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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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Evaluation of economical and operational requirements on new towing aeroplane for AeČR
Titz, Tomáš ; Chlebek, Jiří (referee) ; Šplíchal, Miroslav (advisor)
The aim of the master's thesis is to provide the analysis of the composition of towing used by flying clubs in the Czech Republic. Another part of the analysis is the comparison of home towing types with types used abroad. Another aim is to analyse legislative and operating demands on towing types used in the Czech Republic and process procedures of safety and effective towing. Based on these findings the author formulates economic and operating requirements which an ideal tow plane should meet and compare these requirements with attributes available on the market.
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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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Installation of the LYCOMING power unit into the Bristel UL aircraft
Kročil, Petr ; Juračka, Jaroslav (referee) ; Píštěk, Antonín (advisor)
This diploma thesis focuses on Lycoming drive unit mounting used in two-seater plane of VLA category (the very light aircraft). In the beginning characteristics of currently produced Bristell aircrafts are described. Following chapters aim at research selection of new drive unit mounting based on multi-criteria decision analysis. For selected unit, the weight, center of mass and flight performance are calculated. Additionally, the construction of engine mount is proposed. According to CS-VLA and CS-23 stress level of mounting is defined followed by strength verification. Later in this thesis, a suitable engine cover for engine and cockpit cooling is proposed. A complete fuel system is described in following chapter. Last chapter deals with financial costs of re-engining as well as aircraft operational costs.
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Conversion possibilities of piston twin engine Beechcraft B60 Duke aircraft into prop-jet aircraft
Skládal, Zdeněk ; Šošovička, Róbert (referee) ; Šplíchal, Miroslav (advisor)
Master’s thesis deals with the issue of a conversion of a twin-engined piston aircraft Beechcraft B60 Duke into turboprop engines Walter M601 or Pratt & Whitney Canada PT6.The paper focuses on a financial analysis of conducting of the conversion, resources needed for a certification, authorization for the traffic in the Czech Republic and determination of the rate of return on investment.The thesis further deals with elaborating of the flight and prerformance characteristics, operation costs of both of the proposed engines and compares them with current characteristics and operation costs.
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Universal characteristics of piston engines with a propeller
Šafránek, Martin ; Matějů, Jiří (referee) ; Zikmund, Pavel (advisor)
Determining the characteristics of piston engines with a propeller is a complex task. Accurate calculations are based on engine and propeller characteristics from the manufacturers, which are, however, quite demanding. It is also possible to use simplified models that can predict the achievable values of propeller efficiency and fuel consumption. They are based on a simple propeller efficiency and maximum power. However, these models are often very inaccurate, which is a significant disadvantage. Therefore, it is possible to use the universal characteristics of propeller propulsion units, which offers a more accurate calculation of power and fuel consumption using a relatively simple model. The diploma thesis deals with a summary description of all characteristics of reciprocating internal combustion engines and propellers. A mathematical model was created here, which works according to a certain algorithm based on the joint work of the engine and the propeller. This model can predict the required power and fuel consumption in different flight modes much more accurately. The results were applied to the performance of ultralight aircraft, especially to the range, which was significantly increased.
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Universal characteristics of piston engines with a propeller
Šafránek, Martin ; Matějů, Jiří (referee) ; Zikmund, Pavel (advisor)
Determining the characteristics of piston engines with a propeller is a complex task. Accurate calculations are based on engine and propeller characteristics from the manufacturers, which are, however, quite demanding. It is also possible to use simplified models that can predict the achievable values of propeller efficiency and fuel consumption. They are based on a simple propeller efficiency and maximum power. However, these models are often very inaccurate, which is a significant disadvantage. Therefore, it is possible to use the universal characteristics of propeller propulsion units, which offers a more accurate calculation of power and fuel consumption using a relatively simple model. The diploma thesis deals with a summary description of all characteristics of reciprocating internal combustion engines and propellers. A mathematical model was created here, which works according to a certain algorithm based on the joint work of the engine and the propeller. This model can predict the required power and fuel consumption in different flight modes much more accurately. The results were applied to the performance of ultralight aircraft, especially to the range, which was significantly increased.
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Installation of the LYCOMING power unit into the Bristel UL aircraft
Kročil, Petr ; Juračka, Jaroslav (referee) ; Píštěk, Antonín (advisor)
This diploma thesis focuses on Lycoming drive unit mounting used in two-seater plane of VLA category (the very light aircraft). In the beginning characteristics of currently produced Bristell aircrafts are described. Following chapters aim at research selection of new drive unit mounting based on multi-criteria decision analysis. For selected unit, the weight, center of mass and flight performance are calculated. Additionally, the construction of engine mount is proposed. According to CS-VLA and CS-23 stress level of mounting is defined followed by strength verification. Later in this thesis, a suitable engine cover for engine and cockpit cooling is proposed. A complete fuel system is described in following chapter. Last chapter deals with financial costs of re-engining as well as aircraft operational costs.
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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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|
|
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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