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Retractible landing gear design for Z 143 LSi airplane
Gregor, Jiří ; Vaněk, František (referee) ; Píštěk, Antonín (advisor)
The diploma thesis deals with the design of the replacement the Z 143 LSi landing gear with the new VUT 100 type landing gear in a retractable system. The first part of this thesis is devoted to the description of the Z 143 LSi aircraft and its landing gear and the description of the retractable landing gear type VUT 100. The next part describes the possible variants of the installation the VUT 100 landing gear, which are critically evaluated. Then there is selected the final variant for the installation, which is designed in Catia V5 software. The final design includes remotorization with Lycoming IO-390 and new design of engine bed. For the proposed solution, a new mass analysis with the calculation of centrations, new cases of ground load, a new flight envelope of load and additional cases of load of a new engine bed are prepared. The proposed engine bed is analyzed by the finite element calculation method in the MS Patran software. Finally, a possible scheme of the chassis retraction system is proposed.
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Replica Design of L-40 "Meta Sokol " Airctaft - fuselage
Růžička, Miroslav ; Pešák, Miroslav (referee) ; Píštěk, Antonín (advisor)
This diploma thesis deals with the design of all-metal construction of fuselage of the replica L-40 Meta Sokol aircraft on the basis of CS-VLA regulation. As far as the aircraft is concerned, the thesis establishes the load of tail surfaces, landing gear and engine bed. Futhermore, it designs the construction of fuselage, tail landing gear, including the system of its retraction, wing-fuselage connection, engine bed and the primary design of cockpit. In the end, the thesis focuses on the fuselage production technology.
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Design of single seat aiirplane by the UL - 2 regulation
Kövér, Ondřej ; Schoř, Pavel (referee) ; Píštěk, Antonín (advisor)
Bachelor´s thesis solves conceptual design of oneseater aircraft by the UL-2 regulations, that is up to 300 kilograms of take-off weight. In the first part of the thesis, there is survey of similar aircrafts and summary of their important characteristics. In further section are possible conceptions and the best choice of them outlined. Afterwards are characteristics of carrier surfaces, load calculation and flight envelope mentioned. The last part deals with calculation and design of engine mounting.
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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.
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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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Aircraft design for the installation of a hybrid powerplant
Kapoun, Tomáš ; Bencalík, Karol (referee) ; Píštěk, Antonín (advisor)
The master‘s thesis "Aircraft design for the installation of a hybrid powerplant" is focused on the design of the airplane suitable for hybrid powerplant. At the same time it is also deal with the most suitable location of the components necessary for this powerplant. These components are: a combustion engine, electric motor, gearbox and bed engine. Part of the master thesis is application-mount designed components: location and number of containers with batteries, a proposal for a new engine bed suitable for a hybrid powerplant. In the sub - section of the thesis is made a simple calculation of the economic return on investment from the perspective of the end-user aircraft with a hybrid powerplant.
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Design installation of motors ROTAX for aircraft SKYLEADER 400
Rakušan, Miroslav ; Katrňák, Tomáš (referee) ; Mališ, Michal (advisor)
The bacheloir thesis is focused to calculation forces in engine mount, design and construction of engine mount for engines Rotax 912iS and 914UL, which will be instalated to ultralight plane Skyleader 400. In the first part is short search about planes, which use the engines. Then the engine mount is calculate according to rule UL2-I.part. After the MKP analysis is calculation of screws, which hold the engine mount onto the firewall. In the end of the thesis is installation both of engines in the nose of the plane and engine mount test draft according to rule UL2-I.part.
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Design of VUT 051 RAY aircraft with hybrid power unit
Zeman, Petr ; Bencalík, Karol (referee) ; Píštěk, Antonín (advisor)
The master´s thesis deals with a design of hybrid power unit for a small aircraft. The Introductory part goes into the problems of hybrid power unit and describes its current use in aviation. In the next part of the thesis aircrafts VUT 051 RAY and Skyleader 600 are described and the aircraft with better aerodynamic characteristic is chosen. A suitable conception of hybrid power unit is proposed for this aircraft. On the basis of the proposed conception basic flight performance are figured out. After that a weight and blance analysis are made with the chosen power unit components and thair arrangement. In the final part electric motor mounting and a frame for holding batteries are designed.
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Turboprop powerplant installation into small twoseater airplane
Kövér, Ondřej ; Jebáček, Ivo (referee) ; Juračka, Jaroslav (advisor)
The diploma thesis deals with the problem of application of turboprop engine to a small 2-seater airplane. In the first part, reasons why the application is in considered are stated. Then, the air-plane is characterised, the choice of the most suitable engine, propeller and the weight analysis is made and the centres of gravity are calculated. For chosen engine and propeller, in chapter 6, the flight performance is calculated. In chapter 7 follows calculations of flight envelopes and the lim-it positive and negative load factor is stated. Flight envelopes calculations are followed by the calculation of engine mount loads of flight and ground cases. In chapter 9, the design of engine mount, inlet and outlet system and positioning of important elements are solved. The design part is followed by strength analysis of engine mount and its attachment into engine partition.
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