Temat: aircraft transport - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Polityka rozwoju innowacyjnych rozwiązań w transporcie lotniczym
Development policies of innovative solutions in air transport
Autorzy:: Żmigrodzka, Małgorzata
Kostur-Balcerzak, Katarzyna
Powiązania:: https://bibliotekanauki.pl/articles/26850858.pdf
Data publikacji:: 2017
Wydawca:: Akademia Zamojska
Tematy:: Remotely Piloted Aircraft Systems
Unmanned Aviation Vehicle
innovation
air transport
bezzałogowe statki powietrzne
innowacyjność
transport lotniczy
Opis:: Ostatnie lata wskazują na dynamiczny rozwój coraz to lepszych technologii bezzałogowych statków powietrznych RPAS/UAV (ang. Remotely Piloted Aircraft Systems/Unmanned Aviation Vehicle), potocznie nazywanych „dronami”, których terminologia wywodzi się z regulacji Organizacji Międzynarodowego Lotnictwa Cywilnego (ICAO). Zainteresowanie ich eksploatacją wzrasta nie tylko do celów militarnych, ale też cywilnych, w tym komercyjnych. Celem artykułu jest analiza kierunku rozwoju bezzałogowych statków powietrznych i zaprezentowanie aktualnych możliwości wykorzystania nowych technologii w transporcie lotniczym. Analizując omawiane trendy, autorzy skorzystali m.in. z materiałów udostępnionych na oficjalnych stronach instytucji nadzorujących transport lotniczy, jak również światowych organizacji nawiązujących do tematyki objętej obszarem rozważań zawartych w niniejszym artykule. Trendy światowe idą w kierunku rozwoju nowych technologii, co daje lepsze możliwości techniczne. Problematyczny staje się jednak stan regulacji prawnych, jak również niski poziom świadomości potencjalnych użytkowników. W opinii ekspertów jest jeszcze wiele do zrobienia zanim UAV zostaną wprowadzone do użytku publicznego na szeroką skale. Wiąże się to z wieloma czynnikami. Jednym z nich jest edukacja w nowej dziedzinie lotnictwa cywilnego, z czym wiąże się przygotowanie odpowiednich kadr zarządzających tymi systemami.
Recent advances in Remotely Piloted Aircraft Systems/Unmanned Aviation Vehicle technologies are on the rise. They are popularly called ‘drones’ and their terminology derives from ICAO regulations. The interest in drone exploitation involves not only military but also civilian and commercial areas. The aim of this article is to give an insight into the development direction of remotely piloted aircraft and present current possibilities of using new technologies in air transport. The authors of the article used the subject of research literature analysis method including the sources available on the official websites of the air transport inspecting authorities, as well as world organizations relating to the subject matter analysed in this article. Recent advances in new technologies are on the rise, which offers potential. The condition of law regulations as well as low awareness of the potential users is, however, problematic. According to experts, there is still much to be done before UAV are mass-produced. It is connected with numerous factors. One of them is education in the new branch of civil aviation, which involves senior personnel training.
Źródło:: Facta Simonidis; 2017, 10, 1; 179-194
1899-3109
Pojawia się w:: Facta Simonidis
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: XX lat programu samolotów lekkich i bezpieczeństwa (PSLIB)
Twenty years of Light Aircraft and Safety Program
Autorzy:: Wiśniowski, W.
Powiązania:: https://bibliotekanauki.pl/articles/212379.pdf
Data publikacji:: 2014
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: Program Samolotów Lekkich i Bezpieczeństwa (PSLiB)
konstrukcje
technologie
patenty
Europejski System Transportu Lotniczego
Light Aircraft and Safety Program
constructions
technologies
patents
European Air Transport System
Opis:: W roku 1994 zainicjowano w Instytucie Lotnictwa realizację Programu Samolotów Lekkich i Bezpieczeństwa z myślą o wykreowaniu polskiej specjalności w warunkach nowych realiów ekonomicznych. W pracy przedstawiono konstrukcje, technologie, patenty i publikacje powstałe w ramach programu w ostatnich 20 latach. Podkreślono, że spełnieniem dla twórców programu jest decyzja Komisji Europejskiej o włączeniu lotnictwa lekkiego do Europejskiego Systemu Transportu Lotniczego.
In 1994 in the Institute of Aviation was initiated the realisation of the Program of Light Aircraft and Safety with the aim of creating a Polish specialty in the conditions of the new economic reality. In the paper were presented constructions, technologies, patents and publications created within the program in the last 20 years. It was empasised that a fulfillment for the creators of the program is the decision of the European Commission about including light aircraft into the European Air Transport System.
Źródło:: Prace Instytutu Lotnictwa; 2014, 3 (236) September 2014; 7-25
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Resonance tests - vibration mode shapes from the wing torsion group
Autorzy:: Wiśniewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/245897.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft
resonance tests
vibration mode
torsion wing
Opis:: Resonances of the „ wings torsion " mode shapes to a large extent depend on the structural parameters of the wing, and more specifically to the existence or not of fuel tanks at the wings ends, munitions hard points or engines mounted on the wings. In the paper the group of resonances is presented with mode shapes in which the one, two or three node aircraft wing torsion is present. It is shown in the paper, that these vibration mode shapes consist both of fuselage bending or torsion. Resonance frequencies with mode shapes in which one, two or three node wing torsion occurs depend fundamentally on existence of wing hardpoints. If hardpoints are occupied by fuel tanks, these frequencies are varying continuously in wide range. The various interesting from cognitive point of view combinations have place then, including variable frequencies and variable mode shapes as a function of fuel consumption. The aim for the analysis of 3 cases of resonance a wing torsion mode shapes of airplanes and gliders was to investigate the relationships and mechanisms that are taking place and operate between the torsioningl vibration of the wings and bending or torsion vibrations of the fuselage. Recognition of these phenomena should facilitate the researcher to understand and search effectively and explore the resonances of„ wing torsion " mode shapes.
Źródło:: Journal of KONES; 2009, 16, 4; 557-561
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Determination of water collection on two- and three-dimensional aerodynamic surfaces in external two-phase flow in atmospheric conditions
Autorzy:: Sznajder, R.
Powiązania:: https://bibliotekanauki.pl/articles/244126.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: flow simulations
aerodynamics
two-phase flow
simulation of ice accretion
aircraft engineering
transport
vehicles
Opis:: Simulations of two-phase flow cases consisting of air and water dispersed in atmosphere were conducted using ANSYS FLUENT solver. The computational model was built with the aim of determination of zones of water droplets impinging on the investigated surface, which is a first step towards simulations of ice accretion in flow conditions where super cooled water is present as dispersed phase. It follows Eulerian approach, currently most effective approach for determination of distribution of water collection on two- and three-dimensional surfaces. Dispersed water is treated as continuous phase and its transport equations are being solved along with air flow equations in the whole computational domain. There are two specific factors of this two-phase flow problem. One of them is ratio of air and water density, which is a cause of existence of two time scales in obtaining a numerical solution of this problem: one for convergence of air flow solution and another for solution of flow of dispersed water in the computational domain. This required development of a specific strategy in obtaining a numerical solution in some circumstances important in aerodynamics, especially at high angle of attack with flow recirculation zones on the wing. The other factor is relatively low concentration of water droplets in conditions important for atmospheric icing. The consequence of this is possibility of uncoupling of solution for both phases and narrowing the solution of the phase of dispersed water to a small region of non-uniformity of velocities of the dispersed phase. Results for two objects: an airfoil and helicopter tail rotor blade, exploiting the developed computational strategy will be presented.
Źródło:: Journal of KONES; 2016, 23, 1; 369-376
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Analysis of effects of shape and location of micro-turbulators on unsteady shockwave-boundary layer interactions in transonic flow
Autorzy:: Sznajder, J.
Kwiatkowski, T.
Powiązania:: https://bibliotekanauki.pl/articles/242878.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transonic flow control
laminar-turbulent transition
flow simulations
aircraft engineering
transport
vehicles
Opis:: Solutions for turbulisation of a part of laminar boundary layer upstream of shockwave on laminar airfoil in transonic flow were investigated by means of solution of Unsteady Reynolds-Averagd Navier-Stokes equations using as a closure the four-variable Transition SST turbulence model of ANSYS FLUENT solver. This turbulence model has the capability of resolving laminar-turbulent transition occurring in undisturbed flow as well as under the influence of flow-control devices. The aim of the work was to investigate possibilities of improvement of aerodynamic characteristics of laminar wing of a prospective transport aircraft in adverse conditions characterised by occurrence of a shockwave over a laminar-turbulent transition region with separation of laminar flow under the shockwave. The subject is important for application of laminar flow technology, offering economic and environmental advantages due to decreased friction drag, into civil transport aviation. Natural laminar-turbulent transition in the investigated conditions takes place with occurrence of “laminar separation bubble” under the foot of a shockwave and the resulting shockwave is intensive and prone to unsteady oscillations, the “buffet” phenomenon, limiting operational range of flight parameters. In order to counteract the harmful effects of natural laminar-turbulent transition in transonic flow two types of turbulators, placed upstream of the shockwave, were investigated. One of them consisted of delta-shaped vortex generators, producing chordwise-oriented vortices. The other consisted of rectangular micro-vanes, perpendicular to flow and to airfoil surface producing vortices of rotation axes oriented spanwise. Effectiveness of both types of turbulators was investigated for varying height and their location on airfoil chord. Both types of turbulators have proved their effectiveness in tripping laminar boundary layer. The specific effects of the tutbulators, different for each type occurred in the region where laminar separation takes place on clean airfoil. As a result, the changes of lift and drag were different for each type of turbulators.
Źródło:: Journal of KONES; 2016, 23, 2; 373-380
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Determination of ice deposit shape and ice accretion rate on airfoil in atmospheric icing conditions and its effects on airfoil characteristics
Autorzy:: Sznajder, J.
Sieradzki, A.
Stalewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/242499.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aerodynamics
two-phase flow
simulation of ice accretion
aircraft engineering
transport
vehicle
Opis:: Simulations of ice accretion on airfoil in icing conditions were conducted using ice accretion model implemented by authors in ANSYS FLUENT CFD solver. The computational model includes several sub-models intended for simulations of two-phase flow, determination of zones of water droplets impinging on the investigated surface, flow of water in a thin film on airfoil surface and heat balance in air-water-ice contact zone. The method operates in an iterative loop, which enables determination of effects of gradual deformation of aircraft surface on airflow over the surface, which has impact on distribution of collected water, flow of water film over the surface and local freezing rates. The implementation of the method in CFD solver made it necessary to complement the mathematical model of determination of local rates of deformation of aircraft surface with modification of computational mesh around the surface, which must conform, to the deformed surface. Results of simulated ice accretion on NACA 0012 airfoil were compared with results of experiment conducted in icing wind tunnel for a 420 s long process of ice accretion in steady-flow, steady angle-of-attack conditions. Close agreement of values and location of maximum ice thickness obtained in experiment and in the flow, simulations can be observed. For the airfoil deformed with ice, contour determination of its aerodynamic characteristics at several other angles of attack was conducted proving dramatic degradation of its aerodynamic characteristics due to ice deformation.
Źródło:: Journal of KONES; 2017, 24, 2; 271-278
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Simulation of rime icing and its effects on aerodynamic characteristics of an airfoil
Autorzy:: Sznajder, J.
Powiązania:: https://bibliotekanauki.pl/articles/243475.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: computational fluid dynamics
aerodynamics
two-phase flow
simulation of ice accretion
heat exchange
aircraft engineering
transport
vehicle
Opis:: A mathematical model for simulation of icing dedicated to simulation of ice accretion and its effects on aircraft aerodynamic characteristics in conditions of rime icing is presented. Pure rime icing occurs at lower temperatures than glaze icing and results in higher roughness of the surface of deposited ice. The model accounts for increased surface roughness, in terms of equivalent sand grain roughness, caused by deposited rime ice, which influences generation and dispersion of heat in the boundary layer. Increase of surface roughness is determined by analytical models created upon experimental data obtained in icing wind tunnels. Increased generation of heat is a result of increased tangential stress on the surface and is quantified in the temperature recovery factor determined numerically by a CFD solver. Effects of surface roughness on the intensity of forced convection are quantified by application of Colburn analogy between heat and momentum transfer in the boundary layer, which allows assessment of heat transfer coefficient for known friction coefficient, determined by CFD. The computational method includes determination of the surface distribution of mass of captured water in icing conditions. The model of freezing of captured water accounts for generation of heat due to latent heat of captured water droplets, temperature recovery in boundary layer and kinetic energy of captured droplets. The sinks of heat include forced convection, heating of super cooled droplets, conduction of heat through the ice layer and sublimation. The mathematical model is implemented as user-defined function module in ANSYS Fluent solver. The results include effects of deposited ice, including increased surface roughness on aerodynamic characteristics of an airfoil.
Źródło:: Journal of KONES; 2018, 25, 3; 437-443
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Possibilities of voice supporting of the pilot in multi-task military aircraft
Autorzy:: Szelmanowski, A.
Pazur, A.
Prusik, T.
Malanowicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/247441.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aviation
aircraft voice supporting system
cockpit voice activated system
lotnictwo
Opis:: The article presents selected results of the analytical works, carried out in the Air Force Institute of Technology, in the field of possibilities to support the pilot’s work in the cabin of the modern multi-task aircraft or military helicopter with the use of the computer voice communication assistant, with automatic recognition of the pilot’s voice and speech, which operates in conditions of the lack of time. There are presented the voice systems warning the pilot of the occurrence of an emergency state, as the so-called voice guides, P-591-04 type, used in the MiG-29 multipurpose aircraft and RI-65 type, used in the Mi-17 and Mi-24 helicopters. As an example of implementation of the concept of a new system supporting the pilot’s work, there was selected the voice communication system, constructed in the Air Force Institute of Technology for the W-3PL multi-purpose helicopter with the ZSA integrated avionics system. The main research problems related to the construction of integrated avionics systems, verbally supporting the pilot’s work, were discussed, and the specialized tools and research stations used in the Air Force Institute of Technology for the phonoscopic speech and voice studies, were presented. Furthermore, an example of the functional diagram and the system architecture of the pilot’s work verbal supporting for a selected emergency situation on the aircraft board were demonstrated, as well as the expected range of that system’s applications.
Źródło:: Journal of KONES; 2017, 24, 1; 333-338
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Research method of dynamic capability of an actuating block of the SSP-FK aircraft fire suppression system in false alarm aspect
Autorzy:: Szelmanowski, A.
Zieja, M.
Głyda, K.
Tokarski, T.
Powiązania:: https://bibliotekanauki.pl/articles/244205.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft fire suppression systems
research
simulation methods
aircraft fire protection
Opis:: Numerous cases of self-activation of the SSP-FK aircraft fire suppression system (including commissioning of valves and extinguishing tanks) testify about the fact that it is not yet fully understood in the technical aspect, and because of the performed role on the aircraft is the basic element to ensure flight safety. Solving problems with false fire signalling of the SSP-FK system is an important issue for the safe operation of aircraft and military helicopters, because it is preventive (to warn the crew of the possibility of fire) and rescue system (aiming at extinguish the fire) in each phase of a flight. In addition, the SSP-FK system is used on many types of military aircraft (including helicopters from W-3/3W/3WA/3PL and Mi/8/14/17/24 family as well as An-28 and Tu-154M aircraft. The paper presents selected results of work in the Air Force Institute of Technology in the study of SSP-FK fire suppression system (as one of the main protection systems on-board) used on many types of military aircraft operated in the Polish Armed Forces. In determining the conditions of the false signalling of fire, simulation models of action blocks implementing of the SSP-FK fire suppression system were developed. The research on simulation models was performed in Matlab-Simulink and Circuit-Maker computing packages. The results of these works were used to diagnose selected modules and blocks of the SSP-FK system during the study of actual cases of their false activation.
Źródło:: Journal of KONES; 2016, 23, 3; 525-531
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Development of the aircraft power plants - challenges
Autorzy:: Szczeciński, S.
Powiązania:: https://bibliotekanauki.pl/articles/242001.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
combustion engines
internal combustion aircraft engine
Opis:: On the background of a current level of the aircraft power plants modernities presented here is the trial settlement of the possible directions of their further development - resultant from the current and future economic, military, sports needs. The general direction of development of all types of aeronautical propulsion systems, and also of these produced a long time ago and exploited for many years, is their permanent " upgrade" in the new equipment and of methodic of the current technical state checking for the purpose of the indispensable flights safety assurance, the prolongation of the failure-free exploitation time - but also the maintenance of the economic concurrency requirements. Recently, a categorical form receives the requirement of the noise limitation of aviation power plants and the limitation for emission of toxic elements in exhaust. In the piston engines, the direction of developments are aimed on the design of compression ignition engines, fuelled with standardized aircraft jet fuel. Their additional valour is their smaller fuel expenditure, about 30% less with respect to their spark ignition equivalents. Particularly important is the task of decrease the quantities of fuel used up, the limitation of number of produced engines through raising their efficiency and durability, limitation of noisiness of engines alone and driven: propellers, ventilators and the lifting rotors of helicopters, the limitation of thrust, required to the flight of the airplanes and the helicopters. One turned attention on ecological requirements, which force the application of mineral fuels completed by biofuels.
Źródło:: Journal of KONES; 2008, 15, 4; 545-555
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Modification of aerodynamic wing loads by fluidic devices
Autorzy:: Stalewski, W.
Sznajder, J.
Powiązania:: https://bibliotekanauki.pl/articles/243884.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engineering
mechanical engineering
Opis:: Airplane wing load control systems are designed for modification/redistribution of aerodynamic loads in order to decrease risk of structural damage in conditions of excessive loads, to improve passenger comfort in turbulent atmosphere or to act as flight control systems. Classical examples include systems involving symmetric deflections of ailerons reducing wing root bending moments (Lockheed C-5 Galaxy) or deflections of spoilers stabilizing landing approach path (Lockheed TriStar). The fast development of Micro Electromechanical Systems and their application in Flow Control System opens the perspectives of designing practical wing load control systems based on fluidic actuators, modifying local aerodynamic loads by inducing changes to flow, for example, by inducing flow separation in the boundary layer or modifying Kutta condition on the trailing edge. This is the principle of operation of novel concepts of flow control actuators proposed by Institute of Aviation and discussed in the paper. The systems include actuators in the central part of the wing section, reducing local lift similarly to classical spoilers and actuators on the modified trailing edge, acting similarly to ailerons. The potential advantages in comparison to classical devices include potentially shorter reaction time because of avoiding the necessity of moving large surfaces against high dynamic pressure, which is important in conditions of fast-changing loads in turbulent atmosphere.
Źródło:: Journal of KONES; 2014, 21, 3; 271-278
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Sposoby ograniczenia hałasu emitowanego do środowiska przez transport lotniczy
Solutions to decrease the noise emitted by air transport to enviroment
Autorzy:: Śliwińska, A.
Powiązania:: https://bibliotekanauki.pl/articles/403133.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
Tematy:: transport lotniczy
lotnictwo
zanieczyszczenie środowiska
hałas
ograniczenie hałasu
air transport
aircraft
environment pollution
noise
noise reduction
Opis:: Wykonywanie transportu lotniczego, jak również prowadzenie działalności na terenie portów lotniczych, odpowiada za zanieczyszczenie środowiska hałasem, który utrudnia funkcjonowanie i ma wpływ na życie ludzi i zwierząt. W artykule omówione zostały sposoby redukcji emisji wysokich dźwięków do środowiska, których źródłem są przede wszystkim statki powietrzne, a także funkcjonowanie lotnisk. Przeprowadzone badania wskazały, że stosowane są liczne rozwiązania, które ograniczają emisję hałasu. Wprowadzenie i wykorzystanie nowych technologii, a także rozwiązań technologicznych do walki ukierunkowanej na obniżenie hałasu zarówno w sposób czynny, jak i bierny, pociąga za sobą zmniejszenie negatywnego wpływu hałasu na środowisko.
The air transport as well as the service provided at airports is responsible for noise emission to the local environment, which hinders the functioning and living, of both, people and animals. The paper shows the potential solutions aimed at reducing the emission of high sounds to the environment, which are primarily caused by aircraft, as well as the activities and functioning of airports. The conducted research has shown that there are numerous solutions which may lead to decrease of the noise emission. Just the introduction and use of new technologies, as well as technological solutions have an impact on the reduction of noise, both in an active and passive way. Undoubtedly both have an impact on its reduction and entails a reduction of its negative impact on the local environment. The aim of this study was to characterize the methods, the solutions which can be use either at airports, or in their surroundings or in aircraft’s construction, which allows to reduce the noise emission to the local environment by air transport. The article is a response to the research problem, which was.
Źródło:: Budownictwo i Inżynieria Środowiska; 2018, 9, 2; 89-95
2081-3279
Pojawia się w:: Budownictwo i Inżynieria Środowiska
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Wstępna analiza wpływu wybranych czynników zewnętrznych i parametrów eksploatacyjnych transportowego samolotu odrzutowego na zużycie paliwa
Impact of selected environmental and flight data parameters on fuel consumption of the jet transport aircraft – initial analysis
Autorzy:: Sklorz, R.
Puzio, Ł.
Brodny, J.
Powiązania:: https://bibliotekanauki.pl/articles/113023.pdf
Data publikacji:: 2017
Wydawca:: STE GROUP
Tematy:: transportowy samolot odrzutowy
zużycie paliwa
parametry lotu
fazy lotu
jet transport aircraft
fuel consumption
flight data parameters
flight phases
Opis:: Celem wszystkich przedsiębiorstw jest osiągniecie jak najwyższej efektywności ekonomicznej. Dotyczy to także przewoźników lotniczych. Jednym z obszarów, w którym istnieją możliwości poprawy tej efektywności jest zmniejszenie kosztów eksploatacji posiadanych środków technicznych, głównie samolotów. W tym zakresie oczywistym wydaje się zmniejszenie zużycia paliwa przez samoloty. Aby w procesie tym osiągnąć zadowalające wyniki konieczne jest zidentyfikowanie czynników zewnętrznych oraz parametrów eksploatacyjnych mających największy wpływ na to zużycie. W artykule przedstawiono wstępną analizę wpływu tych wielkości na zużycie paliwa transportowego samolotu odrzutowego. W tym celu dokonano analizy poszczególnych faz lotu samolotu z uwzględnieniem czynników mających najistotniejszy wpływ na zużycie paliwa. Przedstawiono także najważniejsze parametry pracy samolotu rejestrowane w czasie jego lotu oraz dokonano wstępnej analizy ich wpływu na zużycie paliwa. Przedstawione opracowanie należy potraktować jako wstępne do bardziej zaawansowanych analiz optymalizacyjnych zużycia paliwa w samolotach odrzutowych.
Every enterprise aims at maximizing economic yield, including air carrier enterprises. Optimization of direct operating costs related to aircraft operation is a key contributor to economic yield. Fuel consumption constitutes the biggest single direct operating cost for all air carriers, therefore its optimization is of utmost importance. Identification of environmental factors and flight data parameters affecting it is crucial. This article presents initial analysis of selected environmental factors and flight data parameters influencing fuel consumption for distinctively selected flight phases. Analysis given below should be treated as preliminary, giving introduction to the more advanced elaborations.
Źródło:: Systemy Wspomagania w Inżynierii Produkcji; 2017, 6, 6; 209-221
2391-9361
Pojawia się w:: Systemy Wspomagania w Inżynierii Produkcji
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Wyświetlacze ciekłokrystaliczne w środkach transportu samochodowego i lotnictwie
Liquid crystal displays in the vehicle transportation and aviation
Autorzy:: Różański, S. A.
Powiązania:: https://bibliotekanauki.pl/articles/313906.pdf
Data publikacji:: 2018
Wydawca:: Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:: wyświetlacz ciekłokrystaliczny
środki transportu samochodowego
deska rozdzielcza
lotnictwo
kokpity lotnicze
kontrola i monitorowanie
liquid crystal display
means of motor transport
dashboard
aircraft
airline cockpits
control and monitoring
Opis:: W artykule przedstawiono podstawowe własności ciekłych kryształów ze szczególnym uwzględnieniem ich wykorzystania przy konstrukcji wyświetlaczy ciekłokrystalicznych. Omówiono podstawowe własności wyświetlaczy ciekłokrystalicznych, ich strukturę i zasadę działania. Na wybranych przykładach wykazano korzyści jakie płyną z zastosowania wyświetlaczy ciekłokrystalicznych w środkach transportu samochodowego i lotnictwie.
The article presents the basic properties of liquid crystals with particular emphasis on their use in the construction of liquid crystal displays. The basic properties of liquid crystal displays, their structure and principle of operation are discussed. The selected examples show the benefits of using liquid crystal displays in vehicle transportation and aviation.
Źródło:: Autobusy : technika, eksploatacja, systemy transportowe; 2018, 19, 6; 691-697, CD
1509-5878
2450-7725
Pojawia się w:: Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Use of remotely piloted aircraft systems to evaluate the effects of transport collision
Autorzy:: Romańska, H.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/196889.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: transport
RPAS
search and rescue
crisis management
remotely piloted aircraft systems
poszukiwanie i ratowanie
zarządzanie kryzysowe
Opis:: The evaluation of the effects of transport collision often takes the form of ground reconnaissance. Undoubtedly, remotely piloted aircraft systems (RPAS) can support and help the police, firefighters, security agents and paramedics in the event of a transport collision. Although there is a scarce amount of literature concerning the use of RPAS in crisis management, it is important to pay more attention to the benefits of this technology. The article describes the danger of collisions, as well as discusses the possibility of using RPAS, their functionality and potential utility. Sensors installed on RPAS can rapidly identify the place of the accident, the number of casualties, the type of damaged vehicles or the type of contamination.
Źródło:: Zeszyty Naukowe. Transport / Politechnika Śląska; 2017, 94; 199-210
0209-3324
2450-1549
Pojawia się w:: Zeszyty Naukowe. Transport / Politechnika Śląska
Dostawca treści:: Biblioteka Nauki

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