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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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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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Urban Air Mobility VTOL personal vehicle design
Polčák, Marek ; Zikmund, Pavel (referee) ; Popela, Robert (advisor)
Diplomová práce se věnuje koncepčnímu návrhu pilotovatelného prostředku pro UAM. V průběhu návrhu byla vyvíjena snaha zachovat původní myšlenku létajícího motocyklu, což vedlo ke zvolení konfigurace multikoptéry. Na základě statistického průzkumu stávajících konceptů a vstupních požadavků bylo možné odhadnout vstupy pro první iteraci návrhu propulzního systému, který sestává z výběru vrtulí, motorů, kontrolérů a předběžného návrhu baterie. Nakonec byla zvolena konfigurace koaxiální kvadrokoptéry. Klíčovou částí koncepčního návrhu je samotná konstrukce, která je navržena jako prutový duralový rám s krytovými prvky z uhlíkového kompozitu. Motory s vrtulemi jsou uchyceny v nosných prstencích, které přináší aerodynamické a konstrukční výhody. Tyto prstence jsou také navrženy z uhlíkového kompozitu, jejichž vrstvová skladba byla navržena tak, aby dokázala bezpečně přenést dané zatížení. Pevnost navržené prutové konstrukce a kompozitních prstenců byla poté zkontrolována pomocí výpočtu metodou konečných prvků. Pevnostní analýza prutové konstrukce pomohla snížit celkovou hmotnost úpravou průřezu použitých kruhových profilů. MKP analýza kompozitního prstence byla provedena pro dynamické zatížení při přechodu do dopředného letu a byla klíčovým nástrojem pro definici vhodné skladby laminátu kompozitních prstenců tak, aby se docílilo kompromisu mezi hmotností a dostatečnou pevností. Největší důraz musel být kladen na napojení prstenců na centrální prutovou konstrukci, jelikož je využito mechanických spojů, které vytváří silné koncentrátory napětí. V těchto místech bylo zapotřebí silně zesílit laminát a využít zalaminovaný duralový plát, jenž pomohl zvýšit pevnost v těchto místech. Kromě kompozitních dílů prstenec využívá duralové součásti, které byly také zkontrolovány výpočtem. VTOL prostředky mohou silně využívat výhod přízemního efektu. K výpočtu letových výkonů ve visu s vlivem přízemního efektu, byla provedena CFD analýza. Vliv přízemního efektu byl zkoumán ve visu ve třech různých vzdálenostech od země. Vliv přízemního efektu na letové výkony byl vyhodnocen na základě výdrže baterie ve visu, pro který je třeba generovat menší tah a spotřebovávat méně elektrické energie, než by bylo třeba ve větší vzdálenosti od země. Druhá část aerodynamických výpočtů se věnovala určení součinitele odporu v dopředném letu, jenž byl zkoumán ve třech různých naklopeních. Výsledky byly dále využity pro výpočet závislosti rychlosti letu na úhlu naklopení, výdrže baterie a dolet. V závěrečné části práce byly navrženy dva možné způsoby provedení řízení a bylo shrnuto přístrojového vybavení, které by umožnilo bezpečný let.
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Haptic feedback device design for aircraft control
Dubnický, Lukáš ; Jebáček, Ivo (referee) ; Zikmund, Pavel (advisor)
This master thesis is focused on design of control stick grip and rudder pedals extension. These components are equipped with active elements, which provide pilot with haptic feedback. The purpose of the introduced design is to allow prototype to be built into the aeroplane so that the proposed concept of haptic feedback can be tested onboard. It shall verify used technical solutions as well to allow for their application on following development stages that aim at certification of the proposed haptic feedback system to be used in general aviation aeroplanes. The designed components are the successors of prototypes used for experiments carried on flight simulator. The design process follows the requirements of legislation and outcomes of the previous experiments. This thesis follows the design process from setting of the design requirements to mechanical test of 3D printed prototypes.
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