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Legal Context of Nightime Road Accidents with Pedestrians
Daněk, Vladimír ; Bradáč, Albert (referee) ; Semela, Marek (advisor)
The thesis „Legal Context of Night-time Road Accidents with Pedestrian „deals with the interpretation of legal decisions on traffic accidents caused by the vehicle during the night and where the other participant was a pedestrian. The main aim of this thesis is to find the established limits for the assessing of blame in comparable accident situations in cases of traffic accidents of the vehicle and the pedestrian at the reduced visibility with emphasis on the assessing in relation to the circumstances of the cases from the technical and legal point of view and in relation to the health consequences. Legal interpretations of the law are defined within the theoretical part of the thesis with emphasis on the ones which appear repeatedly in the judicial decisions. Approximately 1530 judicial decisions were studied and analysed in the analytical part, of which 56 were selected, that corresponds to the requirements of this thesis. There are also 5 expert evidences provided by the Institute of Forensic Engineering of Brno University of Technology. In the above mentioned cases there were defined the limits for the assessing of accidents based on which the judicial decision was predicted in context with the defined established limits for the judicial decisions at the top of the court hierarchy.
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Stability and controllability of the Z-143 airplane with a more powerful engine
Kochtík, Martin ; Matějů, Jiří (referee) ; Daněk, Vladimír (advisor)
The thesis deals with the calculation and evaluation of the flight characteristics of the aeroplane Z 143 with the power unit Lycoming AEIO-580-B1A. The first part of the text focuses on a general description of the aircraft, its geometric characteristics and calculation of mass and aerodynamic characteristics. In terms of flight performance there are compared the values for contemporary model and developmental aircraft with a more powerful engine. Another part of the work deals with the calculation of properties in terms of stability and manageability. In this section regards the determination of the results of the flight characteristics and their assessment of whether they comply. In the end I discuss the individual results and comment the possible recommendations on correction or improvement of these properties.
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Overview of means for reducing induced drag
Mazánek, Adam ; Švec, Michal (referee) ; Daněk, Vladimír (advisor)
This bachelor thesis deals with the creation of overview of means for reducing induced drag on the wing of an airplane. It describes production of the induced drag and how it changes during a flight. The bachelor thesis also deals with geometrical modifications of the wing. The most extensive part is devoted to structural modifications of wing tips with special aiming on winglets.
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Overview of the development of small and medium lauchers
Dítě, Radovan ; Petrásek, Miloslav (referee) ; Daněk, Vladimír (advisor)
This bachelor's thesis describes the development of small and medium vehicle launchers. The dissertation is divided into four main parts. The first part deals with basic principles of rocketry and types of rocket propulsion. The second chapter describes historical develop-ment of rocketry. The third part describes the development of small and medium vehicle launchers. And the last part is dedicated to the description of current states of small vehicle launchers.
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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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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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Parachute Emergency Systems for Very Light Sport Planes
Šorf, Oldřich ; Salga, Jaroslav (referee) ; Daněk, Vladimír (referee) ; Třetina, Karel (advisor)
This PhD thesis describes parachute rescue systems for small planes and focuses on their functionality in the border areas of the flight envelope, especially at very low altitudes and low airspeeds of flight (fall). For extending the functionality of the rescue system in extreme areas of usability envelope, was founded an innovative dividable parachute slider, which works normally at high speed, but at the low airspeeds does not limit the opening time of the canopy. Structural design of this slider is the subject of a new patent application “Parachute opening speed regulation device”, filed with Industrial property Office in Prague on August 14, 2014 under number 2014-543 PV. The PhD thesis further contains computational principle of circular parachute opening and the structural design. For verification of the dividable slider functionality, a parachute model has been constructed and subjected to a series of drop tests. The main benefit of the PhD thesis is extending the usability of rescue system into its statistically most frequent use, i.e. into low altitudes and low airspeeds of flight (fall).
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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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Measurement of Micro-Accelerations on Board of the Russian Spacecraft „Universat -2“
Fedosov, Viktor ; Kureš, Miroslav (referee) ; Bezděk, Aleš (referee) ; Daněk, Vladimír (advisor)
The Thesis of the dissertation work present results of the accelerometer test operation on board of the Russian small spacecraft Universat – 2. This technical experiment was performed in the frame of the project TEASER (Technological Experiment And Space Environmental Resistance) financed by Ministry of Industry and Trade of the Czech Republic. The principal aim of the project was development and application of end-to-end tests procedures for MAC04TS. Generally, End-to-end Testing is intended for verification of the new product comprehensive operational sequence. In the context of the accelerometer this process includes following aspects: On-Ground Qualification of the instrument flight model and its integration with space platform, operation in orbit to verify the device functionality and performances. The MAC04TS is the new modification of the triaxial electrostatic high sensitive microaccelerometer MAC (or MACEK) designed for measurement of non-gravitational accelerations acting to orbiting spacecraft. Mentioned non-conservative perturbations are primary constraint for theoretical predictions of the spacecrafts orbit evolution. Problem of the precise orbit determination is important not only for ballistic mission analysis and support but at planning and realization of the science researches in Geophysics, Geodesy or in Space Physics branches… Presented text to examination is devoted to partial task of the MAC04TS end-to-end testing, especially, measurement and analysis of the micro-gravitational accelerations in the instrument position on board of the spacecraft. Solution of the problem is based on two methods. The first method was based on the calculation of the accelerations by telemetry information about satellite attitude motion. The second method consisted in direct measuring the accelerations by the triaxial low frequency accelerometer MAC04TS and subsequent smoothing measurement data. Comparison of the acceleration values, obtained by different ways, was carried out as a result of constructing the approximation of the measured acceleration values by their calculated values. The approximation was constructed by the least squares method. Both methods gave similar results. The received estimations of the accelerometer measurements can be used for the analysis of the accelerometer verification.
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