Part of the thesis is the design and methodology for the static strength test wing that required a prescription for that category of aircraft (CS 23).
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Design of Sailing Boat
Křížová, Barbora ; Řezníček, Svatopluk (referee) ; Křenek, Ladislav (advisor)
The topic of this master‘s thesis is design and analysis of a sailing boat in accordance with ergonomic and technological requirements. The goal is to create a sailing boat, which will be modern, visually interesting and which and which will take future development of both design and technology into account.
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Design of winglet for LS-3 glider
Koutník, Tomáš ; Šošovička, Róbert (referee) ; Popela, Robert (advisor)
This diploma thesis describes the design of winglets for LS-3 glider. The method for determination of main winglet parameters based on selected criterion is presented as well as comparation of performace of original wing and final modification. It also includes analysis of wing loading and resetting of speed and weight limits for flying with winglets.
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Design of hydrogen pressure tank installation on the VUT 001 Marabu wing
Koštial, Rostislav ; Juračka, Jaroslav (referee) ; Píštěk, Antonín (advisor)
The content of this Master thesis to design installation of hydrogen pressure tanks for airplane VUT RAY 051. Survey was conducted of the available fuel cell on the market. Position of the tank was chosen over the wing using components for mounting a jet engine TJ100 M for aircraft VUT 001 MARABU. For fuel tanks were designed fairings. Further was calculated mass and centre of gravity analysis of aircraft, basic flight performance of aircraft and the drag variation in the location of the tanks above the wing. Further the strain and strength of hinges was calculated.
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