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Wing leading edge active flow concept analysis
Mahdal, Vít ; Zikmund, Pavel (referee) ; Popela, Robert (advisor)
This research is focused on substitution of commonly used High-Lift devices by active flow control on the wing leading edge. The analysis is done by CFD tools with use of Reynolds-Averaged Navier-Stokes (RANS) method. In the beginning of the research, commonly used High-Lift devices are described. Solver setting and its explanation together with verification and validation is described in the following chapters. An active flow control concept is testing at the LS(1)-0413 airfoil, for 5 different positions of slots, two different slots widths (h/c= 0,0025 and 0,005) and two different blowing velocities (v_Jv_=2,22 and 4,44). In the end of this paper, physical phenomena of blowing is described together with evaluation of different cases. The best case is compared with Fowler and slotted flap at Reynolds number 2,2 million.
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Space mission design
Koziel, David ; Navrátil, Jan (referee) ; Zikmund, Pavel (advisor)
In this work, there are basic laws and knowledge relating to space flights into an orbit around the Earth. Also, there are instructions for beginners, who want to work with the GMAT program (General Mission Analysis Tool), which is the program used for designing space missions. In the final part of the work, there is also a use of the program demonstrated on a specific mission of a satellite (CubeSat) into the Geostationary Earth Orbit. In this section, there is a described method of work, individual relevant functions of the program and possibilities, and a way of work in it. Finally, graphical and data outputs of the simulation are evaluated. Therefore, the output of the work is complex characteristics of the basics of problems of space mission design and a brief GMAT software guide, which could be used in the future to teach.
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Aerodynamic design of transonic UAV glider
Kóňa, Marián ; Pejchar, Jan (referee) ; Zikmund, Pavel (advisor)
This master thesis is focused on aerodynamic design of transonic glider, which is assigned for following an airliner at cruising regime of flight. Main goal of the thesis is to determine basic geometrical design of airplane with respect to Whitcomb aera rule, mass analysis and drag polar. Weight analysis includes determining center of gravity according to longitudinal static stability margin. The drag polar of the airplane is determine for cruising regime of flight, that means the regime of following an airliner.
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Assistant systems in car and aircraft control
Novotný, Timotej ; Horpatzká, Michaela (referee) ; Zikmund, Pavel (advisor)
The bachelor thesis deals with assistance systems in cars and aircraft. The aviation sector is focused on GA aircraft. This thesis describes assistance systems used in cars and aircraft, their contribution to traffic safety and limitations of these systems. The comparison of assisting systems in the automotive and aviation industries shows the difference in the speed of development in individual areas, which is caused mainly due to strict requirements for safety and reliability of aviation systems. Furthermore, we can see the difference in implementation of systems monitoring the condition of a driver/pilot. Although the work of a pilot is more demanding than the work of a driver, today’s aircraft do not have a system for monitoring the condition of a pilot or an emergency landing system. Part of the thesis concerning future assistance systems in aviation is devoted to the system monitoring the pilot’s condition and the automatic landing system. Both systems are still under development. However, experiments have shown that these systems could be implemented in future aircraft and increase aviation safety. The last part of the thesis mentions the future of assistance systems, which create a path to autonomous vehicles.
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Matlab Simulink for Flight Mechanics II module
Černota, Jiří ; Zikmund, Pavel (referee) ; Matějů, Jiří (advisor)
The thesis is about the use of Matlab Simulink software for subject Flight Mechanics II. User interface, which allow computing of aerodynamic derivations and state space matrices, was created. It also provides system for launching simulations of longitudinal aircraft movement in Simulink environment and results visualization. In the last part were suggested examples for practice lessons of the aforementioned subject. These lessons focus on mastering basic block programming and to understand concept of aircraft dynamics and controlling aircraft movement.
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Flight performance analysis of the airplane VUT 081 KONDOR
Kerndl, Jindřich ; Daněk, Vladimír (referee) ; Zikmund, Pavel (advisor)
The aim of this diploma thesis is to analyse flight performance of airplane VUT-081 Kondor. The first part focuses on determination and estimation of aerodynamic characteristics of the airplane. Based on this data flight performance was calculated and evaluated according to CS-ELSA. The last part is dedicated to comparison of flight performance of VUT-081 Kondor with other similar airplanes.
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Overview of the development of flying cars
Kosír, Samuel ; Zikmund, Pavel (referee) ; Daněk, Vladimír (advisor)
This bachelor’s thesis is an overview of flying cars. The first part of the thesis describes their design. This part is further split into sections about technical requirements, take-off & landing modes, pilot modes, power types, propulsion system architectures, and transition between airplane mode and vehicle mode. In the second part is closely described development of flying cars in chronological order. The third part addresses legislative problems and regulations that apply to flying cars.
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Reentry CubeSat
Kopecký, Matěj ; Daněk, Vladimír (referee) ; Zikmund, Pavel (advisor)
This bachelor´s thesis deals with the analysis of the re-entry of the miniature CubeSat satellite from lower orbit. In the opening section, it is explained how re-entry process works, what bodies are typically used and the possibilities for protecting them from atmospheric resistance. The thesis is also focused on the mentioned group of CubeSat satellites and defines them according to general requirements. Using the knowledge learned from the opening section, a theoretical introduction to the preliminary analysis of the re-entry of the CubeSat satellite was put together, followed by a sample calculation. Here, it is explained how the CubeSat moves as it descends throughout the atmosphere and what parameters it needs to meet in order to make the re-entry.
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