Temat: take-off - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Impact of opening time of the take-off pneumatic launcher main valve on take-off pressure losses
Autorzy:: Jastrzębski, G.
Powiązania:: https://bibliotekanauki.pl/articles/243547.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: take-off launcher
pneumatic take-off systems
pressure losses
Opis:: This publication presents UAV rope and pneumatic launchers constructed and operated in the Air Force Institute of Technology. The construction and operating principle were presented, and functional properties of the UAV take-off pneumatic launcher were characterised. Furthermore, a detailed diagram of the take-off pneumatic launcher was shown, and an operating principle of the launcher take-off system and pneumatic control of the take-off procedure were discussed. The operation parameters of the most important operational elements (main ball valve, semi-rotary actuator, pneumatic valves controlling the flow) from the launcher pneumatic system were specified. On the basis of data sheets of pneumatic elements, a calculation model of the mass flow (volumetric flow rate) of compressed air flowing through the main valve (ball valve in the take-off cylinder supply line) of the take-off pneumatic launcher was designed. The possible cracks, through which compressed air leaks and the take-off cylinder dead sections during the main valve opening and shot, were characterised and discussed. The calculation model designed for individual leaks and total compressed air leaks in the take-off line of the pneumatic launcher was presented. Based on the mass flow model (volumetric flow rate) of compressed air flowing through the main valve, and total compressed air leaks, the relationship of compressed air energy losses depending on opening time of the main valve of the take-off pneumatic launcher was determined. In the paper, the results of simulation studies for the times shorter than data sheets of the main valve opening were presented. In addition, the change of the compressed air disposable energy losses was defined. Based on the results of simulation studies, the opening time of the take-off launcher main valve for the acceptable disposable energy loss level of the take-off pneumatic launcher was specified.
Źródło:: Journal of KONES; 2016, 23, 4; 175-182
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Evaluation of the required ground power of a ground - based system for support of the aircraft safe take - off and landing
Autorzy:: Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/242165.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
take-off and landing
magnetic levitation
Opis:: Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation to aid the take-off and landing of the transport aircraft. The use of the aiding system will bring a lot of benefits, however, regarding its innovative character and the problems connected with it, the idea can have been realized in a couple of years or even decades. The aim of this work was to carry out the analysis of the change to the required thrust of the transport aircraft in the take-off, landing and cruise using the system of magnetic levitation. Magnetic levitation or magnetic suspension is a method by which a body floats due to a special quality of magnets. The generated electromagnetic force is used to balance the weight of the object. The current work describes the ways of determining the weights of the main systems of the aircraft with classical construction solutions where the weight of the whole aircraft is estimated on the basis of the statistical methods. It allows determining the weights of all main systems of the aircraft and verifying the results using the known examples. Thanks to this approach, it could be possible to determine the modified aircraft weight more thoroughly, adding the changes in weights of the modified systems.
Źródło:: Journal of KONES; 2012, 19, 4; 411-418
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Methods for determining the take-off speed of launchers for unmanned aerial vehicles
Autorzy:: Jastrzębski, G.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/243050.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aviation
unmanned aerial vehicle
take-off launcher
take-off speed
acceleration recorder
lotnictwo
bezzałogowy statek powietrzny
prędkość startu
rejestrator przyspieszenia
Opis:: Unmanned aerial vehicles (UAV) are currently a very rapidly developing type of aviation. The problem of support during the take-off with the use of, i.e. take-off launchers arose along with their development, especially for UAVs with weights and dimensions preventing manual take-off. One of the major issues associated with UAV take-off launchers is for its UAV accelerating element to obtain its initial speed. The article presents three methods of determining launcher take-off speeds for unmanned aerial vehicles, i.e. the concentrated very oblique projection method, the high-speed camera methods, and the acceleration recorder method. The take-off launcher carriage speed in the oblique projection method is determined from a formula. This method involves “ejections” of concentrated masses from the UAV mass range and measuring the component values resulting from the used formula, which contains the range of the oblique projection, the elevation of the projection and its angle. The method using the high-speed camera involves recording the course of ejections of the concentrated mass from the launcher. The average take-off speed is determined on the basis of a take-off run length (section of the launcher race, where the unit accelerates) and defining the start and end frame of the carriage movement. The third method for the determination of the take-off speed utilizes an acceleration recorder. The method with the recorder involves registering a change in the accelerations when the take-off carriage is being accelerated by a system fixed on the carriage or the accelerated object. The article presents the methodology of dynamic tests of object acceleration on a launcher, necessary for the determination of speed with the mentioned methods. Selected results from actual tests with the use of the 01/WS/2015 launcher, which is an element of the ZOCP JET2 set, were presented. The test results are presented in a tabular form. The methods for the determination of the take-off speed were compared on the basis of performed tests. Based on the obtained results, the factors impacting the accuracy of each of the methods were identified.
Źródło:: Journal of KONES; 2018, 25, 1; 170-176
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: National policy and big-push theory of development in Nigeria: moving away from low-level economic equilibrium
Autorzy:: Umoru, D.
Onimavo, J. A.
Powiązania:: https://bibliotekanauki.pl/articles/321703.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: development
infrastructure
Nigeria
big-push
take-off
rozwój
infrastruktura
Opis:: The paper analyzes the policy implications of the big-push model for development in Nigeria. The highlights of the analysis include existence of three inter-related perceptions namely, poverty trap, big push (BP) and takeoff. The basic idea is that poor countries are in poverty, hence needs BP linking amplified investment, leading to takeoff in national income and development. This indeed rationalizes necessity for overseas aid. In effect, minimum infrastructure and educational resources be apportioned to development programme to achieve success. However, nations that have implemented coordinated investment programs can achieve industrialization of each sector and thus be able push forward sequence of development.
Źródło:: Zeszyty Naukowe. Organizacja i Zarządzanie / Politechnika Śląska; 2018, 116; 177-187
1641-3466
Pojawia się w:: Zeszyty Naukowe. Organizacja i Zarządzanie / Politechnika Śląska
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Optimal configurations of wave energy converter arrays with a floating body
Autorzy:: Zhang, W.
Liu, H.
Zhang, X.
Zhang, L.
Ashraf, M. A.
Powiązania:: https://bibliotekanauki.pl/articles/260084.pdf
Data publikacji:: 2016
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: wave energy
cylinder array
power take-off
hydrodynamic analysis
Opis:: An array of floating point-absorbing wave energy converters (WECs) is usually employed for extracting efficiently ocean wave energy. For deep water environment, it is more feasible and convenient to connect the absorbers array with a floating body, such as a semi-submersible bottom-moored disk, whose function is to act as the virtual seabed. In the present work, an array of identical floating symmetrically distributed cylinders in a coaxial moored disk as a wave energy device is proposed The power take-off (PTO) system in the wave energy device is assumed to be composed of a linear/nonlinear damper activated by the buoys heaving motion. Hydrodynamic analysis of the examined floating system is implemented in frequency domain. Hydrodynamic interferences between the oscillating bodies are accounted for in the corresponding coupled equations. The array layouts under the constraint of the disk, incidence wave directions, separating distance between the absorbers and the PTO damping are considered to optimize this kind of WECs. Numerical results with regular waves are presented and discussed for the axisymmetric system utilizing heave mode with these interaction factors, in terms of a specific numbers of cylinders and expected power production.
Źródło:: Polish Maritime Research; 2016, S 1; 71-77
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Starty i lądowania na ograniczonej wielkości lądowiska po awarii napędu
Take-off and landing on a limited size landing ground following a power failure
Autorzy:: Głaz, M.
Powiązania:: https://bibliotekanauki.pl/articles/212496.pdf
Data publikacji:: 2006
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: start
lądowanie
lądowisko
awarie napędu
take-off
landing
power failure
Opis:: Obiektem badań jest śmigłowiec Mi-2 plus, dla którego należy opracować technikę sterowania po awarii napędu w czasie wykonywania "pionowych " startów i lądowań na krótkich lądowiskach. Do punktów krytycznych, które należy przeanalizować w badaniach techniki wykonania startów i lądowań na ograniczonym lądowisku należą, przede wszystkim, problem przelotu przez pierścień wirowy oraz problem występowania strefy H-V. Należy wziąć także pod uwagę występowanie przeszkód na terenie lądowiska (zakłada się wysokość przeszkód do około 20 m). W opracowaniu zostały zamieszczone symulacje obliczeniowe sterownia śmigłowcem Mi-2 plus po awarii silnika (dla różnych wysokości wystąpienia awarii). Przedstawiono sposób sterownia pochyleniem kadłuba oraz wartością kąta skoku ogólnego pozwalający na uzyskanie określonych trajektorii lotu. Zamieszczono również niektóre wyniki z prób w locie przeprowadzonych w PZL Świdnik S.A. Na podstawie przeprowadzonych symulacji i badań lotnych stwierdzono, iż istnieje możliwość bezpiecznego wykonania manewrów "pionowych " startów i lądowań.
The object of the tests is the Mi-2 Plus helicopter, for which a method of controlling the helicopter after a power failure during vertical take-off and landing on short landing ground should be designed. The problems of flight through the vortex ring and occurrence of the H-V zone belong to the critical points, which should be analyzed in tests of the method of take-off and landing on a short landing ground. The occurrence of obstacles on the area of the landing ground should also be taken into account (the height of the obstacles is assumed to be up to around 20m). In the development of the tests, numerical simulations of controlling the Mi-2 Plus helicopter after engine failure (for varying height at which the failure took place) were included. A method of control through the inclination of the fuselage as well as the value of the rotor tilt angle, which allows for certain flight trajectories to be obtained, was introduced. Included also were certain results from flight tests carried out at PZL Świdnik S.A. On the basis of the simulations performed and flight tests, it was decided that there exists a possibility of safely performing "vertical" take-off and landing manoeuvres.
Źródło:: Prace Instytutu Lotnictwa; 2006, 1-2 (184-185); 119-122
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Minimum emission unconventional MAGLEV assisted take-off
Autorzy:: Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/246124.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
green trajectory
take-off
aircraft emission
magnetic levitation
Opis:: Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation (MAGLEV) to aid the take-off and landing of the transport aircraft. The “Integrated Ground and on-Board system for Support of the Aircraft Safe Take-off and Landing” – GABRIEL, deals with radically new integration of the MAGLEV technology into the air transportation system that contains aircraft, airport, air traffic control, authority, logistic and operational support, maintenance, etc. GABRIEL idea includes operation of the aircraft without the conventional undercarriage system and using the ground based power and supporting systems for take-offs and landings. In case of using the GABRIEL system as a catapult, the aircraft on the track must be accelerated to the speed permitting to reach the altitude of 300 m or more. Such take-off and climb results in minimum noise and minimal emission of substances harmful for the environment. After reaching the altitude of 300 m, the aircraft may follow its flight with using different flight strategies. Different conditions of the unconventional take-off needs to shape other way the trajectory of the initial stage of the aircraft flight after the lift-off. The aim of the present work was to determine the optimal conditions of the lift-off and the optimal trajectory of the initial climb minimizing the emission. Simplified realization of the Ritz- Galerkin method was used in this work, which uses an approximate solution to boundary value problems for determining the optimal flight trajectory.
Źródło:: Journal of KONES; 2014, 21, 4; 335-342
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: A conception of vertical take-off air vehicle with self-aligning moving wings
Autorzy:: Lichoń, D.
Powiązania:: https://bibliotekanauki.pl/articles/242818.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: vertical take-off
air vehicle conception
self-aligning wings
flapping wings
Opis:: The possibility of vertical take-off of an aircraft is a valuable feature in air transport. It allows to increase operational characteristics of an air vehicle and requires less field and low cost ground infrastructure. Currently the vertical take-off feature is practically reserved to helicopters and tilt-rotor aircrafts. Both types of air vehicles have their advantages and also have some important limitations. Regarding the helicopters their construction provides natural vertical take-off features and makes them useful in low altitude flight tasks. However the power required for flight and main rotor kinematics results in low cruising speed and short range performance. The tilt-rotor aircraft is an answer which provides good cruise characteristics saving the vertical take-off feature. The construction of tiltrotor aircraft consists of rotors with adjustable position of tip-path plane. The main technical problem of tilt-rotors is necessity of change aerodynamic configuration from vertical mode to cruise mode at low flight altitude and very low flight speed. A proposed conception of a vertical take-off air vehicle using self-aligning moving wings is focused on producing aerodynamic force always on wings without participation of rotors or propellers. The self-aligning or semirotating wing movement enables to produce aerodynamic force in each flight speed. During take-off lift force is generated by means of power unit driving the wings. The transition from hovering to progressive flight is a smooth phase without aerodynamic configuration changes. It occur as a result of change in wing kinematics or gravity center position. As the flight speed increases the lift force is generated like in classic airplane wing and the power unit load decreases. The conception of presented air vehicle assume to join best features of airplanes and helicopters i.e. vertical take-off, good flight performances and lack of strict border between both phases of flight.
Źródło:: Journal of KONES; 2014, 21, 4; 311-317
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Methods of mathematical modeling of the take-off operation of a commercial aircraft
Metody modelowania matematycznego operacji startu samolotu komunikacyjnego
Autorzy:: Beuth-Jakubowska, K.
Stelmach, A.
Powiązania:: https://bibliotekanauki.pl/articles/374295.pdf
Data publikacji:: 2011
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: modelowanie
lotnisko
samolot komunikacyjny
take-off operation
modeling
airport
aircraft communications
Opis:: While observing the dynamic increase in the intensity of air traffic, the issue of constant controlling and monitoring every individual operation carried out during the flight process becomes a vital matter. One of the most significant operations in this process is the aircraft’s take-off procedure. On the airports such procedures are observed quite frequently, with a rate of several dozen seconds up to few minutes. The correctness of carrying out the mentioned guidelines has a crucial impact on the traffic capacity of the runway, number of operations completed within the area of the airport and, above all, safety of passengers. The research and analysis of these processes cannot, for obvious reasons, be done on objects in real conditions. Therefore, there is a tendency to use IT tools and methods for the purpose of the analysis of the operations which occur in the area of the airport. In order to make use of the computer simulation it is essential to have mathematical models of these operations. The purpose of this article is to create models for particular stages of take-off operation and to identify elementary models of these stages based on parameters recorded by the on board flight recorder. The created mathematical and computer models (for simulation research), reproducing the aircraft’s real operations in the area of the airport, shall be used for automation of the operations conducted in the airport’s area. For the purpose of the analysis comparison of two models has been done to show the effects of conducting mathematical normalization of parameters prior to the analysis.
Obserwując dynamiczny wzrost ruchu lotniczego istotnym staje się zagadnienie ciągłej kontroli i monitorowania poszczególnych operacji wykonywanych podczas procesu przelotu. Jedną z ważniejszych operacji w tym procesie jest operacja startu samolotu. Na lotniskach komunikacyjnych operacje te odbywają się z częstotliwością od kilkudziesięciu sekund do kilku minut. Poprawność wykonywania tych założonych procedur w czasie tej operacji ma istotny wpływ na przepustowość drogi startowej, liczbę operacji wykonywanych w rejonie lotniska a przede wszystkim na bezpieczeństwo pasażerów. Badanie i analiza tych procesów z przyczyn oczywistych nie mogą być wykonywane na obiektach w rzeczywistych warunkach. W związku z tym dąży się do wykorzystania w analizie operacji zachodzących w rejonie lotniska narzędzi i metod komputerowych. Aby wykorzystać możliwości symulacji komputerowej koniecznym jest posiadanie modeli matematycznych tych operacji. Celem artykułu jest zamodelowanie poszczególnych etapów operacji startu a następnie identyfikacja elementarnych modeli tych etapów w oparciu o parametry zarejestrowane przez pokładowy rejestrator parametrów lotu samolotu. Zbudowane modele odwzorowujące rzeczywiste operacje samolotu w rejonie lotniska, będą mógłby być wykorzystane w praktyce lotniczej.
Źródło:: Transport Problems; 2011, 6, 4; 47-59
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Umowy „off take” jako źródło finansowania alternatywnego w projektach geologiczno-górniczych
Off take agreements as a source of alternative financing in geological mining projects
Autorzy:: Kustra, A.
Ranosz, R.
Powiązania:: https://bibliotekanauki.pl/articles/164307.pdf
Data publikacji:: 2015
Wydawca:: Stowarzyszenie Inżynierów i Techników Górnictwa
Tematy:: umowy off take
finansowanie
projekty geologiczno-górnicze
off take contracts
financing
geological-mining project
Opis:: W artykule zaprezentowano umowy off take (odkupu) jako źródło alternatywnego finansowania w branży górniczej. Wskazano przyczyny szybkiego rozwoju umów odkupu w świetle dekoniunktury na rynkach surowców mineralnych oraz problemów wynikających z pozyskania finansowania na nowe projekty geologiczno-górnicze. Jednocześnie wskazano typy umów off take oraz przedstawiono przykłady ich zastosowania w przypadku realizacji działalności w formule project finance w branży górniczej.
This paper presents the ‘off take contracts’ (repurchase agreements) as an alternative form of financing investments in the mining industry. In the paper the reasons for rapid growth of repurchase agreements have been indicated, both in the light of the downturn at the markets of mineral resources, and in the context of problems obtaining financing for new geological-mining projects. The paper indicates the ‚off take contracts’ types and presents the examples of their use in the project finance formula in the mining industry.
Źródło:: Przegląd Górniczy; 2015, 71, 8; 35-39
0033-216X
Pojawia się w:: Przegląd Górniczy
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Zależność strefy startu rakiety od charakterystyki sterującej siły gazodynamicznej
The Dependence of the Launch Zone on the Characteristics of the Controlling Gas-Dynamic Force
Autorzy:: Dziopa, Z.
Powiązania:: https://bibliotekanauki.pl/articles/403448.pdf
Data publikacji:: 2011
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: mechanika
rakieta
lot
sterowanie
strefa startu
mechanics
missile
flight
control
take-off zone
Opis:: Celem pracy jest przedstawienie wpływu charakterystyki sterującego silniczka gazodynamicznego na zakres strefy startu rakiety. W badaniach numerycznych wykorzystany jest model rakiety bliskiego zasięgu samonaprowadzającej się na cel. Rakieta w całym zakresie lotu sterowana jest aerodynamicznie przy wykorzystaniu pary sterów. Naprowadzanie na cel jest możliwe dzięki obrotowi rakiety wokół osi podłużnej. Do korekcji trajektorii lotu tuż po opuszczeniu wyrzutni dodatkowo zastosowane są sterujące silniczki gazodynamiczne. Od charakterystyki ciągu tych silniczków zależy, jak szybko wypracowywany jest przez rakietę właściwy kąt wyprzedzenia. Charakterystyka generowanej przez układ sterowania siły gazodynamicznej wpływa na obszar strefy startu rakiety. Można tak dobrać ciąg silniczków gazodynamicznych, aby rozszerzyć obszar skutecznego strzelania.
The aim of the paper is to present how the controlling characteristics of the small gas-dynamic engine affect the scope of the missile launch zone. The short-range self-targeting missile model was applied in the numerical studies. The missile within the entire scope of the flight is controlled aerodynamically with a pair of rudders. Aiming at a target is possible owing to the missile rotary motion round the longitudinal axis.Additionally, small controlling gas-dynamic engines are applied for correcting the flight trajectory immediately after launching. How fast the missile develops the proper lead angle depends on the characteristics of the small engines thrust. The characteristics of the gas-dynamic force generated by the control system influences the missile launch zone. The way of matching the small gas-dynamic engines thrust may widen the effective shooting zone.
Źródło:: Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa; 2011, 2, 4 (6); 37-46
2081-5891
Pojawia się w:: Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: The influence of ship rolling motion on take-off aerodynamic characteristics of aircraft
Autorzy:: He, Z.
Sun, X.
Gu, X.
Powiązania:: https://bibliotekanauki.pl/articles/259257.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: ship rolling motion
ski-jump take-off
Meshless method
WALE turbulence model
aerodynamic characteristics
Opis:: Ship motion is an important factor affecting on the safety of ski-jump take-off. The simplified frigate ship SFS1 was numerically simulated, and the results were compared with the experimental data, the feasibility of the calculation method was verified; Meshless method and WALE turbulence model were used to simulate the process of aircraft skijump take-off, aerodynamic characteristics under different rolling conditions during the aircraft ski-jump take-off process were presented. The results showed that: the influence of ship rolling motion on lift coefficient, drag coefficient and pitching moment was small, side force and rolling moment were greatly affected by rolling motion; the region of downwash with the maximum speed was about 10 m from the bow; the safety of ski-jump take-off was greatly affected when aircraft was close to the bow within 20 m.
Źródło:: Polish Maritime Research; 2018, S 2; 23-29
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Different defuzzification methods in Guimbal Cabri G2 helicopter takeoff possibility evaluation
Autorzy:: Mendrek, M.
Grzesik, N.
Krzyżak, A.
Kuźma, K.
Powiązania:: https://bibliotekanauki.pl/articles/374121.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: fuzzy logic
fuzzy expert system
helicopter take off
logika rozmyta
regułowe systemy ekspertowe
start helikoptera
Opis:: The article discusses the aerodynamic properties of the Guimbal Cabri G2 helicopter. The main considerations concern the helicopters ascending to the altitude under initial conditions, which were assumed in the project and how the change of the defuzzification method affects the work of the fuzzy controller. The authors analyzed the following: the aircraft, the crew and the payload. The authors assessed the altitude and the minimum time of the helicopter climb. In designing and the work simulation process, the authors used Matlab and Simulink software. A comparison of the influence of selected defuzzification methods on the work of the fuzzy controller was made.
Źródło:: Transport Problems; 2018, 13, 2; 27-38
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Nonlinear PTO effect on performance of vertical axisymmetric wave energy converter using semi-analytical method
Autorzy:: Liu, M.
Liu, H.
Zheng, X.
Chen, H.
Wang, L.
Zhang, L.
Powiązania:: https://bibliotekanauki.pl/articles/258878.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: wave energy converter (WEC)
power take-off (PTO)
capture width ratios
analytical method
eigen function
Opis:: The wave energy, as a clean and non-pollution renewable energy sources, has become a hot research topic at home and abroad and is likely to become a new industry in the future. In this article, to effectively extract and maximize the energy from ocean waves, a vertical axisymmetric wave energy converter (WEC) was presented according to investigating of the advantages and disadvantages of the current WEC. The linear and quadratic equations in frequency-domain for the reactive controlled single-point converter property under regular waves condition are proposed for an efficient power take-off (PTO). A method of damping coefficients, theoretical added mass and exciting force are calculated with the analytical method which is in use of the series expansion of eigen functions. The loads of optimal reactive and resistive, the amplitudes of corresponding oscillation, and the width ratios of energy capture are determined approximately and discussed in numerical results.
Źródło:: Polish Maritime Research; 2017, S 3; 49-57
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Probabilistic model for airport runway safety areas
Autorzy:: Szabo, S.
Vittek, P.
Kraus, J.
Plos, V.
Lališ, A.
Štumper, M.
Vajdova, I.
Powiązania:: https://bibliotekanauki.pl/articles/374515.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: take-off
landing
runway
safety area
probability
distance
start
lądowanie
pas startowy
obszary bezpieczeństwa
prawdopodobieństwo
odległość
Opis:: The Laboratory of Aviation Safety and Security at CTU in Prague has recently started a project aimed at runway protection zones. The probability of exceeding by a certain distance from the runway in common incident/accident scenarios (take-off/landing overrun/veer-off, landing undershoot) is being identified relative to the runway for any airport. As a result, the size and position of safety areas around runways are defined for the chosen probability. The basis for probability calculation is a probabilistic model using statistics from more than 1400 real-world cases where jet airplanes have been involved over the last few decades. Other scientific studies have contributed to understanding the issue and supported the model’s application to different conditions.
Źródło:: Transport Problems; 2017, 12, 2; 89-97
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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