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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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Replica Design of L-40 "Meta Sokol " Aircraft - wing
Pluhař, Tomáš ; Jebáček, Ivo (referee) ; Píštěk, Antonín (advisor)
This diploma thesis targets in concept of wing, aileron, flap and main undercarriage of the ultralight replication of the plane L-40 called Meta Sokol. The thesis developed from cooperation with two other members of the team – Alice Lipková (aerodynamics, power) and Miroslav Růžička (fuselage, tail unit and rear gear). The first part of this diploma thesis is concerned with load and concept of structure of the wing. At first the flight envelope is specified, then charakteristics of shearing force, bending moment and torsion moment are determined spanwise. The concept and subsequent strength verification of structure of the wing is also solved. The same process is claimed to concept of the aileron and the flap. The second part of this diploma thesis is dealt with main landing gear, its support, structure, springing and the principle of retraction. The final passage is devoted to load of the undercarriage.
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Wing fatigue safe life investigation of single-engine multipurpose aircraft
Hubáček, Jan ; Juračka, Jaroslav (referee) ; Chybík, Ladislav (advisor)
Práce se zabývá stanovením bezpečné únavové životnosti křídla. Letadlo, které bylo podrobeno analýze, je vzpěrový hornoplošník celokovové konstrukce. Letadlo je certifikováno na základě předpisu FAR 23 Amendment 23-46. Výpočet bezpečné únavové životnosti musí být proveden v souladu s požadavky předpisu FAR 23 a jeho poradními oběžníky.\\ Teoretická část práce je věnována hlavně přehledu literatury a představení projektu, kde byla stručně shrnuta jeho historie vzniku. Část přehledu projektu také pojednává o podstatě požadavku na posouzení bezpečné únavové životnosti zadavatelem. V další části byl rovněž proveden rozbor literatury týkající se únavy. Jednalo se zejména o rozbor předpisu FAR 23, jeho poradních oběžníků a obecně literatury vztahující se k únavě jak v letectví, tak v obecném strojírenství.\\ Druhá část diplomové práce byla zaměřena zejména na výpočetní analýzu a vývoj specializovaného software. Výpočetní část obsahovala zejména přípravu vstupů, včetně obálek zatížení, stanovení typického letu, výpočet zatížení křídla a napjatostní analýza ve vybraných řezech křídla. Z výstupů prvotní analýzy se následně provedl výpočet poškození a životnosti pro daný typový let.
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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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Aspects impact trends in the operation technology of civil aviation aircraft
Korytář, Jan ; Šplíchal, Miroslav (referee) ; Chlebek, Jiří (advisor)
The aim of the work is a general description of the effects on air traffic and aircraft. The first part of the work is devoted to a brief description of the development of individual technical parameters and performance of aircraft from the 1920s to the present with an assessment of the effects. The second part of the work is about the influence of current requirements and the third part is a general view of the future development of construction and technology for more economical and environmentally friendly air transport
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Museum of warfare
Dvouletý, Martin ; Pilgr, Milan (referee) ; Barnat, Jan (advisor)
The subject of the Bachelor thesis is the design and assesssment of the steel (load bearing) structure of the future museum of military equipment. The building, with passageway for the visitors, is going to serve museum for garaging medium and heavy equipment. The framework is constructed by connection of abutment pillars placed in the distance of 10 m and roof girders with haunches. Construction is designed to have mono-pitched roof created by 5,36 m long pillar and 6,4 m long pillar connected with girder. In the endwise direction the frames are in the distance of 6 m. The construction is specific by its plan. By its cranking at the end of the first wing under 45° angle there is created smaller interstice. At the end of the interstice is another 45° angle cranking connected to the second wing. Thanks to the cranking between the wings the first wing extends endwise and the second extends crosswise. Another specifics are gate constructions placed on the side of the higher pillars. The gate is intended for enterance and exit of the military equipment to be placed for an exposition in the museum. The framework is designed by norms ČSN EN for the ultimate and serviceability limit state. As the main material used for load-bearing elements was steel S355.
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Preliminary aerodynamic analysis of remotely controlled model with jet propulsion
Novák, Ondřej ; Zikmund, Pavel (referee) ; Popela, Robert (advisor)
This bachelor´s thesis deals with aerodynamic analysis of unmanned aircraft and subsequent changes to design of wing, its position and wing-fuselage junction. In this work emphasis is laid on flow separation, its interaction with other flow structures and its influence on aerodynamic properties. The goal of these changes to the aircraft is ensuring sufficient stability and controllability in low as well as high angle of attack flight. AVL, XFLR5 and CFD methods were used in the thesis. In case of inaccuracy of CFD calculation, two backup wing related modifications were prepared.
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