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Performance and Emission of the Aircraft with Hybrid Propulsion During Take-Off Operation Cycle

Pawlak Małgorzata, Kuźniar Michał

Advances in Science and Technology. Research Journal

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2024

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Vol. 18, no 1

155--166

EN

The paper presents the energy consumption and emissions of pollutants in the exhausts during the take-off operation mission of a Short Take-Off and Landing (STOL) aircraft equipped with a traditional and hybrid propulsion system. This research is part of the contemporary trend of research aimed at reducing the impact of aviation on the natural environment. The analyzed propulsion system consists of turbine engines and electric motors cooperating with them. In this work, on the basis of data from flight tests, the energy requirement for the aircraft to perform the intended mission was determined. On this basis, fuel consumption and the corresponding pollutant emissions were determined for an aircraft with a traditional power unit. For comparison, an aircraft with a hybrid propulsion system with the same mass as an aircraft with a traditional propulsion system was used. Then, energy consumption, fuel consumption and emission of CO2, CO, NOx, VOC, PM10 and PM2.5 were obtained for both aircraft variants. The most important results of the conducted research include a reduction in CO2 emissions by 23% and NOx emissions by 46% in the case of the hybrid propulsion. This indicates potential benefits of using hybrid propulsion in aviation.

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A rotating piston engine with electric generator in serial hybrid propulsion system for use in light aircraft

Kalwara Maciej, Kuźniar Michał, Orkisz Marek

Combustion Engines

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2021

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R. 60, nr 4

42--45

EN

Analysis of the possibility of using a rotary engine based electric generator to propell a powered sailplane. The paper presents analysis of utilising Wankel type enine as a power input 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 wankel 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 electric generator was selected and its effectiveness, as well as the effectiveness of entire propulsion system was assessed from the motor glider's performance point of view. Basing on the research conducted, conclusions were drawn and there were indicated the objectives and directions of further research on hybrid propulsion with specific aerodynamic and mass limitations of the aircraft.

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3E - A new paradigm for the development of civil aviation

Orkisz Marek, Kuźniar Michał

Combustion Engines

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2020

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R. 59, nr 2

3--10

EN

Nowadays, in civil aviation, issues related to improving efficiency, reducing the costs of air operations as well as the negative impact of air transport on the environment are of increasing importance. These ideas allow the formulation of the paradigm relating to the development of air transport - ‘more Efficiently, more Economically, more Eco-friendly - 3E’. The article presents in a cross-sectional and synthetic way research conducted by leading scientific centres around the world as well as prototype aviation constructions designed by companies from the aviation industry. Benefits and disadvantages of future propulsions, such as purely electric, hybrid and distributed propulsions, were presented. Conclusions were formulated regarding further possible directions of civil aviation development, taking into account the improvement of its efficiency as well as economic and ecological indicators.

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Determination of CO2 emissions for selected flight parameters of a business jet aircraft

Pawlak Małgorzata, Kuźniar Michał

Journal of KONES

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2019

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Vol. 26, No. 3

155--163

EN

In the last two decades, there has been observed a noticeable increase in the popularity and availability of air transport services, including regional ones. This intensive development of transport is accompanied by an increase in the adverse impact to the environment, increases noise level, and exhausts emissions, despite the modification and modernization of engines. Determining the emission for regional flights takes into account the specificity of the aircrafts design, such as the size of the aircraft and the performance of the engines. In this article, an attempt was made to determine the CO2 emissions of a business jet flying from Gdansk to Rzeszow. The methodology of the research (the method of calculating emissions based on fuel consumption) and the performance characteristics of the aircraft engines have been described. In the first part of the article, the speed-altitude characteristics of the DGEN-380 engine for different cruise parameters were determined using the virtual engine test bench WESTT CS/B. These characteristics have enabled the engine to match the flight characteristics (altitude, speed). For specific flight parameters, the thrust and fuel consumption were determined. On this basis, for the adopted trajectory and flight time of an aircraft equipped with two DGEN-380 engines, total fuel consumption and CO2 emission factors and values in CRUISE phase was determined with regard to the wind speed and direction. The obtained results were illustrated graphically and discussed.

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Analysis of the impact of changes in flight speed and altitude on emission indexes of pollutants in jet engine exhausts

Pawlak Małgorzata, Kuźniar Michał

Journal of KONES

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2019

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Vol. 26, No. 2

107--113

EN

In currently implemented international aviation strategies and programs, including those realised under the European Union policy, such as Clean Sky, SES, SESAR and, CORSIA, the environmental aspect is particularly prominent – reducing the emission of all gaseous pollutants, and from 2020 also particulate matter. Therefore, it is important to know how the change in flight parameters (altitude, speed) affects the emission of pollutants in jet engine exhausts. Such information will enable to adjust the flight altitude of the aircraft when ecological aspect is taken into consideration. In addition to the operating condition (altitude, flight speed, range of power or thrust), the amount and type of pollutants emitted depends on the type of aircraft, its aerodynamic characteristics, engine type and as well as on the type of fuel used. The impact of changes in aircraft flight parameters (speed and altitude) on the performance of a bypass jet engine and the emission of pollutants in its exhausts is analysed in the paper. For this purpose, the speed-altitude characteristics of such an engine were determined. Next, the emission indexes (EI) for the LTO phase taken from the ICAO database were used to determine the emission indexes corresponding to given parameters of both the engine operation and the aircraft flight. For selected speeds and cruising altitudes, the value of thrust required for the flight of the aircraft was determined and to this value, the engine operation range was assigned as well the corresponding pollutant emission indexes. This allowed to calculate the mass of pollutants emitted per unit of time for given flight parameters. The results obtained are presented in the graphs and discussed.

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Analysis of the application of distributed propulsion to the AOS H2 motor glider

Kuźniar Michał, Orkisz Marek

Journal of KONES

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2019

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Vol. 26, No. 2

85--92

EN

The paper describes the selection of a distributed propulsion for the AOS H2 motor glider (selection of engines, their number, and propellers) and determination of its performance. This analysis is related to the research conducted on environment friendly and hybrid propulsions in various research centres. The main aim of the analyses conducted is to increase the performance of vehicles powered by electric motors. The batteries have a low density of energy, i.e. the ratio of mass to cumulated energy. Instead of a battery set, it is possible to apply a hybrid- electric system, where the combustion engine works as a generator or an electric-hydrogen generator, where the hydrogen cell supports a small set of batteries. One of such flying vehicles, fitting in this trend, is the AOS H2 motor glider built at the Rzeszow University of Technology in cooperation with other universities. It is a hybrid aircraft, equipped with a hydrogen cell, which together with a set of batteries is a source of electricity for the Emrax 268 electric motor. To increase the vehicle's performance (the range and flight duration), it is possible to use a distributed propulsion. This type of propulsion consists in placing many electric motors along the wingspan of the aircraft. Appropriate design of such a system (propeller diameters, engine power, number of engines) can improve the aerodynamic and performance parameters of the airframe. An analysis of the performance for the selected flight trajectory for this propulsion variant was conducted and compared to the performance of the AOS H2 motor glider equipped with traditional propulsion. The consumption of hydrogen was also determined for both systems. The results obtained were presented in the diagrams and discussed in the conclusions.

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Comparative analysis of pollutants emission by classical and distributed propulsions applied on the AOS motor glider

Orkisz Marek, Wygonik Piotr, Kuźniar Michał, Kalwara Maciej

Combustion Engines

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2019

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R. 58, nr 4

102--106

EN

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 electric engine with effective parameters: N = 55 kW, M = 120 Nm. The power source is a battery set with a capacity of 16 Ah and a range extender powered by a LCR 407ti rotating piston engine with maximum power of 28 kW. In the variant of the distributed propulsion. Ten electric engines of AXI 8120 type were used to drive small propellers arranged along the wingspan. The power source in this variant is analogous to the variant with the Emrax electric engine. For the adopted variant of the flight mission of the motor glider. a flight trajectory model was developed, which was used to determine the load of the power unit. In laboratory conditions. emission tests of both propulsions were conducted. The results are summarized in charts and discussed in the conclusions.

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Comparative analysis of combustion engine and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere

Orkisz Marek, Wygonik Piotr, Kuźniar Michał, Kalwara Maciej

Combustion Engines

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2019

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R. 58, nr 3

213--217

EN

Comparative analysis of combustion and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere. For the propulsion of the AOS 71 motor glider, two types of propulsion were planned as development versions. The first analysed propulsion is based on a combustion engine, but of the Wankel type (LCR 814 engine with the power of 55 kW). The second designed propulsion is an hybrid based on a LCR 407 combustion engine with a power of 28 kW, which is connected in series with an electric generator propelling the engine (Emrax 228 engine), total power of the propulsion is 55 kW. The comparison of emissions of harmful compounds emitted to the atmosphere generated by the combustion and hybrid power unit intended for assembly in the AOS 71 motor glider, assuming various loads and methods of hybrid propulsion control, was made. The tests were conducted in laboratory conditions. Several different programs were designed to simulate different energy management methods in a hybrid system, depending on the predicted mission and load of the motor glider. On the basis of laboratory tests, exhaust emission was determined from both propulsions as a function of rotational speed and load. Then, based on the assumed flight trajectory and collected test data, the emission for both propulsions variants was determined. The values of emission parameters were compared and the results were presented in diagrams and discussed in the conclusions.

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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

Orkisz Marek, Wygonik Piotr, Kuźniar Michał, Kalwara Maciej

Combustion Engines

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2019

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R. 58, nr 3

264--268

EN

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 glider's performance point of view. On the basis of the conducted research, conclusions were drawn and there were indicated the objectives and directions of further research on hybrid propulsion with specific aerodynamic and mass limitations of the aircraft.

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Energetyczna analiza porównawcza zespołów napędowych w zastosowaniu do lekkiego statku powietrznego

Kuźniar Michał

Autobusy : technika, eksploatacja, systemy transportowe

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2019

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R. 20, nr 1-2

88--92

PL

W nawiązaniu do badań nad ekologicznymi źródłami napędu dla samolotów przeprowadzono energetyczną analizę porównawczą dla zespołów napędowych korzystających z rożnych źródeł zasilania. Do analizy wykorzystano płatowiec motoszybowca AOS-71. Obliczenia przeprowadzono dla różnych zespołów napędowych: spalinowego, elektrycznego, hybrydowego spalinowego oraz hybrydowego z ogniwem wodorowym. Podstawowym założeniem była taka sama masa startowa samolotów wynosząca 660 kg. Dokonano wyznaczenia energii zgromadzonej na pokładzie, a następnie długotrwałości i zasięgu lotu dla każdego rodzaju napędu. Analizę przeprowadzono dla dwóch trajektorii lotu. Wyniki przedstawiono na wykresach i omówiono we wnioskach.

EN

In reference to the research conducted on environmentally friendly sources of propulsion for aircrafts, there was carried out an energetic comparative analysis for power units using various power sources. For this analysis, the AOS-71 glider airframe was used. The calculations were done for different variants: a combustion engine, an electrical engine, a hybrid combustion engine and a hybrid engine with a hydrogen cell. The research was based on the assumption of the same aircraft take-off weight of 660 kg. The energy accumulated on board was determined, and then the duration and range for each type of propulsion for two flight trajectories. The results were presented in diagrams and discussed in the conclusions.