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This thesis deals with the design of electrical control for a constant speed propeller. The objective of this paper is to demonstrate the propeller governor design process on a case example of a DMP-3 propeller paired with a Rotax 912 ULS, using knowledge of flight mechanics, electrical engineering and automation. The scope of this thesis addresses the problems of propeller pitch control using an electrically driven linear actuator. In conclusion, this paper compares the benefits of the DMP-3 constant speed propeller, considering its use in existing airplanes within the UL-2 and CS-LSA category. Furthermore, it evaluates the capabilities of the proposed electronic governor, and outlines possibility of further development in this field.

This master‘s thesis is focused on the design of four-seat metal aircraft with low take-off weight in accordance with CS-23. Main dimensions of aircraft are designed, weight analysis, aerodynamic characteristics and flight performance are calculated in this thesis. In conclusion, the estimated costs of development and production are determined.

Determining the characteristics of piston engines with a propeller is a complex task. Accurate calculations are based on engine and propeller characteristics from the manufacturers, which are, however, quite demanding. It is also possible to use simplified models that can predict the achievable values of propeller efficiency and fuel consumption. They are based on a simple propeller efficiency and maximum power. However, these models are often very inaccurate, which is a significant disadvantage. Therefore, it is possible to use the universal characteristics of propeller propulsion units, which offers a more accurate calculation of power and fuel consumption using a relatively simple model. The diploma thesis deals with a summary description of all characteristics of reciprocating internal combustion engines and propellers. A mathematical model was created here, which works according to a certain algorithm based on the joint work of the engine and the propeller. This model can predict the required power and fuel consumption in different flight modes much more accurately. The results were applied to the performance of ultralight aircraft, especially to the range, which was significantly increased.

Práce je zaměřena na nalezení optimálního a nového motoru pro PS-28 Sport Cruiser, pro větší výkon a tah. Rotax 912 ULS je v současné době jediným motorem, který klient této práce (Czech Aircraft Works, dále jen CZAW) instaluje do letadel Sport Cruiser. Tato čtyřválcová pohonná jednotka má maximální vzletový výkon 100 hp. Pro náročnější zákazníky bude nabídka rozšířena o Lycoming O-235-L2C, což je také čtyřválcový motor s maximálním vzletovým výkonem 118 koní. Což znamená, že společnost bude mít větší možnost a klient bude mnohem spokojenější.

Práce je zaměřena na nalezení optimálního a nového motoru pro PS-28 Sport Cruiser, pro větší výkon a tah. Rotax 912 ULS je v současné době jediným motorem, který klient této práce (Czech Aircraft Works, dále jen CZAW) instaluje do letadel Sport Cruiser. Tato čtyřválcová pohonná jednotka má maximální vzletový výkon 100 hp. Pro náročnější zákazníky bude nabídka rozšířena o Lycoming O-235-L2C, což je také čtyřválcový motor s maximálním vzletovým výkonem 118 koní. Což znamená, že společnost bude mít větší možnost a klient bude mnohem spokojenější.

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.