Temat: airplane - Prolib Integro

Skocz do pozycji: 1.

Tytuł:: Modelling of flight dynamics of an airplane encountering trailing vortices generated by another airplane
Autorzy:: Czechowicz, B.
Kowaleczko, G.
Nowakowski, A.
Tematy:: air transport
airplane
airplane flight dynamics
trailing vortices; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/248149.pdf Link otwiera się w nowym oknie
Opis:: This paper presents method of flight dynamics modelling for aircraft encountering trailing vortices generated by other airplane. The mathematical model of 6-DOF spatial motion was applied. Aerodynamic forces produced by a wing were calculated using strip theory method – the wing was divided into a series of chordwise strips and contribution of each strip in these forces was determined. Local angle of attack for each strip was determined taking into account an influence of trailing vortices. Exemplary results of simulations for the case of two straight vortices encountered by aircraft are shown. Incremental contributions to aerodynamic forces and moments of all strips are summed. Model and description of trailing vortices, induced velocity inside the vortex, induced velocity outside the vortex, model of motion dynamics, equations of motion, airplane forces, moments acting on the airplane, aerodynamic forces and moments, trailing vortex effect on the airplane are presented in the paper. In particular, pair of straight trailing vortices, induced velocity for Rankine vortex, strip model of the wing, angle of attack for the strip, airplane pitch angle, bank angle, altitude, trajectory are illustrated.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Determining of the optimum size of turbofan engine for obtaining the maximum range of multi-purpose airplane
Autorzy:: Wygonik, P.
Tematy:: airplane range
airplane and engine integration
engine cycle parameters; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/247502.pdf Link otwiera się w nowym oknie
Opis:: Aircraft range is one of the most important criteria of the assessment of the performance properties of an aircraft. For the needs of the paper the mathematical model of an aircraft (multi-purpose aircraft) and the engine which propels the aircraft was built (turbofan, two-spool, with jet mixer). For the analysis it was chosen so-called typical Breguet model and the conventional range. The models were modified as they should consider the characteristics of the engine in the non-dimensional form. The aim of the simulation research was to discuss the influence of the engine parameters (geometrical and thermodynamic) on the aircraft range, realized mainly in the subsonic and supersonic conditions. The decision which of these conditions can have a significant influence on the selection of the calculating point (i.e. the point which determines the geometrical dimensions of the engine) is difficult as there is no clear direction which aircrafts make up the important share in a mission or missions. It was decided that the parameter which connects the engine geometry with the range model is so-called non-dimensional coefficient of engine geometry which is the relation of the area on the inlet to the engine related to the wing area of the aircraft. It was shown that for various parameters of the engine cycle it is possible to show such a value of the non-dimensional coefficient of geometry which maximizes the aircraft range. The results obtained show opposite requirements as for the engine geometry for the subsonic and supersonic flight. On this basis the compromise solution was proposed to fulfil the requirements of the multi-purpose aircraft.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Hydrogen-powered ultralight training aircraft — a systems engineering approach
Autorzy:: Kuk, Sebastian Piotr
Tematy:: electric flight
hydrogen airplane
ultralight
training airplane
systems engineering; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/63008457.pdf Link otwiera się w nowym oknie
Opis:: This study identifies a practical and scalable entry point for hydrogen-powered aviation by applying a systems engineering and Minimum Viable Product (MVP) approach. Given persistent challenges –including hydrogen storage limitations, integration constraints, and a lack of supporting infrastructure – the most viable early application is found in a Light or Ultralight training aircraft. A hydrogen electric configuration using Proton Exchange Membrane (PEM) fuel cells and high-pressure gaseous hydrogen storage is proposed. This solution minimizes technical and logistical barriers, aligns with existing flight school operations, and offers a pathway toward broader adoption of hydrogen in aviation.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Study on Possible Replacement of the Aluminum Spar with a Composite Structure Illustrated with the Case of Agricultural Aircraft
Autorzy:: Fałek, M.
Szymczyk, E.
Jachimowicz, J.
Tematy:: composite structure
agricultural aircraft
airplane wing; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/98018.pdf Link otwiera się w nowym oknie
Opis:: Composite materials are increasingly being used in aviation. Specific stiffness and strength of composite materials (especially CFRP laminate, sandwich structure) are higher compared to metal alloys. They are beneficial features of materials used in aviation. Mass reduction of aircraft structures (e.g. due to the use of composite materials) contributes to an aircraft’s better performance in terms of its range, top speed and ceiling and consequently causes an increase in airplanes capacity. Moreover, the use of high-strength and lightweight materials in aviation contributes to longer life time and lower exploitation costs. The aim of the paper was the study the possibilities of replacing the aluminum spar of an airplane wing with a composite structure. In order to compare the mass and strength of the aluminum with the composite spar, the global shell and local solid models were created and finite elements analysis was performed. The analysis was carried out for the front spar of the wing of the agricultural aircraft PZL-106.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: European airports usefulness analysis to develop European Personal Air Transportation System (EPATS)
Autorzy:: Klepacki, Z.
Majka, A.
Tematy:: transport
projektowanie samolotów
optymalizacja
airplane design
optimization; Pokaż więcej
Wydawca:: Polskie Stowarzyszenie Telematyki Transportu
Powiązania:: https://bibliotekanauki.pl/articles/393948.pdf Link otwiera się w nowym oknie
Opis:: The paper presents results of survey of European airports and civilian landing fields. The most important features, such as location, airport category technical characteristics of the runway, and equipment were collected in a database form. Moreover, a broad demographic analysis has been performed, the objectives of which included the determination of the number of population living in the immediate vicinity of airports of various categories. Catchment areas for airports of various categories have also been specified. Based on the analysis of the results, the suitability of airports for use within air transport system operated with light transport aircraft has been evaluated.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Comparative analysis of light transport aircraft usefulness from the point of view of direct operating cost and fuel consumption
Autorzy:: Klepacki, Z.
Majka, A.
Tematy:: transport
projektowanie samolotów
optymalizacja
airplane design
optimization; Pokaż więcej
Wydawca:: Polskie Stowarzyszenie Telematyki Transportu
Powiązania:: https://bibliotekanauki.pl/articles/393950.pdf Link otwiera się w nowym oknie
Opis:: The need to increase speed, range and operational load in air transport is currently more topical than ever and is related to the efficiency of fuel use. Minimisation of costs and fuel consumption is connected with the necessity to analyse the influence of profile and procedures of flights depending on the type of aircraft functioning in the transport system. The main objective of the paper was to develop a method of determining costs and fuel consumption depending on the aircraft type and the profile of transport tasks fulfilled, and then to carry out comparative calculations for various types of aircraft designed for local transport. Based on the comparative analysis of results, conclusions have been formulated concerning the optimum ranges of using aircraft with various types of propulsion and optimum flight profiles.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Two-combustor turbofan engine performance analysis
Autorzy:: Jakubowski, R.
Tematy:: jet engine
turbofan engine
engine performance
airplane engine development; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/241903.pdf Link otwiera się w nowym oknie
Opis:: A conception of a two-combustor turbofan engine is the main scope of this paper. At the beginning, the problems of turbofan engines development are briefly discussed as a background of this work. In this part the turbofan engines innovation activities are presented. It is mentioned the engine’s innovations consists of many aspects but some important ones are: lowering of production operation cost, maintenance, reduction of noise and exhaust gases emission while engine reliability should stay on the same level or event increase. Next, the conception of turbofan engine with two combustors is presented in this context. Some positive aspects for environment, production and maintenance of such engine are discussed. Then the thermodynamic cycle of two-combustor engine is presented and analysed. On this basis, the engine numerical model is prepared. Next, some information about the model simplifications and calculations done to determine performance of the engine is presented. Then the results of the simulation calculations of the engine performance are presented and discussed. The relationship of engine thrust and specific fuel consumption vs. engine flight conditions are shown. Based on the results there were discussed the advantages and disadvantages of two combustors engine as an airplane propulsion are specified. The conclusions are formulated and presented in the last part of the paper.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Rational moulding of constructional figure and the usable properties of the airplane
Racjonalne formowanie postaci konstrukcyjnej i cech użytkowych samolotu
Autorzy:: Klepacki, Z.
Majka, A.
Tematy:: transport
projektowanie samolotów
modelowanie
optymalizacja
airplane design
modelling
optimization; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/242868.pdf Link otwiera się w nowym oknie
Opis:: The choice ofparameters of designed airplane should take place according to rational rules, allows to evaluate of project-variants. In spite of the evidence of this ascertainment, both the theory and the designing practice concentrates on the methods of seeking of solutions, and the problem of valuing is maximized simplified, and sometimes outright vulgarized. During that time, it is criteria and limitations determine the form of unknotting, and in the effect about the commercial success of all undertaking. The schema of the general designing of the airplane permits to restore approximate conditions for the real work of the airplane. Obtained results substantially are relative to "depths" of the modelling of the airplane characteristic (accuracy of partial models), the end result is a compromise. Authors worked out the software for different types of airplanes obtaining probable results of calculations. The main elements of the definition of the projects task, the full and reduced morphological board, the partial model, the mathematical model of the airplane are illustrated in the paper.
Wybór parametrów projektowanego samolotu powinien odbywać się według racjonalnych zasad, pozwalających wartościować warianty projektowe. Mimo oczywistości tego stwierdzenia, teoria i praktyka projektowania koncentruje się na technikach szukania rozwiązań, zaś problem wartościowania jest maksymalnie upraszczany, a czasem wręcz trywializowany. Tymczasem, to kryteria i ograniczenia stanowią o postaci rozwiązania, a w efekcie o sukcesie handlowym całego przedsięwzięcia. Schemat ogólnego projektowania samolotu pozwala odtworzyć warunki zbliżone do rzeczywistego funkcjonowania samolotu, Uzyskane wyniki w dużym stopniu zależą od "głębokości" modelowania właściwości samolotu (precyzji modeli cząstkowych), rezultat końcowy jest wynikiem kompromisu. Autorzy opracowali oprogramowanie dla różnych typów samolotów uzyskując prawdopodobne wyniki obliczeń. Główne elementy definicji zadania projektowego, pełna i zredukowana tablica morfologiczna, model cząstkowy oraz model matematyczny samolotu są zilustrowane w artykule.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Optimal cruise performance of light transport aircraft from fuel efficiency point of view
Optymalne osiągi przelotowe lekkiego samolotu transportowego z punktu widzenia zużycia paliwa
Autorzy:: Klepacki, Z.
Majka, A.
Tematy:: transport
projektowanie samolotów
modelowanie
optymalizacja
airplane design
modelling
optimization; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/244209.pdf Link otwiera się w nowym oknie
Opis:: The need for the increase of speed, range and the useful load of general air transport is presently more actual than ever. In direct conjunction with these factors is the aircraft fuel efficiency. Determination of the fuel quantities used up in aircraft motions both in the air and on the ground has very essential meaning in the analysis of economics of the air transport. Reducing the amount of fuel consumed involves knowing the effect of alternate profiles and procedures on fuel consumption or fuel flow for the various aircraft types operating in the system. The aviation community is striving to provide more fuel efficient operations in the system. Critical to many of the efforts is the ability to estimate fuel consumption. A methodology of SFC (specific fuel consumption) valuation relating to aircraft performance and actual flight profile is the main goal of the work. Aircraft fuel consumption model consist of two submodels. The first is the aircraft computational model, with several submodels: geometrical, aerodynamic, mass, power unit. The second is utilization model, namely transport operation model. The calculations were done for few different categories airplanes. Final results and recommendations based on the analysis of fuel consumption and transportation energy effectiveness are presented in conclusions.
Potrzeba zwiększania szybkości, zasięgu i ładunku użytecznego transportu lotniczego jest obecnie bardziej aktualna niż kiedykolwiek. Wiąże się z tym sprawność wykorzystania paliwa. Określenie ilości paliwa zużywanego przez samolot poruszający się zarówno w powietrzu jak i na ziemi ma bardzo istotne znaczenie w analizie ekonomiki transportu. Minimalizacja ilości zużytego paliwa wymaga przeprowadzenia analizy wpływu profilu i procedur wykonywania lotów na wymaganą ilość paliwa w zależności od typu samolotu funkcjonującego w systemie transportowym. Firmy lotnicze dążą do wykonywania zadań z maksymalną efektywnością z punktu widzenia zużycia paliwa. Dla wielu z nich najważniejszym zadaniem jest, więc możliwość wiarygodnego oszacowania zużycia paliwa. Głównym celem pracy było opracowanie metody wyznaczania zużycia paliwa w zależności od rodzaju samolotu i profilu lotu. Aby zrealizować ten cel opracowany został odpowiedni model matematyczny składający się z dwóch pod-modeli. Pierwszy z nich to kompleksowy model obliczeniowy samolotu, drugi zaś, model użytkowania. Z wykorzystaniem tych dwóch modeli wyznaczone zostały wskaźniki oceny efektywności samolotów różnych kategorii wykonujących typowe zadania transportowe. Na podstawie analizy porównawczej wyników, sformułowane zostały wnioski dotyczące optymalnych zakresów użytkowania samolotów z różnymi rodzajami napędu oraz optymalnych profilów przelotowych.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: The influence of multi - role aircraft mission type on the low bypass engine performance parameters
Autorzy:: Wygonik, P.
Tematy:: gas turbine engine design
airplane-engine integration
aircraft mission optimization; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/242065.pdf Link otwiera się w nowym oknie
Opis:: The aim of the article is to find the relationship and dependencies between the mission parameters of the multi-role aircraft (altitude, flight velocity, thrust load) and the parameters that define the flow of the turbofan engine. The conclusions of these studies are relevant at the stage of preliminary engine design. There was built the model of thermal cycle of low bypass. The model of an airplane was simplified to its aerodynamic characteristics. The mission was divided into air tasks (stages) such as a take-off, a climb at a certain velocity, sub and supersonic flight and maneuvers (i.e. turn). Dimensionless energy criteria binding both the engine and aircraft parameters were introduced. There were conducted the simulation studies of the model airplane-engine mission to show the part of the mission that "dimensions " the engine. The results were limited to the presentation of the impact of circuit parameters such as T3, π, μ on the defined criteria. The calculations were carried out for a number of selected missions defined in the literature as Loll, HiLoHi and HiHiHi. The comparison of the energy requirements of these missions was done. There were pointed out these criteria of the mission evaluation that may affect making decisions at early design stages. There were designated the areas of design variability in an engine meeting the criteria for energy mission. The advantage of this model is universal character of dimensionless criteria, whereas the disadvantage is the need to build complex models of the engine and the assumption at the outset aerodynamic characteristics of the aircraft. The originality of the presented solution is to show an alternative, unconventional approach to the design process (not as so far) the engine itself but the entire aviation system.
Dostawca treści:: Biblioteka Nauki

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