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Wyszukujesz frazę "Ścisłowski, Karol" wg kryterium: Autor

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    Wyświetlanie 1-5 z 5
    Tytuł:
    An assessment of the transient effect on helicopter main rotor stability and power demand
    Autorzy:
    Raczyński, Radosław
    Siadkowska, Ksenia
    Ścisłowski, Karol
    Wendeker, Mirosław
    Powiązania:
    https://bibliotekanauki.pl/articles/2202519.pdf
    Data publikacji:
    2022
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    propulsion
    rotor
    power demand
    helicopter
    transient effect
    napęd
    wirnik
    zapotrzebowanie na moc
    śmigłowiec
    efekt przejściowy
    Opis:
    The researched object is a helicopter main rotor with blades of variable geometric twist characteristics. Variable torsion refers to systems of actuators made of shape memory alloys. The presented numerical analyses allow for evaluating both the dynamics of the rotor in transient states, i.e. in the zone between the static phase and the full activation phase and the impact of the change on the pulsation of the amplitude of the necessary power generated by the rotor corresponding the flight state, and thus covering the demand by the disposable power generated by the engine. This study follows a methodology of numerical analyses based on Multi Body Dynamics and the Finite Element Method and uses fluid mechanics elements and algorithms to analyze lift generation, compiled in a single computational environment referring to the same period of time.
    Źródło:
    Combustion Engines; 2022, 61, 4; 23--28
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of propulsion units dedicated to test stands for aviation systems
    Autorzy:
    Siadkowska, Ksenia
    Czajka, Błażej
    Ścisłowski, Karol
    Wendeker, Mirosław
    Powiązania:
    https://bibliotekanauki.pl/articles/2097514.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    combustion engine
    electric motor
    test stand
    unmanned aerial vehicle
    silnik spalinowy
    silnik elektryczny
    stanowisko pomiarowe
    bezzałogowy statek powietrzny
    Opis:
    This paper presents an analysis of selected propulsion units dedicated to test stands for unmanned aircraft systems. It focuses on engines suitable for aircraft with a maximum take-off mass up to 150 kg. The study includes an analysis of propulsion units that can be used to power systems on stationary test stands dedicated to advanced research and measurement of prototype aerospace technologies intended for use in rotorcraft. The analysis of propulsion units shows that electric units are a better choice for powering UAV rotorcraft test stands. Their main advantages include the possibility to simplify the construction of the device by eliminating gears and to mount the motor in a vertical position, simpler power supply, cooling and control systems and the lack of an exhaust system. Additional advantages are undoubtedly lower vibration generation, cheaper and easier operation as well as better comfort.
    Źródło:
    Combustion Engines; 2021, 60, 2; 39--43
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Strength analysis of a prototype composite helicopter rotor blade spar
    Autorzy:
    Kliza, Rafał
    Ścisłowski, Karol
    Siadkowska, Ksenia
    Padyjasek, Jacek
    Wendeker, Mirosław
    Powiązania:
    https://bibliotekanauki.pl/articles/2097429.pdf
    Data publikacji:
    2022
    Wydawca:
    Polskie Towarzystwo Promocji Wiedzy
    Tematy:
    FEM
    composite spar
    main rotor blade
    carbon fiber
    strength analysis
    Opis:
    This paper investigates the strenght of a conceptual main rotor blade dedicated to an unmanned helicopter. The blade is made of smart materials in order to optimize the efficiency of the aircraft by increasing its aerodynamic performance. This purpose was achieved by performing a series of strength calculations for the blade of a prototype main rotor used in an unmanned helicopter. The calculations were done with the Finite Element Method (FEM) and software like CAE (Computer-Aided Engineering) which uses advanced techniques of computer modeling of load in composite structures. Our analysis included CAD (Computer-Aided Design) modeling the rotor blade, importing the solid model into the CAE software, defining the simulation boundary conditions and performing strength calculations of the blade spar for selected materials used in aviation, i.e. fiberglass and carbon fiber laminate. This paper presents the results and analysis of the numerical calculations.
    Źródło:
    Applied Computer Science; 2022, 18, 1; 5--19
    1895-3735
    Pojawia się w:
    Applied Computer Science
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of operating parameters of the aircraft piston engine in real operating conditions
    Autorzy:
    Czarnigowski, Jacek
    Rękas, Daniel
    Ścisłowski, Karol
    Trendak, Michał
    Skiba, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/2097612.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    piston engine
    engine parameters
    statistic
    normal operating conditions
    silnik tłokowy
    parametry silnika
    statystyka
    normalne warunki pracy
    Opis:
    The article presents the results of analysis of operational parameters of piston engine CA 912 ULT which is a propulsion system of ultralight gyroplane Tercel produced by Aviation Artur Trendak. Research was conducted under normal operating conditions of the autogyro and data was collected from 20 independent tests including a total of 28 flight hours, divided into training flights and competition flights. Engine speed, manifold air pressure and temperature, fuel pressure, injection time, and head temperature were recorded at 9 Hz during each flight. Collective results were presented to show the statistical analyses of the individual parameters by determining the mean values, standard deviations and histograms of the distribution of these parameters. Histograms of operating points defined by both engine speed and manifold air pressure were also determined. Analyses of the engine dynamics as a distribution of the rate of change of the engine rotational speed were also carried out. It was shown that the engine operating points are concentrated mainly in the range of idle and power above 50% of nominal power. The most frequent range is 70-80% of nominal power. It was also shown that the dynamics of engine work in real operating conditions is small. It was also shown that the way of use significantly influences the distribution of operating points. During training flights, an increase in the number of take-offs and landings causes an increase in the amount of engine work at take-off and nominal power and at idle.
    Źródło:
    Combustion Engines; 2021, 60, 4; 83--89
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Bench Tests for Exhaust Gas Temperature Distribution in an Aircraft Piston Engine with and without a Turbocharger
    Autorzy:
    Czarnigowski, Jacek Andrzej
    Skiba, Krzysztof
    Rękas, Daniel
    Ścisłowski, Karol
    Jakliński, Piotr
    Powiązania:
    https://bibliotekanauki.pl/articles/2123277.pdf
    Data publikacji:
    2021
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    temperature distribution
    piston engine
    exhaust system
    turbocharging
    Rotax 912
    Opis:
    In ultralight aviation, a very important engine parameter is the power-to-weight ratio. On the one hand, there is a tendency to minimize the size and weight of engines, and on the other hand, there is a demand to achieve the highest possible power by using supercharging systems. Increasing power brings many benefits, but it also increases temperature in the exhaust system, posing a threat to delicate parts of the ultralight aircraft fuselage. Therefore, it is necessary to control temperature values in the engine exhaust system. This article presents the temperature distribution in the exhaust system of an aircraft engine by the example of a four-cylinder Rotax 912 engine with an electronic fuel injection system. The research was conducted in two stages: measurements were made first for the engine without a turbocharger with an original exhaust system and later for its modified version with an added turbocharger system. The paper presents a comparative analysis of exhaust gas temperatures measured at three points: 30, 180 and 1000 mm from the cylinder head. The tests were conducted for the same preset engine operating conditions at constant speed and manifold air pressure. It has been shown that the exhaust temperature in the exhaust manifold decreases with the distance from the cylinder head. The highest gradient, over three times higher than the gas temperature from 589.9 °C to 192.3 °C, occurred in the manifold with a turbocharger for 2603 RPM and 31 kPa of manifold air pressure. The introduction of turbocharging causes an increase in exhaust gas temperatures before the turbocharger by an average of 12%, with this increase being greater for operating points of higher inlet manifold pressure. Turbocharging also causes a significant decrease in exhaust gas temperatures behind the turbocharger and the silencer because the temperature drops there by an average of 25%.
    Źródło:
    Advances in Science and Technology. Research Journal; 2021, 15, 3; 155--166
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-5 z 5

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