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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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Flight Simulator of General Aviation Aircraft
Mamula, Marko ; Koštial, Rostislav (referee) ; Matějů, Jiří (advisor)
This bachelor‘s thesis maps the major and mostly used commercial flight simulator softwares on the market, and points out the main differences in developing the aircraft in each simulator. It focuses on the flight simulator X-Plane and describes how it works with the flight model. The main goal of this thesis is developing a virtual model of an experimental aircraft VUT-061 Turbo and comparing its flight data with the data measured on the actual aircraft. Furthermore it suggests the adequate hardware needed for completing the physical simulator.
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Optimized design of turbine engine intake
Kubo, Michal ; Matějů, Jiří (referee) ; Popela, Robert (advisor)
This master thesis deals with design of a subsonic intake which is used to supply small jet engine integrate into the fuselage of agile small unmanned aerial vehicle (UAV). Some kinds of these intakes are listed in order to inspire and introduce future designers into this part of jet plane design. This thesis contains a small amount of theory about compressible flow, and necessary knowledge which are important to know before the very first attempt to design an intake. Two models were designed in order to prove that the theory listed in this thesis is useful and can be used as a guide in design process of subsonic intakes. Both designs have the same layout. S-duct design with one intake placed on the belly of fuselage was chosen. After CFD analysis of first model it was found that there are huge area with separated flow and vortex. Separated flow leads to big total pressure loss and pressure distortion. While designing the second model the emphasis was to avoid this vortex and improve flow conditions. This optimization was success and the second design have smaller pressure loss in compare to the first design. The difference is more than 50% at fly speed M=0,8.
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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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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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Alternative ways to take off and land for fixed-wing aircrafts
Cäsar, Tomáš ; Matějů, Jiří (referee) ; Zikmund, Pavel (advisor)
Target of this thesis was to propose and evaluate workability in matter of basic physical principles for shortening lengths of take-off and landing distances especially for small, single-seated aircrafts. These variants were proposed in order to be used at building roofs for transport of employees to work and back. Every variant is presented with loads, which would affect aircraft and pilot and also estimated runway length for comparison with classic landing. Calculations were made for two versions of aircrafts, one for present, achievable with current technologies and second futuristic, which takes into account expected development in aviation.
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Design of laboratory stand for temperature measurement
Matějů, Jiří ; Horský, Jaroslav (referee) ; Raudenský, Miroslav (advisor)
This Bachelor’s thesis solves design of a laboratory stand for temperature measurements. The stand is able to accelerate a steel sample of maximal weight 20 kg from the height of 7m to the speed of maximum 10 m/s. During a duty cycle of the stand the sample is accelerated on the length of 4 m, the constant speed is kept on the length of 2 m, on the length of 1 m the sample is stopped and then it’s lifted to a position for accelerating. During the constant speed the sample is cooled by water nozzles and there is measured temperature curve in the sample. The acceleration and constant speed is regulated by asynchronous servo motor with servo-driver. The stopping of sample is done by external mechanical braking system. The thesis is focused on selection of design solution, basic dynamic calculation and selection of individual components of stand.
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