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Flight control system design for modern sailplane
Kocour, Petr ; Šplíchal, Jan (referee) ; Dubnický, Lukáš (advisor)
The thesis focuses on flight control mechanisms used in sailplanes or alternatively ultralight airplanes. The research done shows basic demands put on the flight control mechanisms and the different solutions that can be used to fulfill these demands. The research summary then compares the alternative solutions to each other. In the following chapter, the wing in subject is introduced, including its main parameters. Following is a description of the chosen variants for the flight control mechanism initial design, with explanations of why those variants were chosen. The result is a flight control mechanism initial design, which incorporates the selected properties, including for example automatic connection of separate mechanisms, differentiation of aileron deflection, different ratios of aileron to flap deflection for the inner and outer flaperon segments or placement of the summary mechanism into the wing itself. To check the suitability of the initial design, a stress calculation was carried out on what was approximated to be the part of the mechanism subjected to the most stress. The results of the FEM calculation suggested eligibility of the mechanism, showing the Von-Mises stress of 61 MPa, well below the yield strength of common aluminum alloys.
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Light Aircraft Crashworthiness
Střecha, Daniel ; Šplíchal, Jan (referee) ; Löffelmann, František (advisor)
Passive safety in general aviation is still an area with significant shortcomings compared to the automotive industry. Whether it’s seat belts, airbags, or better materials that absorb impact energy, the automotive industry is years ahead. This bachelor thesis serves as a comprehensive overview of passive safety in light aircraft. It presents the main factors affecting human body tolerance and the criteria used in aviation construction regulations. One of the main objectives of this work was to provide an overview of safety features that can be implemented in light aircraft even after the aircraft has been put into operation. Selected features include seat belts, airbags, fire protection systems, ballistic parachute, and emergency locator transmitter (ELT). Each of these elements has different weights and costs. Among the more expensive and heavier systems is the ballistic parachute, which offers the significant advantage of safe landing in case of failure of the main control components of the aircraft but is offset by high acquisition and maintenance costs. The result of this work is also a questionnaire distributed among several pilots and operators of light aircraft. The evaluation showed that the favorite passive safety features among pilots include the ELT system, four-point seat belts, and ballistic parachute. Furthermore, the survey revealed that when choosing an aircraft, pilots would prioritize flight performance and characteristics over passive safety. In the future, it is essential to focus on raising awareness of passive safety during pilot training.
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Sandwich Insert Design of the Formula Student Monocoque
Velfl, Tomáš ; Šplíchal, Jan (referee) ; Löffelmann, František (advisor)
The bachelor thesis is devoted to the insert joints and wheel suspension attachments on the racing frame of a Formula Student vehicle. First, research was done to obtain the necessary knowledge on the subject. Then the external loads stressing the joints were experimentally and computationally determined. Before starting the actual design of the attachments, the effect of introducing local loads into the sandwich structure of the monocoque was investigated, firstly on small calibration samples. The first phase of testing was to verify the failure mechanisms, the interaction between the different components of the composite sandwich and to test different attachment designs using different materials. Based on the data obtained, the material libraries were refined, and computational models were developed and extended by parametrization. Thus, in the next step, the final designs of the individual suspension points meeting the predetermined objectives were iteratively created. During validation tests, the functionality of the design and sufficient oversizing were demonstrated. Technologies such as CT scanning were also used. The results were evaluated to determine further testing options and further improvements to the current solution.
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Utilization of natural resources for a garden greenhouse
Šplíchal, Jan ; Babička Fialová, Dominika (referee) ; Jegla, Zdeněk (advisor)
The thesis performs the analysis of the potential of using natural resources, specifically solar radiation and rainwater, for garden greenhouses of various sizes, using self-created balance calculation tools and calculations made by them using available meteorological data. At the same time, the thesis provides a comprehensive overview of the technological possibilities of photovoltaic and irrigation systems in the context of garden greenhouses. The results of the calculations show that appropriately designed technological solutions can effectively ensure sufficient electricity and water for the autonomous function of the system. For smaller greenhouses, a simple photovoltaic system with one panel of about 0.5 m2 and a battery with a capacity of 300 Wh is sufficient for normal seasonal operation. For medium-sized and larger greenhouses, it is necessary to consider the optimal number of panels and batteries with regard to operational needs and the length of the season, but the number of panels and batteries is also acceptable in this case. For the irrigation system, it is important to consider the capacity of the barrel, which should be proportionate to the way the water is used. If the primary use of drip irrigation is being considered, then the performed analyzes show that a barrel capacity of 100 liters should be sufficient even for the needs of larger greenhouses.
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Buckling analysis of the load-bearing system
Majer, Tomáš ; Löffelmann, František (referee) ; Šplíchal, Jan (advisor)
The research part of the work summarizes the knowledge in the field of calculation of buckling stability and methods of heat transfer. The next part deals with the calculation of the buckling stability of two types of samples using an analytical approach, finite element method, and verified using experimental measurements. Finally, the work deals with CFD calculation for determining the temperature field on the examined samples, which is used to calculate the buckling stability with temperature influence.
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Comparison of FEM models using 1D and 2D elements used to flutter analysis
Zubaľ, Filip ; Navrátil, Jan (referee) ; Šplíchal, Jan (advisor)
The diploma thesis deals with flutter, which is one of the most dangerous dynamic aeroelastic phenomena in aviation. The work includes the creation process and subsequent flutter analysis of two FEM models of the wing of the BUT 051 Ray experimental aircraft. The goal of the work is to compare individual FEM models and determine the critical flutter speed, to evaluate the effectiveness and usability of FEM models created by 1D or 2D elements.
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New Aluminium Alloys in Aircraft Structures
Przeczek, Jan ; Šplíchal, Jan (referee) ; Klement, Josef (advisor)
This bachelor work deals with newly developed wrought aluminium alloys, designed for application in aerospace industry. The task of that work is to compare recent aircraft aluminium alloys with conventional alloys and indicate direction of progress in this field. The comparison is particularly focused on improvement of mechanical and/or technological properties of these alloys.
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Increasing the life of blanking punch by coating
Šplíchal, Jan ; Lidmila, Zdeněk (referee) ; Podaný, Kamil (advisor)
This Bachelor thesis presents possible methods for increasing the lifespan of cutting tools made of steel 19 436 designed for cutting stator and rotor plates made of silicon steel. These sheets are characterized by high hardness, which adversely affects the edges of the scissors. Experimental hardness measurement on delivered samples has verified the actual heat treatment on the surface and inside the scraper. The measured value 62 HRC corresponds to the input requirements. Based on the literature study, a combination of chemical – heat treatment and coating was chosen as the most appropriate method. In order to preserve the microstructure of the punch produced after the heat treatment, it was necessary to apply the coating by physical vapor deposition, which is characterized by low deposition temperatures. The FeinAl coating will be applied by cathodic arc deposition and is primarily designed to protect tools and cutting tools.
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Simulation of ultrasonic wave in the composite aircraft structures
Cimrhanzl, Jan ; Koštial, Rostislav (referee) ; Šplíchal, Jan (advisor)
V této diplomové práci jsou popsané SHM metody používané v letectví a dále jsou udělány MKP simulace šíření ultrazvoukových vln v celokompozitním tenkostěnném materiálu používaném u leteckých konstrukcí. Pro simulaci byla zvolena SHM metoda nazývaná pitch-catch. Simulace byla provedena na dvou různých kompozitových materiálech a každý z nich byl testován třemí různými konfiguracemi s trhlinou a jednou konfigurací bez trhliny. Jako prepocessor byl použit MSC.Patran a jako post processory byli použity MSC.Nastran a MSC.Dytran, jejichž výsledky byli na závěr porovnány. Simulace prokázali, že rychlost šíření a amplituda vln šířících se v simulovaném panelu je trhlinami ovlivněna. Při konfiguracích s trhlinami rychlost šíření i amplituda vln byli menší, než v případě bez trhliny. Jako vhodnější post processor při MKP simulacích se ukázal MSC.Nastran, jehož výsledky byli přesnější a zárověň bylo i snažší správně odečítat hodnoty dat z grafů pro podrobnější pozorování šíření vln.
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Construction of ultralight aircraft control
Marek, Ondřej ; Šplíchal, Jan (referee) ; Juračka, Jaroslav (advisor)
This bachelor thesis deals with control of ultralight glider D-14. Based on the research of applied construction solutions of ultralight airplanes I designed my own solution of the specific elements and construction nodes. Also, in accordance with the UL-2 directive load of main control systems are determined. 3D model of the glider fuselage with the elements of the particular assemblies is attached.
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