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Propulsion unit of competition model airplane
Vančo, Miroslav ; Matějů, Jiří (referee) ; Hájek, Tomáš (advisor)
This bachelor´s thesis deals with the design and validation of the operation of the model propulsion system, according to the Aero Design East rules. The introduction is focused on rules and regulations of the competition and then, the point analysis is carried out. The research section is devoted to an overview of the propulsion system components and their basic parameters. The most appropriate configurations of the propulsion system are selected, based on calculations from the manufacturer´s datasheet. These configurations are then validated by measurements of static thrust and measurements in aerodynamic tunnel. In these measurements, the responses of the limiter for boundary power are also examined. In the last part, the choice of the propulsion system is completed.
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Design of the propulsion unit of the competition model airplane with vertical take-off and landing
Pilát, Adam ; Navrátil, Jan (referee) ; Hájek, Tomáš (advisor)
This bachelor’s thesis was written in order to design the propulsion system for a vertical takeoff and landing competition model airplane intended to participate in the New Flying Competition 2022. The task of the thesis was to analyze the rules of the competition and design the propulsion system. The research section includes an analysis on the competition’s rules followed by a review of the propulsion system components. In the next section, a basic analysis of the parameters of the airplane is performed for the purpose of the airplane fulfilling the competition requirements. In the last part of the thesis, a propulsion system components selection method is proposed and carried out. The output of the thesis is a propulsion system suitable for use in the designed airplane.
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Design for building an electric drive into a Orlican VSO-10 Gradient glider
Vančo, Miroslav ; Juračka, Jaroslav (referee) ; Sklenář, Filip (advisor)
This diploma thesis deals with the design of building electric propulsion (FES) into an Orličan VSO-10 Gradient glider. The introduction is focused on problem statement with main challenges of building electric propulsion into gliders. The research section is devoted to current situation on the market of gliders with overview of the propulsion systems and their basic parameters. The most appropriate configuration of the propulsion system is selected, based on performance calculations, regulations, and requirements. For final configuration, installation into the glider construction is designed, with respect to actual regulations. In the last part, cost of propulsion and installation is calculated.
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Design of the propulsion unit of the competition model airplane with vertical take-off and landing
Pilát, Adam ; Navrátil, Jan (referee) ; Hájek, Tomáš (advisor)
This bachelor’s thesis was written in order to design the propulsion system for a vertical takeoff and landing competition model airplane intended to participate in the New Flying Competition 2022. The task of the thesis was to analyze the rules of the competition and design the propulsion system. The research section includes an analysis on the competition’s rules followed by a review of the propulsion system components. In the next section, a basic analysis of the parameters of the airplane is performed for the purpose of the airplane fulfilling the competition requirements. In the last part of the thesis, a propulsion system components selection method is proposed and carried out. The output of the thesis is a propulsion system suitable for use in the designed airplane.
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Propulsion unit of competition model airplane
Vančo, Miroslav ; Matějů, Jiří (referee) ; Hájek, Tomáš (advisor)
This bachelor´s thesis deals with the design and validation of the operation of the model propulsion system, according to the Aero Design East rules. The introduction is focused on rules and regulations of the competition and then, the point analysis is carried out. The research section is devoted to an overview of the propulsion system components and their basic parameters. The most appropriate configurations of the propulsion system are selected, based on calculations from the manufacturer´s datasheet. These configurations are then validated by measurements of static thrust and measurements in aerodynamic tunnel. In these measurements, the responses of the limiter for boundary power are also examined. In the last part, the choice of the propulsion system is completed.
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