Research Interests:
Research Interests:
Analysis of the possibility of using an engine with a rotating piston as the propulsion of an electric generator in application to a motor glider propulsion The paper presents an analysis of the possibilities of application of a rotating... more
Analysis of the possibility of using an engine with a rotating piston as the propulsion of an electric generator in application to a motor glider propulsion The paper presents an analysis of the possibilities of application of a rotating piston engine (Wankel type) as a propulsion for an electric generator in the motor glider propulsion system. This generator would be a part of the propulsion system of a hybrid motor glider using the AOS 71 motor glider airframe. In the research, the rotational characteristics of the LCR 407ti engine were determined experimentally. Driving torque run, power and fuel consumption were determined as a function of engine speed. The obtained results are presented in diagrams. The conceptual diagram of the hybrid drive is presented. The current generator was selected and the effectiveness of the generator and the entire propulsion were assessed from the motor gliders performance point of view. On the basis of the conducted research, conclusions were drawn...
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Research Interests:
Comparative analysis of harmful compounds emission of classical and distributed propulsions applied on the AOS motor glider, taking into account the perspective of the development of hybrid propulsions. A novel path is indicated by... more
Comparative analysis of harmful compounds emission of classical and distributed propulsions applied on the AOS motor glider, taking into account the perspective of the development of hybrid propulsions. A novel path is indicated by so-called distributed aircraft propulsion. The advantages and disadvantages of this type of solutions are presented, as well as the conceptual design of the distributed propulsion for the AOS 71 motor glider. In the paper there were compared the emissions of harmful compounds generated by a hybrid power unit developed for the airframe of AOS 71 motor glider – traditional propulsion, so-called focused (one-propeller) and dispersed propulsion (multi-propelled). Functional diagrams of both types of propulsions solutions are presented. Construction and aerodynamic constraints of both propulsions are discussed and comparative analysis is made. In the traditional version of the propulsion (so-called focused propulsion). the propeller is driven by an Emrax 228 e...
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Research Interests:
This paper describes the fracture problem of the turbine casing of helicopter engine. Visual inspection of the defected component was incomplete because of the fact that the fracture was repaired by welding during technical inspection of... more
This paper describes the fracture problem of the turbine casing of helicopter engine. Visual inspection of the defected component was incomplete because of the fact that the fracture was repaired by welding during technical inspection of engine. In this work, authors try to ...
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The problems of turbofan engines development is briefly discussed in the beginning. Next the conception of turbofan engine with two combustors is presented, and an engine thermodynamic cycle is analysed. The proposed engine it is a... more
The problems of turbofan engines development is briefly discussed in the beginning. Next the conception of turbofan engine with two combustors is presented, and an engine thermodynamic cycle is analysed. The proposed engine it is a modification of the contemporary turbofan engine by addition of another combustor. First one is classical combustor located between high pressure compressor and turbine. Second one is located between high pressure turbine and low pressure turbine. This conception allows to lower the high pressure turbine inlet temperature. The second combustor increases energy of gasses inflow the low pressure turbine to the sufficient level for fan drive. The results of numerical analysis are used to show performance of the proposed engine and to present their advantages with compare to the classical turbofan engine construction. Then some other positive aspects of two combustors engine are discussed. It refers to possibilities of pollution emission reduction and overhau...
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Research Interests:
In the paper, the concept of a hybrid drive control for unmanned aerial vehicle was presented. A combustion engine was coupled with a brushless dc motor by an electromagnetic coupling. The signal processor TMS320F2812 was used to control... more
In the paper, the concept of a hybrid drive control for unmanned aerial vehicle was presented. A combustion engine was coupled with a brushless dc motor by an electromagnetic coupling. The signal processor TMS320F2812 was used to control the hybrid drive and control algorithms of motoring and generating operation of the BLDC and the combustion engine were realized. The hybrid drive was started and waveforms of chosen parameters of the hybrid drive were registered in different working states.
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Research Interests: Engineering and Nap
W pracy zawarto wyniki bada ń laboratoryjnych zaprojektowanego i wykonanego prze z autorów silnika BLDC przeznaczonego do hybrydowego nap ędu równoległego dla bezzałogowego aparatu latającego. W warunkach laboratoryjnych wyznaczono charak... more
W pracy zawarto wyniki bada ń laboratoryjnych zaprojektowanego i wykonanego prze z autorów silnika BLDC przeznaczonego do hybrydowego nap ędu równoległego dla bezzałogowego aparatu latającego. W warunkach laboratoryjnych wyznaczono charak te ystyki mechaniczne badanego silnika oraz jego sprawno ści przy różnych wartościach napi ęć zasilaj ących wynikaj ących z założeń projektowych. Wyznaczono równie ż charakterystyki regulacyjne silnika
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A hybrid drive of an unmanned aerial vehicle uses two mechanically coupled drives. In one of the drives, an electrical machine is used. Its role is not only limited to a motoring operation, e.g. during achieving the flight ceiling. The... more
A hybrid drive of an unmanned aerial vehicle uses two mechanically coupled drives. In one of the drives, an electrical machine is used. Its role is not only limited to a motoring operation, e.g. during achieving the flight ceiling. The electric machine changes its operation into generating after reaching the flight ceiling, this allows not only meeting current electrical energy demands but also battery recharging. This paper presents the results of laboratory tests of a BLDC machine in motoring and generating operation. Mechanical characteristics of the motor for different supply voltages and external characteristics for generator were determined. The possible energy conversion efficiencies for both motoring and generating operations were determined.
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The paper presents an analysis of influence of selected fault states on properties of brushless DC motor with permanent magnets. The subject of study was a BLDC motor designed by the authors for unmanned aerial vehicle hybrid drive. Four... more
The paper presents an analysis of influence of selected fault states on properties of brushless DC motor with permanent magnets. The subject of study was a BLDC motor designed by the authors for unmanned aerial vehicle hybrid drive. Four parallel branches per each phase were provided in the discussed 3-phase motor. After open-winding fault in single or few parallel branches, a further operation of the motor can be continued. Waveforms of currents, voltages and electromagnetic torque were determined in discussed fault states based on the developed mathematical and simulation models. Laboratory test results concerning an influence of open-windings faults in parallel branches on properties of BLDC motor were presented.
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Research Interests:
This paper presents results of a study concerning operating modes of brushless DC machine (BLDCM) used in the hybrid drive designed for unmanned aerial vehicle (UAV). A mathematical model of the machine and a simulation model of the whole... more
This paper presents results of a study concerning operating modes of brushless DC machine (BLDCM) used in the hybrid drive designed for unmanned aerial vehicle (UAV). A mathematical model of the machine and a simulation model of the whole drive system are proposed. Structure of the parallel hybrid drive system is discussed. Results of simulations are presented for three different operation modes provided for the machine in the UAV drive system, i.e. engine starting, motoring operation with regulated airscrew speed, and generating operation. Finally, preliminary results of laboratory tests are presented.
Research Interests: Engineering and Dc Motor
Purpose – The paper aims to present a way of engine model integration, an aircraft (multitask) and the mission into the single model that allows to study, from the level of selection of the engine cycle parameters, the feasibility of a... more
Purpose – The paper aims to present a way of engine model integration, an aircraft (multitask) and the mission into the single model that allows to study, from the level of selection of the engine cycle parameters, the feasibility of a specific mission with the assumed aerodynamic characteristics exemplified by a multitask airplane. Design/methodology/approach – There were introduced dimensionless geometric and energetic criteria, binding parameters of the engine and the airplane. The following models were built: of the turbofan engine and the aircraft movements with the application of these criteria, creating a dimensionless model allowing for measuring the impact of engine design parameters on the efficiency of the mission undertaken. Findings – The results were limited to the presentation of the impact of circuit parameters, such as engine TIT, OPR, BR on the defined criteria. The application of dimensionless criteria reduced the dimension of the task. Practical implications – Th...