Autor: Skorupka, Z. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Magnetoreological fluids as method for active controlling of landing gear shock absorber characteristic
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/213110.pdf
Data publikacji:: 2010
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: silniki i paliwa lotnicze
aerodynamika i mechanika lotu
materiałoznawstwo
aircraft engines and fuels
aerodynamics and mechanics of flight
materials science
Opis:: Smart materials are being used in much larger scale in mechanical solutions. Aviation usage of these materials seems to be natural because of interest in new technologies use in this industry. In this article authors discuss characteristics of magnetoreological fluids as a smart materials, examples of its industrial usage, requirements on landing gear characteristics, design and laboratory tests of model shock absorber in which MRF was used as damping fluid.
Materiały inteligentne (ang. smart materials) znajdują coraz większe zastosowanie w konstrukcjach inżynierskich. Wykorzystanie ich w lotnictwie jako jednej z najbardziej nastawionej na nowoczesne rozwiązania gałęzi inżynierii jest jak najbardziej naturalne. Praca zawiera krótką charakterystykę cieczy magnetoreologicznej jako materiału inteligentnego, wymagania stawiane podwoziom lotniczym, opis konstrukcji oraz badań modelowego amortyzatora wykorzystującego MRF jako czynnik roboczy .
Źródło:: Prace Instytutu Lotnictwa; 2010, 5 (207); 48-56
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: FEM temperature evaluation of model braking test in comparison to selected laboratory test
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/247287.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
air transport
simulation
friction materials
model braking
Opis:: Friction pair tests or model brake tests are one of the trials done in order to evaluate friction pair materials usefulness in full-scale brakes. Such tests are both time consuming and expensive, so most of the manufacturers want to reduce them as much as possible by using numerical simulations for both time and costs savings. It is not possible to eliminate laboratory tests entirely because of the safety regulations requirements. Without regulatory compliance, no brake material can be used in consumer products such as cars or airplanes. Nowadays most of the FEM programs are capable of simulate braking (friction) process in many of its aspects. Accuracy of calculations varies according to complexity of the model and phenomena taken into account. One of the interesting aspects of braking is the friction temperature generation especially due to its destructive impact on the vehicle brakes. Laboratory evaluation of the temperature can be performed in limited spectrum because of inaccessibility of the friction area. FEM calculations can help to determine temperature changes and temperature value during process. It also helps to determine temperature induced damaging conditions for the friction material or the whole brake design. In this paper author compares FEM of friction temperature calculations and laboratory test performed in Landing Gear Laboratory of Institute of Aviation in Warsaw where author works on daily basis. FEM simulation was created in order to resemble mentioned friction material test and to create model of the geometry of the tested material including test stand parts. All of the calculations were performed using COMSOL MULTIPHISICS software.
Źródło:: Journal of KONES; 2015, 22, 3; 213-219
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Wear in friction brakes Wear in friction brakes
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/243767.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: wear
wear testing
brakes
friction pair
friction material tests
full-scale brake tests
Opis:: Parameters of friction systems decline in time by the process of wear. In friction brakes, the wear phenomenon is much more visible than in other friction systems. Wear itself is on one hand not desirable because of need for brake system parts replacement but sometimes is needed due to regeneration of the friction area which is damaged for example by temperature or aggressive ambient conditions. Wear can be fatal or catastrophic for the friction brake, leading to heavy damage or even to permanent loss of braking capability during operation. As the brake is one of the crucial safety systems in both aviation and road vehicles, it is necessary to know if and how wear will be present in friction brake system before the brake is allowed to be installed in the vehicle, especially one that carries people. Wear can be estimated via numerical methods for well-known brakes (i.e. materials) or it has to be tested using laboratory methods in order to check and prove or deny initial design assumptions. In this paper, the author describes the phenomenon of friction brake wear and laboratory-testing methods of friction materials wear using brake model test stand for aviation brake friction materials certification testing located in Institute of Aviation Landing Gear Laboratory. Author also presents sample data from aviation brakes materials testing in order to show how wear can affect friction brake performance and durability.
Źródło:: Journal of KONES; 2016, 23, 2; 325-332
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Laboratory tests of stand-alone hydraulic piezo-valve
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/244697.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: laboratory testing
hydraulic valve
flow control
piezo crystal
Opis:: Flow control inside the aviation landing gear shock absorbers is nowadays performed by fixed orifices or by the half-active spring based valves located inside of the device. All of the mentioned solutions are optimized on limited, mostly to one, landing scenarios due to their non-adjustable nature (even spring based valves are treated as passive due to their lack of actual real-time controllability). The easiest way of full hydraulic fluid flow control is to mount in its way a valve, which is able to seamlessly open and close causing the flow to change in wide range. Unfortunately, most of the used solutions are too large or not fast enough to fit the shock absorber requirements. The most promising way is to design tailor-made valve based on a piezo crystal actuator, which is most suitable due to its size and speed. Such a design has been made and tested by the engineers of the Institute of Aviation in Warsaw in Landing Gear Laboratory. In this article, the author describes test campaign of the hydraulic piezo-valve. Several tests have been made in order to assess the design correctness and to determine the basic parameters of the valve. Achieved results, presented in this article, show the full functionality of the solution in laboratory tests according to the design assumptions [8].
Źródło:: Journal of KONES; 2018, 25, 4; 385-381
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: ABS system use impact on braking torque in aviation brake
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/245882.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
motor vehicle
brake
brake design
brake tests
ABS tests
Anti-Lock system
Opis:: ABS (Anti-Locking) systems improve performance and safety of the braking systems. Use of ABS is now factory standard in both commercial and military aviation. ABS system in its origin was designed in order to prevent wheels from slipping and locking on the low friction surfaces such as ice. By preventing wheel, locking ABS system helps in not losing control over the vehicle during difficult braking conditions. In Aviation ABS, systems were introduced quite early as mechanical systems but their common usage is connected with computer and electronic systems development in 1970’s. In aircraft, ABS systems are responsible for safety of braking by preventing phenomena described above and for preventing landing with engaged brakes what is common in military and in big commercial aviation. In modern aviation ABS systems use is both safety and economical feature resulting in visible profits during airplane lifetime. Other question is efficiency of the process i.e. braking torque value. Braking torque is the most important parameter of brake from exploitation point of view. It is directly connected with braking distance as well with amount of force needed to achieve assumed braking parameters for the mechanical vehicle. Stability of braking torque is important in order to get optimized characteristics of the braking process itself. Most of the brake characteristics and efficiency calculations were based on assumption that braking torque should be stable during braking process. In this paper author would like to investigate ABS use impact on braking torque, which by definition is not stable in anti-lock equipped systems. Author will base on literature sources as well as on results of laboratory tests made during development of ABS system for 2700 kg take off mass airplane made in Landing Gear Laboratory of Warsaw Institute of Aviation in which author works on daily basis.
Źródło:: Journal of KONES; 2014, 21, 1; 259-265
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Adaptive landing gear control system assumptions
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/247705.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: laboratory testing
landing gear
adaptive control
control system
Opis:: In the present time, landing energy dissipation process in aviation shock absorber design is optimized for the most demanding, but still safe, landing scenario (reserve energy landing conditions). Most of the current solutions are based on a fixed hole (orifice) or a set of holes regulating hydraulic fluid flow in the shock absorber. This approach although safe provides no optimization of the forces acting on the fuselage in different (less energetic than limit energy) conditions. Due to the progress in hydraulic flow control, it is possible to design and control a proper system for extended optimization of the landing process energy dissipation. The complete system contains two parts, one of which is a direct flow executive electro-mechanical system and second of which is an electronic control system. The electronic control system directly manages executive system via a set of inputs, thus creating proper output signals for the optimal flow control. In this article, the author presents the idea of the computer control part of the adaptive hydraulic flow control system. The author describes a set of possible control input and output signals both external and internal, from the landing gear reference system, characterizing their role in the landing process. The author also defines possible control algorithms selected to fit the assumptions of the adaptive landing gear system. Finally, the author presents a proposal for the laboratory grade control system for future testing of the assumptions described in this article.
Źródło:: Journal of KONES; 2018, 25, 2; 329-333
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Braking moment comparison and analysis for various brake designs using results from sample and full scale friction material tests
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/242444.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
motor vehicle
brake
brake design
brake tests
full scale tests
model tests
friction material
Opis:: Brake is one of the most important safety feature in every mechanical vehicle from bikes to airplanes. Brakes have to be designed in order to meet safety, reliability, efficiency and economical requirements. One has to remember that not only design of brake is important but also friction material used in its construction. Without proper materials, brakes are not able to generate proper braking moment. Braking moment is the most important parameter of brake from operation point of view. It is directly connected to braking distance as well with amount of force needed to achieve assumed braking parameters for the mechanical vehicle. Stability of braking moment is important in order to get optimized characteristics of the braking process itself. Most of the brake characteristics and efficiency calculations base on assumption that braking moment should be stable during braking process. During years of tests made on full scale brakes and friction material sample tests, author observed that real braking moment curve is not stable during braking process. This phenomenon is likely to affect braking efficiency and in result slightly change braking distance. In this paper author would like to address this issue by showing brake moment curves made for different brakes and friction materials. Tests, which were author’s base for paper contents, were made using full scale brake testing and friction material sample testing. All of the tests described in the paper were performed in Landing Gear Laboratory of Warsaw Institute of Aviation in which author works on daily basis
Źródło:: Journal of KONES; 2013, 20, 1; 303-308
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Laboratory investigations on landing gear ground reactions (load) measurement
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/243799.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: laboratory-testing
landing gear
load measurement
direct measurement
indirect measurement
Opis:: Ground reaction measurement in landing gear laboratory tests is used in order to gain knowledge about loads transferred to the aircraft structure. Ground reaction level is defined during aircraft design phase and it is required not to exceed limit value in real construction. Load from landing affect directly strength of aircraft structure especially mounting points what translates both strength of aircraft structure especially mounting points what translates both on safety and weight of the final design. Meeting the safety requirements is crucial in aviation regulations conformity. Landing gear ground reactions evaluation is performed during laboratory tests in order to meet the compliance with the ground load requirements assumed in design phase. Proper test method is crucial to prove the actual load. One of the methods is landing gear dynamic drop test where landing forces are measured. Force measurement is made in several ways according to test stand construction and test object specifics. In this article, three methods are described due to author’s experience in landing gear tests. Proposed techniques cover two direct and one indirect force measurements. Direct approach is based on strain gauge measurement principle. One is a strain gauge plate fixed to the ground while the second one is based on strain gauges attached to landing gear mounting nodes. Indirect approach is based on the acceleration of the tested object, which by definition is correlated with the force applied to the structure. Obtained test results allow determining the kinetic energy absorbed by landing gear during drop test. In this article author also presented numerical integration of the time history data and compared them with simulation results in order to show equivalence of all three of the test methods and to prove correctness of the test initial conditions determination.
Źródło:: Journal of KONES; 2017, 24, 2; 225-230
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Wybrane zagadnienia konstrukcji podwozia płozowego przeznaczonego do wiropłatowej platformy uzytkowej ILX-27
Selected issues of ILX-27 rotorcraft landing gear design
Autorzy:: Skorupka, Z.
Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/212267.pdf
Data publikacji:: 2013
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: problematyka konstrukcji wiropłatów
konstrukcja podwozia płozowego
wiropłatowa platforma uzytkowa ILX-27
problems of rotorcraft design
ILX-27 rotorcraft
landing gear design
Opis:: Podwozia wiropłatowych statków powietrznych muszą spełnić szereg zadań stawianych przez warunki operacyjno/użytkowe przewidziane w założeniach eksploatacyjnych. Podwozie płozowe dzięki swojej odporności mechanicznej, możliwościom użytkowym oraz stosunkowo niewysokim kosztom budowy i eksploatacji, jest najbardziej rozpowszechnionym typem podwozia stosowanego w wiropłatach, w odniesieniu do równoważnych podwozi innych typów. W przypadku wiropłatów operujących w trudnych warunkach terenowych podwozie takie jest jedynym rozwiązaniem konstrukcyjnym pozwalającym na wykonanie stawianych przed nimi zadań. Podwozie płozowe pomimo pozornego nieskomplikowania, wymaga od konstruktorów dogłębnej wiedzy inżynierskiej w celu osiągnięcia zakładanego efektu w postaci bezpiecznego produktu, chroniącego nie tylko samą konstrukcję a także przewożoną aparaturę a co najważniejsze ludzi znajdujących się na pokładzie. W artykule autorzy pokażą złożoność zagadnień związanych z konstrukcją podwozia płozowego na przykładzie konstrukcji wykonanej na potrzeby projektu „Bezzałogowy śmigłowiec – robot do zadań specjalnych” realizowanego w Instytucie Lotnictwa we współpracy z Instytutem Technicznym Wojsk Lotniczych oraz WZL-1.
Aircraft landing gear is one of essential functional system of the aircraft without which it would be impossible to use one. Landing gears can be in built in different forms in order to meet design assumptions. Helicopters are the aircrafts requiring specific functionality from the landing gears what requires different design approach. Skid landing gear used for described project was designed and optimized in order to withstand difficult operation conditions expected for unmanned helicopter. In this article there is a number of the design issues described using as an example ILX-27 UAV as reference for modern design of skid type landing gear.
Źródło:: Prace Instytutu Lotnictwa; 2013, 5-6 (232-233); 26-33
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Strain gauge pin based force measurement
Autorzy:: Skorupka, Z.
Sobieszek, A.
Powiązania:: https://bibliotekanauki.pl/articles/247743.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: strain gauges
landing gear
test stand
measuring system
Opis:: In this article authors present force measurement method based on strain gauge measuring system installed inside pin, which is a part of light helicopter Main Landing Gear Shock Absorber. Strain gauges in full bridge configuration were installed inside the mounting pin (upper one – fuselage side). Placement and type of strain gauges were selected during the preliminary tests, which verified the validity and conditions of the force measurement. Preliminary tests allowed verification and selection of an optimal measurement system by testing two types of them. The impact on force according to the angle of force vector direction was also verified. Preliminary tests of the strain gauges equipped pin were performed using quasistatic tests stand – 40 T hydraulic press for applying force acting on shock absorber and pin. Whole measuring system is planned to be used in real time analysis of shock absorber force acting on fuselage mounting node. The strain gauges allows measurement of force in any place of the structure, the article presents the advantages of the system located inside pin. Additionally, the installation technologies of strain gauges in hard-to-reach places are presented. The article is summed up with an analysis of the problems, which arise during the installation and measurement process using strain gauges installed in such a specific place.
Źródło:: Journal of KONES; 2018, 25, 2; 335-340
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: A finite element model development as a part of process of energy absorption material selection
Autorzy:: Jakubowski, R.
Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/244612.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: RASTAS Spear
material
energy absorption
finite element model
LS-DYNA
Opis:: The Warsaw Institute of Aviation major role in the RASTAS Spear project was to design an energy absorption system for the space probe lander. As the system was meant to be unmanned, the main requirement was to use no active solutions like parachute or rocket propulsion (less complexity in application and thus more reliability). A group of various materials was chosen to be tested. Tests campaign was divided into three stages: static compression tests, low speed dynamic tests and high speed dynamic tests. The high-speed dynamic tests were divided into two substages. In the first one simple cube specimens were tested to obtain data necessary for second substage in which full-scale object was tested. Having valuable data from experiments, numerical simulations in LS-DYNA software were carried out and then the results were compared. Based on experimental data several iterations during finite element model developing process were made. That process allowed setting up properly simulation by changing and adjusting properties such: material models, contact types, element formulation and other important constants. The finite element simulation results showed a good correlation with experimental data. The knowledge gained from numerical model optimization in connection with experimental data allowed for creating faster and more accurate energy absorbing material selection methodology. This methodology was successfully used in subsequent projects in which Institute of Aviation took part and also can be used in other future applications.
Źródło:: Journal of KONES; 2016, 23, 3; 217-223
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Wind power plants : types, design and operation principles
Autorzy:: Tywoniuk, A.
Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/244681.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: wind energy
wind power plants
energy conversion
renewable energy
Opis:: Many countries worldwide support green energy production on large scale mostly by solar or wind energy subsidizing manufacture and operation of such systems. During the last two decades, there has been significant increase in wind energy production globally. Statistics show continuously growing investments in the development and installation of wind turbines and farms. Currently, wind energy is the second most important source of renewable energy after water energy. By 2016 global cumulative installed wind capacity surpassed 432 k MW [GWEC]. In last several years, most dynamic growth in wind power generation investments was recorded in Asia. Europe, in comparison, has less impressive but steady growth in wind power plants through the years. In this article, authors present global demand on energy in comparison to efficiency of wind power plants in relation to the local and global location as well as to the scale of installed system. Authors also present statistical data concerning wind power plants development. General classification, using number of criteria (ex. power output, construction size, rotor axis orientation and other) of wind to electric power converting devices is presented. Various types of devices, which authors describe in this article, can perform conversion of wind blow energy to the electric energy using different yet similar methods.
Źródło:: Journal of KONES; 2018, 25, 3; 479-487
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Strain gauge measuring plate for dynamic tests
Autorzy:: Sobieszek, A.
Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/949513.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: dynamic tests
strain gauges
measuring plate
test stand
Opis:: In dynamic tests, especially landing gears, it is necessary to measure and record load levels. In this article, authors present measurement methods used in the landing gear tests on the 10-Ton Drop Test Machine, which is capable of simulating conditions similar to real landing in landing energy dissipation tests. Possible test objects include dampers, shock absorbers, and crash structures and devices. In described case load measurement can be done by several methods where one of them is strain-gauge plate based load measurement. This type of measurement is weighting system under the test object where all forces acting on it are measured. Strain gauge plate is usually tailormade measurement system, which is composed out of mechanical device (plate itself) equipped with strain gauge force sensors, strain gauge amplification system and recording system. In addition, differences between static and dynamic measurements are described as well as influence of dynamic test conditions on strain gauges behaviour. In the article, authors describe general layout of the system, advantages and disadvantages of the test stand and problems that may appear during measuring. Authors also emphasize how the accuracy of the design affects to the quality of measurement. At the end of the article, advantages and disadvantages of the test stand and problems that may appear during measuring are described.
Źródło:: Journal of KONES; 2018, 25, 4; 399-404
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Wybrane zagadnienia konstrukcji podwozia do wiatrakowca I28
Selected issues of 128 gyroplane landing gear design
Autorzy:: Skorupka, Z.
Tywoniuk, A.
Powiązania:: https://bibliotekanauki.pl/articles/213936.pdf
Data publikacji:: 2013
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: problematyka konstrukcji wiropłatów
konstrukcja podwozia do wiatrakowca 128
problems of rotorcraft design
landing gear design of gyroplane 128
Opis:: Podwozia lotnicze są jednym z podstawowych układów funkcjonalnych statków powietrznych, bez którego niemożliwe byłoby ich użytkowanie. Mogą przybierać różne formy w zależności od przyjętych parametrów. Wiropłatowe statki powietrzne wymagają specyficznej funkcjonalności podwozi, którą autorzy postarają się przedstawić na przykładzie podwozia do obiektu typu wiatrakowiec. Wiatrakowiec jest szczególnym rodzajem wiropłatu, który zyskuje na popularności dzięki nieskomplikowanej budowie i obsłudze przy okazji łącząc w sobie zalety samolotu i śmigłowca. Dla inżynierów skonstruowanie tego typu pojazdu jest sporym wyzwaniem ze względu na konieczność połączenia niezawodnej, prostej i taniej konstrukcji z wyśrubowanymi normami bezpieczeństwa statków powietrznych. Spełnienie wymagań certyfikacji jest trudne szczególnie w przypadku wprowadzania do projektu własnych niestosowanych wcześniej rozwiązań. Doświadczenie kadry inżynierskiej Pracowni Podwozi Instytutu Lotnictwa, pozwoliło na zaprojektowanie podwozia mieszczącego się w granicach założonych przez projekt, a przy okazji przyczyniło się do stworzenia unikalnych rozwiązań konstrukcyjnych.
Aircraft landing gear is one of essential functional system of the aircraft without which it would be impossible to use one. Landing gears can be in built in different forms in order to meet design assumptions. Rotorcrafts are the aircrafts requiring specific functionality from the landing gears which will be described in this article using I28 gyroplane as an example.
Źródło:: Prace Instytutu Lotnictwa; 2013, 5-6 (232-233); 34-40
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Analiza systemów ABS w pojazdach mechanicznych
ABS systems analysis in motor vehicles
Autorzy:: Paprzycki, I.
Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/249844.pdf
Data publikacji:: 2013
Wydawca:: Instytut Naukowo-Wydawniczy TTS
Tematy:: ABS
ESP
hamowanie pojazdów
vehicle braking
Opis:: W artykule przedstawiono genezę powstania, koncepcje i założenia projektowe systemów ABS stosowanych w pojazdach mechanicznych. Pierwszy projekt systemu kontroli poślizgu wytworzony na potrzeby statków powietrznych zakładał realizację techniki hamowania pulsacyjnego, stosowanego przez kierowców rajdowych. Technika ta jest praktycznie niemożliwa do wykonania przez pilota samolotu. Konieczne, zatem było zaprojektowanie układu elektromechanicznego realizującego powyższe zadanie. Artykuł zawiera opis rozwiązań inżynierskich zastosowanych w systemach kontroli poślizgu z uwzględnieniem możliwości technicznych sprzed ponad 80 lat jak i współczesnych. Autorzy opisują pierwotne założenia systemu powstałego po raz pierwszy na potrzeby lotnictwa oraz obecnych systemów stosowanych niemalże, jako standardowe wyposażenie nowo produkowanych aut osobowych. W dalszej części skupiono się na rozwoju systemów ABS w oparciu o nowatorskie rozwiązania z dziedziny zarówno elektroniki, hydrauliki oraz systemów mechatronicznych.
This paper present the concepts and conceptual design of the ABS system used in motor vehicles. First ABS system was design for aircraft use where threshold braking is nearly impossible. It was necessary to design a system that automatically lower the hydraulic pressure and release the brakes. This article includes a description of over 80 years old and modern engineering solutions. It calls the first anti - lock braking system project assumptions for the aircraft use. It also describes the assumptions of modern system, that is installed in all new commercial and passenger vehicles. The next part of this paper focusses on the innovative systems that leverage electronics, hydraulics and mechatronics solutions.
Źródło:: TTS Technika Transportu Szynowego; 2013, 10; 1143-1154, CD
1232-3829
2543-5728
Pojawia się w:: TTS Technika Transportu Szynowego
Dostawca treści:: Biblioteka Nauki

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