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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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Solution of Powertrain Dynamics in Vehicle
Hodas, David ; Drápal, Lubomír (referee) ; Novotný, Pavel (advisor)
The main aim of this diploma thesis is to evaluate and select the most appropriate option how to mount a power unit in Formula Student vehicle. It assesses an overall dynamic behaviour of a drive unit mounted in student formula. At the end of the final thesis is an assessment of proposed engine mount variants. The study of parameters that most influence engine vibrations can be seen there.
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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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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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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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Remotorization of the L60 aircraft
Sahrai, Daniel ; Bartoněk, Jaroslav (referee) ; Imriš, Pavel (advisor)
The subject of the diploma thesis is the replacement of the power unit to the Aero L-60 "Brigadýr" aircraft. The reason for such a conversion is the ending life of the original power unit, accumulating technical problems and the effort to achieve higher aircraft performance during normal operation. In the introduction, the aircraft is introduced and there are mentioned the results achieved in the selection of a suitable power unit during the previous work. Furthermore, the work briefly deals with the issue of certification and selection of a suitable method that will lead to the approval of the change and to maintain the airworthiness of the aircraft. The work also addresses the effects of reconstruction on the center of gravity of the aircraft, which are minimized by the appropriate design of the engine mount. The model of such a engine mount was created in the computer software CATIA V5 and subsequently a strength analysis of nine loading cases was performed on it. Furthermore, an analytical inspection of the engine bed tubes on the struts and a check of the strength of the bolts connecting the engine mount to the aircraft airframe were performed. At the end of this work is described the practical installation of the engine and engine mount, including other engine systems.
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Reconstruction of Sport Aircraft M-2 Skaut - Mounting of Power Unit.
Zakopal, Libor ; Vaněk, František (referee) ; Kubíček, Petr (advisor)
This diploma thesis deals with the design of an engine mount for the M-2 Skaut aircraft on the basis of LSA and CS-VLA specifications. It is divided into several sections: analysis of input conditions, determination of factors which influence the geometry, the main design and its verification using the Finite Element Method. The FEM is compared with an analytical solution to determine its accuracy. This thesis also deals with a selection of acceptable propelers for this engine along with a basic design of an oil and fuel system.
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Remotorization of the L60 aircraft
Sahrai, Daniel ; Bartoněk, Jaroslav (referee) ; Imriš, Pavel (advisor)
The subject of the diploma thesis is the replacement of the power unit to the Aero L-60 "Brigadýr" aircraft. The reason for such a conversion is the ending life of the original power unit, accumulating technical problems and the effort to achieve higher aircraft performance during normal operation. In the introduction, the aircraft is introduced and there are mentioned the results achieved in the selection of a suitable power unit during the previous work. Furthermore, the work briefly deals with the issue of certification and selection of a suitable method that will lead to the approval of the change and to maintain the airworthiness of the aircraft. The work also addresses the effects of reconstruction on the center of gravity of the aircraft, which are minimized by the appropriate design of the engine mount. The model of such a engine mount was created in the computer software CATIA V5 and subsequently a strength analysis of nine loading cases was performed on it. Furthermore, an analytical inspection of the engine bed tubes on the struts and a check of the strength of the bolts connecting the engine mount to the aircraft airframe were performed. At the end of this work is described the practical installation of the engine and engine mount, including other engine systems.
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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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