|
|
Airplane Cooling System Optimization
Lajza, Ondřej ; Fiľakovský, Karol (referee) ; Horák, Aleš (referee) ; Píštěk, Antonín (advisor)
Dissertation thesis is focused on the aircraft cooling system optimization. The knowledge of the pressure loss is necessity for design of an optimal system. In the beginning of the thesis, the different designs of piston engine cooling systems are described for both aircrafts and automobiles. Other sections outline the determination of the coolers characteristics and describe the different test sections applicable for the characteristics measurement. The test section built at the Institute of the aerospace engineering is described as well. Practical part of the thesis describes the calibration of the test section. The measurements of the specific coolers were compared with the CFD simulation of two models - the simplified cooler model and cooler element model. Additionally, the measurements were compared with results obtained at specialized coolers testing facility.
|
|
|
Design of VUT 081 Kondor aeroplane in double-fuselage variant
Suk, Filip ; Vaněk, František (referee) ; Píštěk, Antonín (advisor)
The aim of the diploma thesis is to determine loads of the empennages and the engine mount for the engine ROTAX 912iS of the VUT 081 Kondor aircraft. Further the thesis deals with a design of a stabilizer and of beams of empennage with fins. I also present a design of mountings for beams to the center wing box. The design is presented with regard to CS-VLA regulations and the ELSA regulation for modular construction.
|
|
| |
|
|
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.
|
|
| |
|
|
Aircraft design for the installation of a hybrid powerplant
Kapoun, Tomáš ; Bencalík, Karol (referee) ; Píštěk, Antonín (advisor)
The master‘s thesis "Aircraft design for the installation of a hybrid powerplant" is focused on the design of the airplane suitable for hybrid powerplant. At the same time it is also deal with the most suitable location of the components necessary for this powerplant. These components are: a combustion engine, electric motor, gearbox and bed engine. Part of the master thesis is application-mount designed components: location and number of containers with batteries, a proposal for a new engine bed suitable for a hybrid powerplant. In the sub - section of the thesis is made a simple calculation of the economic return on investment from the perspective of the end-user aircraft with a hybrid powerplant.
|
|
|
The Landing Gear design for RAPID 600 aircraft
Chren, Tibor ; Hlinka, Jiří (referee) ; Píštěk, Antonín (advisor)
This diploma thesis deals with design of retractable landing gear for Rapid 600 aircraft. The main purpose of this thesis is to analyze different retraction options for front and main landing gear and resulting selection of suitable variants. The thesis is consequently concerned with design of selected options including proposal of automatic landing gear control system and specifying the features and characteristics of this system. In the thesis there is also included the analysis of critical flight conditions which could be detected by this system.
|
|
|
Installation of the LYCOMING power unit into the Bristel UL aircraft
Kročil, Petr ; Juračka, Jaroslav (referee) ; Píštěk, Antonín (advisor)
This diploma thesis focuses on Lycoming drive unit mounting used in two-seater plane of VLA category (the very light aircraft). In the beginning characteristics of currently produced Bristell aircrafts are described. Following chapters aim at research selection of new drive unit mounting based on multi-criteria decision analysis. For selected unit, the weight, center of mass and flight performance are calculated. Additionally, the construction of engine mount is proposed. According to CS-VLA and CS-23 stress level of mounting is defined followed by strength verification. Later in this thesis, a suitable engine cover for engine and cockpit cooling is proposed. A complete fuel system is described in following chapter. Last chapter deals with financial costs of re-engining as well as aircraft operational costs.
|
|
| |
|
| |
guest ::
