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Development of the aircraft control devices
Stanislav, Filip ; Zikmund, Pavel (referee) ; Daněk, Vladimír (advisor)
This bachelor thesis handles by literature research the development of airplane control devices since end of the 18th century. The principle of airplane control using three rotational degrees of freedom is known since beginning of 20th century, but there were many attempts to find this principle more than hundred years ago. The three axis control system was used for the first time by Wright brothers and has been used since then. The particular design of the airplane control surfaces is nowadays selected with regard to aerodynamical properties with requirements of minimum weight and adequate strength. An increasing control forces on control stick and pedals in airplane cocpit due to demanding requirements to maneuverability and speed of flight do not allow pilot comfortable and easy driving. Therefore it is necessary to influence this forces. In the text there are described possibilities of influencing them such as problems of feedback from control surfaces to pilot. This thesis gives a comprehensive overview of development of airplane control principles and gives the summary of classical and unconventional airplane control devices.
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Flight performance of competition RC airplane
Majtán-Černák, Tomáš ; Zikmund, Pavel (referee) ; Hájek, Tomáš (advisor)
This Bachelor thesis is dealing with designing procedures for measuring flight performances of aircraft model, built according to Air Cargo Challenge 2015 competition regulations. Firstly, the competition is introduced, together with its requirements and regulations. Then, aircraft with its basic design parameters is presented. As a basis for designing flight test, thesis includes introduction of theory on this matter. Finally, Bachelor thesis contains measurement methodology itself as well as evaluation of the results.
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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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Aerodynamic Characteristics Identification of Atmospheric Airplane from Flight Measurement Results
Zikmund, Pavel ; Salga,, Jaroslav (referee) ; Jebáček, Ivo (referee) ; Daněk, Vladimír (advisor)
The thesis deals with aerodynamic characteristics identification from flight measurement. The topic is part of flight mechanic – handling qualities. The first theoretic part consists of three identification methods description: Error equation method, Output error method and Filter error method. Mathematical model of an airplane is defined and restricted to the motion with 3 degree of freedom. There is also introduced simulation of flight measurement for identification software validation. Practical part is focused on experiment preparation, execution and evaluation. The airplane VUT 700 Specto had been chosen to carry out flight tests. The airplane was modified to the new electric powered VUT 700e Specto after first measurement flights with combustion engine. Data record from on-board measurement unit was completed by telemetric data from autopilot and remote control system. Flight tests were carried out in stabilised mode of autopilot in symmetric flight. The results were confronted with analytical analysis results and DATCOM+ software parameter estimation.
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Aerodynamic Characteristics Identification of Atmospheric Airplane from Flight Measurement Results
Zikmund, Pavel ; Salga,, Jaroslav (referee) ; Jebáček, Ivo (referee) ; Daněk, Vladimír (advisor)
The thesis deals with aerodynamic characteristics identification from flight measurement. The topic is part of flight mechanic – handling qualities. The first theoretic part consists of three identification methods description: Error equation method, Output error method and Filter error method. Mathematical model of an airplane is defined and restricted to the motion with 3 degree of freedom. There is also introduced simulation of flight measurement for identification software validation. Practical part is focused on experiment preparation, execution and evaluation. The airplane VUT 700 Specto had been chosen to carry out flight tests. The airplane was modified to the new electric powered VUT 700e Specto after first measurement flights with combustion engine. Data record from on-board measurement unit was completed by telemetric data from autopilot and remote control system. Flight tests were carried out in stabilised mode of autopilot in symmetric flight. The results were confronted with analytical analysis results and DATCOM+ software parameter estimation.
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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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Conceptual design of air- mobil
Podhorský, Matěj ; Zikmund, Pavel (referee) ; Píštěk, Antonín (advisor)
The topic of the thesis is a conceptual design of a roadable aircraft. The comparison of existing concepts is made, as well as description of proposed solution, aircraft mass analysis, basic aerostatic calculations, flight and gust envelope calculation and a design of truss construction of the fuselage. The CS-VLA, alternatively ELSA-K, has been used as a certification base. The compliance to this certification specification is one of the goals of this thesis.
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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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Stability and controllability evaluation of the four-seater, single-engined airplane
Matějů, Jiří ; Zikmund, Pavel (referee) ; Daněk, Vladimír (advisor)
The diploma thesis deals with evaluation and suggestion of changes for the conceptual design of an airplane TL4000 in terms of stability and controllability. In the first part there are determined stability and controllability derivativations of the aircraft. Thereafter are estimated aircraft weight, moment of inertia and necessary geometric characteristics. In the second part there are calculated stability criteria for a sample case. In the third part, on the basis of this calculation, a program is created. This program combines the advantages of MS Excel, Matlab and Matlab Simulink. By means of this program criteria of stability and controllability were calculated parametrically for different regimes of flight, identified critical cases and compared with the requirements of CS-23rd. Based on this evaluation were recommanded modifications of the conceptual design TL4000.
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