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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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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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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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Load State of an Aircraft with an Elastic Wing
Schoř, Pavel ; Daněk, Vladimír (referee) ; Slavík, Svatomír (referee) ; Píštěk, Antonín (advisor)
V této práci je navržena metoda výpočtu zatížení letadla s netuhým křídlem, založená na spojení panelové metody prvního řádu dle Katz and Plotkin, Low-Speed Aerodynamics, 2001 s metodou stukturální analýzy dle Píštěk et al., Pevnost a životnost letadel I, 1988 a Lebofsky,Numerically Generated Tangent Stiffness Matrices for Geometrically Non-Linear Struc- tures, 2013. Panelová metoda poskytuje přasná data pro výpočet zatížení křídla od vzdušných sil za předpokladu že lze dané proudění aproximovat po- mocí potenciálního proudění, Narozdíl metod založených na interakci s CFD metodami lze navrženou metodu používat i na bežném počítači.
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Overview of the dwvelopment of new reusable space vehicles
Rohánek, Jan ; Junas, Milan (referee) ; Daněk, Vladimír (advisor)
This thesis focuses on the development of reusable space vehicles. The introduction describes history of cosmonautics. Next chapter talks about history of Space Shuttles and then names and compares the most import projects of USA and USSR. Next topic of this thesis is about problematics of reusable rocket carriers. Last chapter names and describes today´s projects of new space shuttles. The conclusion consists of overall assessment and forecast of future reusable space vehicles development.
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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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Conceptual study of light two-seater surveillance aircraft
Kaňák, Ondřej ; Daněk, Vladimír (referee) ; Popela, Robert (advisor)
This master’s thesis deals with the conceptual design of light surveillance aircraft. It involves modifying of VUT 001 Marabu according to the new requirements, which has been mainly brought by new definition of typical flight. Also there is solved design and geometry surfaces of new aircraft. It contains design and computation of stand for electro-optical monitoring device. Last but not least are calculated important flight performances.
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