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Tytuł:
Models of the reference departure and arrival ifr procedures for the purpose of research in RPAS integration in controlled airspace
Autorzy:
Lichoń, Daniel
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/243095.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
RPAS integration
SID
STAR
unmanned aviation
controlled airspace
controlled airports
Opis:
The air operations in controlled airspace performed according to Instrument Flight Rules (IFR) are composed of three main flight phases, i.e. departure, cruise, arrival. Controlled airspace is divided into the terminal area and en-route airspace. The terminal area encloses the departure and arrival phases while the en-route airspace encloses the cruise phase. The IFR procedures are designed for manned aviation to ensure the safety of air operations. Development of the aviation concerns among others the increase in the number of unmanned aviation operations. Currently, on the European level, there is an on-going, long-term program of integration of the unmanned aviation in the uniform (non-segregated) airspace. This work concerns the research in the integration of the Remotely Piloted Aircraft Systems (RPAS) in the IFR procedures of the controlled airports. The objective was to build the reference models of Standard Instrument Departure and Arrival Procedures (SID and STAR). Basing on the procedure design guidelines the models of procedural nominal track, tolerance area, obstacle clearance area, climb or descend gradient, manoeuvres in SID and STAR were done. The guidelines describe the operational minima thus the statistics of existing procedures was done to select the suitable procedure parameters such as a number of navigational points, segments lengths, altitudes, climb or descent gradients. Reference models of SID include straight departure and turning departure procedures. Reference models of STAR include non-precision approach procedures according to used navigational aids, i.e. GNSS, VOR. The reference procedures were numerically implemented which will be used in the further works on RPAS integration problem by simulations of the RPAS ability to execute of the SID and STAR.
Źródło:
Journal of KONES; 2019, 26, 3; 121-128
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
3E - A new paradigm for the development of civil aviation
Autorzy:
Orkisz, Marek
Kuźniar, Michał
Powiązania:
https://bibliotekanauki.pl/articles/2097457.pdf
Data publikacji:
2020
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
airplane
electric propulsion
hybrid propulsion
distributed propulsion
reduction of emission exhaust
reduction of noise
decrease of fuel consumption
samolot
napęd elektryczny
napęd hybrydowy
napęd rozproszony
redukcja emisji spalin
redukcja hałasu
zmniejszenie zużycia paliwa
Opis:
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.
Źródło:
Combustion Engines; 2020, 59, 2; 3--10
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of the application of distributed propulsion to the AOS H2 motor glider
Autorzy:
Kuźniar, Michał
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/244774.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engineering
engines
mechanical engineering
Opis:
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.
Źródło:
Journal of KONES; 2019, 26, 2; 85-92
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Experimental determination of compressor map of the DGEN 380 engine compressor using the WESTT CS/BV turbine engine simulator
Autorzy:
Pazura, Karolina
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/2097512.pdf
Data publikacji:
2021
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
compressor map
engine bench
turbofan jet engine
turbine engine
mass flow rate
mapa kompresora
ława silnika
silnik turbowentylatorowy
silnik turbinowy
masowy wskaźnik szybkości płynięcia
Opis:
Currently aviation focuses mainlly on increasing the economy and ecology of engines. Production of NOx, CO2 and SO2 adversaly impacts the environment. Parallel goal to minimize SFC to achieve both lower: emission and mission costs. The optimization of components is thus very important. One of the ways of optimizing cycle is doing that based on compressor maps. However it is very expensive to plot one since experimental work needs to be done. The aim of this article is to present a methodology of creating compressor map based on ENGINE ANALOGY. There was used the virtual bench WESTT CS/BV for tests to receive pressure ratio and mass flow of DGEN 380 for three different values of flight speed and altitude, while the rotational speed was changed. The construction similarity of CFM 56-5B and APS 3200 gives the opportunity to plotted compressor maps using the engine analogy without the need for an experiment or using the virtual bench.
Źródło:
Combustion Engines; 2021, 60, 2; 26--31
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Badania modelowe wpływu zmian objętości przestrzeni roboczych i degradacji kanału przepływowego na pracę zespołu wirnikowego silnika turbinowego w stanach nieustalonych
Autorzy:
Orkisz, Marek.
Stawarz, Sławomir.
Powiązania:
Zeszyty Naukowe Wyższa Szkoła Oficerska Sił Powietrznych, 2001, nr 1, s. 211-227
Data publikacji:
2001
Tematy:
Silniki odrzutowe badanie
Silniki lotnicze badanie
Opis:
Rys.; Bibliogr.; Streszcz.
Dostawca treści:
Bibliografia CBW
Artykuł
Tytuł:
Neural network approach to compressor modelling with surge margin consideration
Autorzy:
Loryś, Sergiusz Michał
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/2091364.pdf
Data publikacji:
2022
Wydawca:
Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:
modelling
compressor map
neural-network
Opis:
Artificial neural networks are gaining popularity thank to their fast and accurate response paired with low computing power requirements. They have been proven as a method for compressor performance prediction with satisfactory results. In this paper a new approach of artificial neural networks modelling is evaluated. The auxiliary parameter of ‘relative stability margin Z’ was introduced and used in learning process. This approach connects two methods of compressor modelling such as neural networks and auxiliary parameter utilization. Two models were created, one with utilization of the ‘relative stability margin Z’ as a direct indication of surge margin of any estimated condition, and other with standard compressor parameters. The results were compared by determination of fitting, interpolation and extrapolation capabilities of both approaches. The artificial neural networks used during the process was a two-layer feed-forward neural-network with Levenberg–Marquardt algorithm with Bayesian regularization. The experimental data was interpolated to increase the amount of learning data for the neural network. With the two models created, capabilities of this relatively simple type of neural-network to approximate compressor map was also assessed.
Źródło:
Archives of Thermodynamics; 2022, 43, 1; 89--108
1231-0956
2083-6023
Pojawia się w:
Archives of Thermodynamics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
A rotating piston engine with electric generator in serial hybrid propulsion system for use in light aircraft
Autorzy:
Kalwara, Maciej
Kuźniar, Michał
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/2097559.pdf
Data publikacji:
2021
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
hybrid
combustion engines
motor glider
rotary engine
Wankel engine
hybrid propulsion
hybryda
silniki spalinowe
motoszybowiec
silnik rotacyjny
silnik Wankla
napęd hybrydowy
Opis:
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.
Źródło:
Combustion Engines; 2021, 60, 4; 42--45
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Comparative analysis of pollutants emission by classical and distributed propulsions applied on the AOS motor glider
Autorzy:
Orkisz, Marek
Wygonik, Piotr
Kuźniar, Michał
Kalwara, Maciej
Powiązania:
https://bibliotekanauki.pl/articles/133089.pdf
Data publikacji:
2019
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
distributed propulsion
hybrid
motor glider
rotary engine
Wankel engine
hybrid propulsion
emission
exhaust gases
napęd rozproszony
hybryda
motoszybowiec
silnik rotacyjny
silnik Wankla
napęd hybrydowy
emisja spalin
Opis:
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.
Źródło:
Combustion Engines; 2019, 58, 4; 102-106
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
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
Autorzy:
Orkisz, Marek
Wygonik, Piotr
Kuźniar, Michał
Kalwara, Maciej
Powiązania:
https://bibliotekanauki.pl/articles/133727.pdf
Data publikacji:
2019
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
hybrid
combustion engines
motor glider
rotary engine
Wankel engine
hybrid propulsion
emission
exhaust gases
hybryda
silniki spalinowe
motoszybowiec
silnik rotacyjny
silnik Wankla
napęd hybrydowy
emisja spalin
Opis:
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.
Źródło:
Combustion Engines; 2019, 58, 3; 213-217
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
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