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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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Mathematical model verification for flight simulator
Kminiaková, Tatiana ; Zikmund, Pavel (referee) ; Sklenář, Filip (advisor)
The diploma thesis deals with the flight test program which is necessary to obtain the required data for EASA/FAA flight simulator certification. Flight tests are focused on flight performance and characteristics. Required regulations are selected and described. To verify the simulator model and certification parameters a flight test program was created. The flight test program is composed of flight and ground tests. In the final part of the thesis, the flight test evaluation procedure is shown. Each test contains the final valuation or recommendation for simulator model modification.
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Engine Rotax 915 for small light aircraft
Hrabovský, Matúš ; Juračka, Jaroslav (referee) ; Jebáček, Ivo (advisor)
The thesis deals with the issue of replacement of the Rotax 912 ULS engine with the Rotax 915 iSc3 B engine and its impact on flight performance, characteristics and airframe loads of the WT 9 Dynamic. For accomplish better maneuverability tail surfaces are enlarged. Both versions of airplane with different engines and tails surfaces are quantified with respect to airframe loads and flight characteristics. The output of the diploma thesis can be used for strength design of airplane structure and stress tests of the new modification of the WT 9 Dynamic aircraft.
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In-flight measurements of micro aerial vehicles
Málek, Ladislav ; Zikmund, Pavel (referee) ; Dvořák, Petr (advisor)
Bachelor thesis deals with flight measurements on selected unmanned platforms within the project Detection and monitoring of invasive spieces using unmanned aircraft. Firstly, the project itself and the platform used are presented. The theoretical part is devoted to methods of measuring flight performance. Finally, thesis contains used measurement methodology, processing and evaluating of data.
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Design of light four-seater aircraft
Mikulášek, Miloš ; Vaněk, František (referee) ; Píštěk, Antonín (advisor)
This master‘s thesis is focused on the design of four-seat metal aircraft with low take-off weight in accordance with CS-23. Main dimensions of aircraft are designed, weight analysis, aerodynamic characteristics and flight performance are calculated in this thesis. In conclusion, the estimated costs of development and production are determined.
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Optimization of flight trajectories of small aircraft
Fried, Kristián ; Procházková, Hana (referee) ; Šplíchal, Miroslav (advisor)
The thesis deals with optimization of vertical flight path of smaller aircraft, aiming to construct a mathematical model for mnimizing energy consumption during flight. The model has been set up to work with aircraft types Cessna C172 and WT9 Dynamic in accordance to their instrumentation and style of operation. The optimization model results are compared with flight data acquired from the real world operation for potential fuel burn and CO2 emmisions savings. The output of the diploma thesis may be used during flight planning or analyzing the operational fligt data.
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Mathematical model verification for flight simulator
Kminiaková, Tatiana ; Zikmund, Pavel (referee) ; Sklenář, Filip (advisor)
The diploma thesis deals with the flight test program which is necessary to obtain the required data for EASA/FAA flight simulator certification. Flight tests are focused on flight performance and characteristics. Required regulations are selected and described. To verify the simulator model and certification parameters a flight test program was created. The flight test program is composed of flight and ground tests. In the final part of the thesis, the flight test evaluation procedure is shown. Each test contains the final valuation or recommendation for simulator model modification.
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Engine Rotax 915 for small light aircraft
Hrabovský, Matúš ; Juračka, Jaroslav (referee) ; Jebáček, Ivo (advisor)
The thesis deals with the issue of replacement of the Rotax 912 ULS engine with the Rotax 915 iSc3 B engine and its impact on flight performance, characteristics and airframe loads of the WT 9 Dynamic. For accomplish better maneuverability tail surfaces are enlarged. Both versions of airplane with different engines and tails surfaces are quantified with respect to airframe loads and flight characteristics. The output of the diploma thesis can be used for strength design of airplane structure and stress tests of the new modification of the WT 9 Dynamic aircraft.
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Conceptual design of high performance glider with electric propulsion (in complience with EASA CS-22)
Hlůšek, Josef ; Sklenář, Filip (referee) ; Hlinka, Jiří (advisor)
This master's thesis is focused on conceptual design of glider with electric propulsion system following the CS-22 regulation. Statistical analysis of the glider with an auxiliary electric engine has been carried out in order to determine basic design parameters for conceptual design. Based on analytical drag polar, the flight performance parameters are calculated, in particular flight range and influence of the solar panels on the flight range. This thesis also includes preliminary design solution of accumulator placement within the wing.
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Influence of wing design modification on aircraft polar curve
Mixová, Alexandra ; Matějů, Jiří (referee) ; Navrátil, Jan (advisor)
This thesis focuses on determining the polar curve of Roko NG aircraft, its evaluation and design of possible wing modification; on the influence of said modification on the polar curve and determination of basic flight performance. The introduction explains basic concepts and problems of aerodynamics. The following part discusses the particular type in comparison with similar ultralight aircrafts. Measurement determines the actual polar curve which can be compared to the analytically determined polar curve of the existing airplane, and to the analytically determined polar curve of the plane with modified wing. From this newly defined polar curve, the basic flight performance is expressed and compared with the flight performance of the existing aircraft.
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