Autor: Balicki, W. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Start-up and acceleration control of the turbine engine with the detonation combustion chamber
Autorzy:: Balicki, W.
Powiązania:: https://bibliotekanauki.pl/articles/247622.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turbine engine
combustion chamber
rotating detonation engine (RDE)
start-up control
Opis:: This article presents the results of tests of helicopter turbine engine, where the classic combustion chamber was replaced with an innovative solution. In this chamber instead of the classic combustion deflagration, was generated a rotating detonation. Theoretical considerations expected to get a higher engine efficiency, because as the thermodynamic Fickett-Jacobs cycle, which can describe the working principle turbine engine detonation chamber, has a higher efficiency than a Brayton cycle, according to which the engines of conventional chamber are working. The appearance of detonation combustion was diagnosed basing on observation of the gas pressure flue in the chamber, using piezoelectric sensors. Before the detonation chamber was used in turbine engine, a series of problems on the various methods of initiation of detonation process and the procedures for controlling the flow rate into the chamber of air and fuel were solved. There was a test stand constructed, which used a helicopter turbine engine GTD-350, wherein the jugs combustion chamber was replaced with detonation chamber. A control system for the flow of fuel in the combustion chamber was developed: aviation kerosene Jet-A1 with addition of hydrogen. With its use obtained unfailing starts of chamber, also the engine running on the idle and on the flight range and accelerations at idle range to flight range. The possibility of the detonation combustion for a long time, especially in transient states - practically limited only by the capacity of fuel tanks – is the achievement of the research team.
Źródło:: Journal of KONES; 2015, 22, 4; 21-27
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Usefulness of the adopted method for the number of aviation occurrences prediction
Autorzy:: Balicki, W.
Glowacki, P.
Powiązania:: https://bibliotekanauki.pl/articles/246325.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
air traffic safety
safety management
aviation occurrence
transport lotniczy
bezpieczeństwo ruchu lotniczego
zarządzanie bezpieczeństwem
wypadki lotnicze
Opis:: Poland – according to ICAO requirements, is obliged to conduct analyses of the coefficients adopted to assess the level of safety in civil aviation. They are carried out on the basis of the data contained in the ECCAIRS database. The authors have processed the data contained in this database by analysing them using various criteria (ICAO aviation occurrence categories, flight phases, different airports) to test the methodology of the safety indicators values forecasting and setting their “warning levels”. Exceedance of these levels could be a signal for taking preventive action by the relevant competent aviation authorities. The proposed method is based on the assumption that the determined parameters are governed by normal distribution rules (Gaussian). Parameter values calculated based on real data from 2016 were compared with those predicted a year earlier. It was found that the factors for different events have increased significantly - above the calculated warning levels, particularly for general aviation. The results of this analysis may support competent aviation authorities' decisions in areas where safety risks are most critical.
Źródło:: Journal of KONES; 2017, 24, 1; 23-29
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Possibilities for limiting aircraft turbine engine abrasive wear of interior duct elements
Możliwości ograniczania erozyjnego zużycia elementów składowych kanałów przepływowych lotniczych silników turbinowych
Autorzy:: Szczeciński, S.
Balicki, W.
Powiązania:: https://bibliotekanauki.pl/articles/213058.pdf
Data publikacji:: 2007
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: elementy składowe kanałów przepływowych
lotnicze silniki turbinowe
aircraft turbine
interior duct elements
Opis:: The paper describes the reasons for ingestion of contaminants into turbine engine interior with inlet air, resulting in lowered efficiency of main engine elements: compressor and turbine and further reduction of engine reliability and lifetime. The direct effect of the aerodrome (landing field) surrounding landscape on the type of contaminants ingested with the turbine engine inlet air and measures used to limit quantity of them are discussed in the paper. The inlet vortex is presented as the fundamental cause for turbine engine ingestion of contaminants from aerodrome surface, and analytic and experimental research methods used in investigation of this phenomena and preventive measures undertaken are also presented in the paper.
W opracowaniu opisano przyczyny przedostawania się zanieczyszczeń do wnętrza silników wraz z powietrzem wlotowym oraz wynikające stąd skutki w postaci zmniejszenia sprawności głównych zespołów: sprężarki i turbiny, a także ograniczenia niezawodności i trwałości silników. Omówiono wpływ bezpośredniego otoczenia lotnisk (lądowisk) na rodzaj zanieczyszczeń i sposoby ograniczania ilości zanieczyszczeń w strumieniu dolotowym silników turbinowych. Przedstawiono wir wlotowy jako podstawową przyczynę zasysania zanieczyszczeń z płyt lotniskowych przez silniki odrzutowe, a także analityczne i eksperymentalne metody badania tego zjawiska oraz sposoby utrudniajace jego powstawanie.
Źródło:: Prace Instytutu Lotnictwa; 2007, 4(191); 3-12
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Vibration of turbine engines as the criterion of production quality of rotor assemblies and their current technical state
Drgania silników turbinowych jako kryterium jakości wytwarzania zespołów wirnikowych i ich bieżącego stanu technicznego
Autorzy:: Szczeciński, S.
Balicki, W.
Powiązania:: https://bibliotekanauki.pl/articles/213533.pdf
Data publikacji:: 2005
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: silniki turbinowe
drgania
zespoły wirnikowe
kryterium jakości wytwarzania
turbine engines
vibration
criterion of production
rotor assemblies
current technical state
Opis:: The article deals with the problem of vibration of the aircraft turbine engines with special attention devoted to the unbalance stages of rotors. This problem is rarely mentioned in the specialist engine reference books. It was shown that the amount of information contained in the data got from the permanently made measurements of amplitudes and frequencies of the transverse vibration of engines, particularly in case of the multi-rotors, can not be overestimated. The relationships of these parameters to: the constructional form of rotors, the quality of their realization and assembling, the effect on the clearance changes in supports and the possibilities to detect emergency states of engines have been presented.
W artykule poruszono problem drgań lotniczych silników turbinowych ze szczególnym uwzględnieniem stopnia niewyważenia wirników. Zagadnienie to bywa jedynie śladowo poruszane w silnikowej literaturze specjalistycznej. Tymczasem ilość informacji zawarta w danych uzyskanych z permanentnie dokonywanych pomiarów amplitud i częstotliwości drgań poprzecznych silników, zwłaszcza wielowirnikowych, jest nie do przecenienia. Przedstawiono związki tych parametrów z formą konstrukcyjną wirników, jakością ich wykonania i montażu, wpływem zmian luzów w podporach i możliwościami wykrywania stanów zagrożenia bezpiecznego użytkowania silników.
Źródło:: Prace Instytutu Lotnictwa; 2005, 4 (183); 9-16
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Aircraft engines : analysis of reported systems failures in Polish aviation during years 2008-2015
Autorzy:: Balicki, W.
Glowacki, P.
Powiązania:: https://bibliotekanauki.pl/articles/243587.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engine
failure
engine system
ATA chapter
safety system
Opis:: Aircraft engine failure during different aircraft flight phases can cause accidents or incidents. ICAO Annex 19 requires from each state establishing the state safety program (SSP) and from the subordinate aviation organizations safety management system (SMS). Point 5.2.1 of Annex 19 instructs to establish safety database, which should be used for effective analysis of actual and potential safety deficiencies. Such analysis should lead to determining necessary measures in order to improve safety. Polish Civil Aviation Authority among other databases manages an important one called European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS). The authors have done a laborious processing of the data contained in that database analysing engine failures based on criteria like phases of flight, ATA chapters concerning powerplant and category of the occurrence. Separately, under consideration were taken engines installed on aircraft with an MTOM <5700 kg (mainly General Aviation) and for aircraft with MTOM > 5700 kg (commercial aviation). The article presents a proposed method of predicting the number of events, the alert levels for the next years and for ATA chapters’ determination, assuming a normal distribution (Gaussian). It is one of the first attempts to use the actual data contained in the database of events in Poland. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important.
Źródło:: Journal of KONES; 2016, 23, 1; 31-37
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Causes of the powerplants failures installed on Polish civil aviation aircraft
Autorzy:: Balicki, W.
Głowacki, P.
Powiązania:: https://bibliotekanauki.pl/articles/133379.pdf
Data publikacji:: 2017
Wydawca:: Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:: powerplant
aircraft engine failure
safety risk
elektrownia
awaria silnika samolotu
ryzyko zagrożenia
Opis:: Currently in Poland about 2,500 different engine types are installed on the aircraft. In the years 2008-2016 powerplants failures caused nearly 600 aviation events. Aborted flight or emergency landing, especially in the case of aircraft powered by a single piston engine occurred. The objective of the article was to determine the failure causes and assessment of their impact on the flight safety. Engine faults were assigned to particular types of powerplants, for example turboshaft, piston, etc. Causes of the failures were examined, assigning ATA chapter to each of them. Also human factor was taken into account. According to the ICAO methodology, aviation safety engine systems essential for flight safety and theirs impact on the safety risk was determined. The results of the analyzes presented in this article are useful for managing the national aviation safety and supervising SMS in aviation organizations. The article shows that preventive measures to raise the level of aviation safety should be taken. This is the first comprehensive analysis of the powerplants failure causes and an evaluation of their influence on the level of aviation safety in Poland.
Źródło:: Combustion Engines; 2017, 56, 1; 110-121
2300-9896
2658-1442
Pojawia się w:: Combustion Engines
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: ICAO aviation occurrence categories significantly affecting aviation safety in Poland from 2008 to 2015
Autorzy:: Głowacki, P.
Balicki, W.
Powiązania:: https://bibliotekanauki.pl/articles/198482.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: air transport
security management
aircraft accident
aircraft power plant
transport lotniczy
zarządzanie bezpieczeństwem
wypadek lotniczy
napęd statków powietrznych
Opis:: Poland, as a member of the EU, is represented within the ICAO, by the European Aviation Safety Agency. However, this does not relieve our country from the responsibility of developing a state safety programme (SSP). The need to set up such a programme, which has to be specific to every country involved in aviation operation, was introduced by the ICAO’s Annex 19. One of the important points in Annex 19 is: “5.2.1 Each State shall establish and maintain a safety database to facilitate the effective analysis of information on actual or potential safety deficiencies obtained, including that from its incident reporting systems, and to determine any actions required for the enhancement of safety”. The Polish Civil Aviation Authority, along with other databases, manages the European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS). The authors (who are specialists dealing with exploitation processes in aviation) have conducted a laborious processing of the data contained in the ECCAIRS database, analysing them based on various criteria: aviation occurrence categories (as defined by the ICAO), phases of flight for different airports in Poland etc. Aircraft with an maximum take-off mass (MTOM) 5,700 kg (commercial aviation) were considered separately. It was found that the most events are those that relate to power plant (SCF-PP) airframes and related system (SCF-NP) failures, followed by collisions with birds (BIRD), events related to airports (ADRM) and events related to the required separation of aircraft (MAC). For lighter aircraft, the dominant categories are ARC, CTOL, GTOW and LOC-I events. The article presents a proposed method for predicting the number of events, determining the alert levels for the next years and assuming a normal distribution (Gaussian). It is one of the first attempts to use actual data contained in the database of events on airports in Poland. The results of this analysis may support the decisions of supervisory authorities in the areas where security threats are most important.
Źródło:: Zeszyty Naukowe. Transport / Politechnika Śląska; 2017, 94; 47-56
0209-3324
2450-1549
Pojawia się w:: Zeszyty Naukowe. Transport / Politechnika Śląska
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Assessment of the airframe systems affecting safety risks caused by large aircraft
Autorzy:: Balicki, W.
Głowacki, P.
Kawalec, M.
Powiązania:: https://bibliotekanauki.pl/articles/245601.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: large aircraft
failure
ATA chapter
safety level
Opis:: Hazard is a safety condition that could cause or be a part of unsafe aircraft operation. It also has an impact on aviation safety related to aircraft systems as well as services. Safety risk is a part of so-called safety management and is the predicted probability and severity of the outcomes of a hazard. Aircraft utilized by airlines and cargo operators which have MTOM >5700 kg are defined by authors as a large aircraft and have to be treated in their systems reliability analysis separately from small aircraft. Despite the fact that both types of aircraft categories events are included in the same databases - European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS) and Aircraft Continuing Airworthiness Monitoring (ACAM), due to different predominant systems failures could not be considered in the same way. The authors have performed processing of the data contained in available databases analysing large aircraft airframe systems faults, which were assigned to the specific ATA chapters. The most frequently occurring defects of the aircraft systems were identified. The goal of this article is to present a method of the current reliability of large aircraft systems assessment. Based on it, the authors are proposing a way of safety risk estimation and prediction of the safety levels for the next two years. The results of this analysis may support the decisions of supervisory authorities in the areas where security threats are most important. They can also help aircraft operators with identification of the aircraft systems, which require special attention.
Źródło:: Journal of KONES; 2016, 23, 1; 39-46
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Comparison the piston air engine performance with aviation gasoline (Avgas) or the E-85 ecological fuel supply
Autorzy:: Balicki, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/243897.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: nternal combustion engine
piston air engines
ecological fuels
exhaust pollutant
Opis:: The fuel presently used for feeding of aircraft piston engines (petrol including TEL) is characterized by "strong unfriendliness" for environment. Many research centres have been going on fuels investigation, which could substitute Avgas utilized in aviation. This is why are there no being in force for Europe standards defining the allowable emission of pollutions in exhaust gases of aircraft piston engines (equivalent to EURO - standards introduced for traction engines). The mixtures of gas o line and alcohols are tested as "alternative" aircraft fuels for spark ignition engines, and in case of Diesel engines - evenjet kerosene. During the research works on test bed carried out at Institute of Aviation the performance offour-stroke aircraft carburettor piston engine supplied by "classical" aircraft petrol and the E - 85 fuel (mixture of petrol and ethanol) were compared. Except for measuring the functional parameters of engine (rotational speed, torque, specific fuel consumption, pressures and temperatures) the emissions of gaseous pollutants incorporated in exhaust gas were measured and analyzed. The range of modifications of engine supply system - necessary to introduce in case of changing of fuel type within the tested engine -was worked up. There are foreseen comparative test of fuelling the engine with mixtures of petrol and alcohols in different proportions in the next phase of research works.
Źródło:: Journal of KONES; 2010, 17, 3; 25-32
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Safety performance indicators assessment for small aircraft airframe systems
Autorzy:: Balicki, W.
Głowacki, P.
Loroch, L.
Powiązania:: https://bibliotekanauki.pl/articles/244319.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft system
small aircraft
ATA chapter
safety risk
Opis:: Safety performance indicators are the parameters used for monitoring and assessing safety performance. Such factors are determined based on available safety databases, collected on government level (in Poland Civil Aviation Authority) or by aircraft operators. Aircraft system failure during different flight phases can cause an accident or an incident. Polish Civil Aviation Authority between other data bases manages two important ones called: European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS) and Aircraft Continuing Airworthiness Monitoring (ACAM).General Aviation (GA) operates mainly aircraft with MTOM<5700 kg powered by the single piston engine. At present, reliability of GA aircraft systems in Poland is unknown. Increasing size of this fleet in Poland requires taking necessary measures in order to establish safety risks and safety performance targets for GA fleet. The authors have performed processing of the data included in available databases analysing airframe failures based on criteria like: phases of flight, ATA chapters concerning aircraft systems and the category of occurrence. The goal of this article is to present method of the current reliability of GA aircraft systems assessment. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important also can help production organizations in identification of the aircraft systems, which required design changes.
Źródło:: Journal of KONES; 2016, 23, 2; 31-38
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Testing of initiation of rotating detonation process in hydrogen - air mixtures
Autorzy:: Balicki, W.
Irzycki, A.
Łukasik, B.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/247318.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: internal combustion engine
turbine engines
combustion chamber
rotating detonation
Opis:: The paper presents results of some research work done in the project, which aims to apply of an innovative combustion chamber to the turbine engine. Expected benefits of using of a new chamber in which classical deflagration type combustion process would be replaced with a detonation combustion type, arise from greater efficiency of FickettJacobs cycle, which corresponds to rotating detonation combustion, in comparison to "classical" Brayton cycle, characteristic of deflagration combustion. The presented task concerned fundamental research carried out on test bench designed and built at the Institute of Aviation in Warsaw. To initiate the detonation combustion in the fuel-air mixtures the ignition device of appropriately high energy is necessary. The released energy should be directed to the area where the mixture has proper constitution - preferably close to stoichiometric one. Four different ignition manners were examined in the course of research: electrical ignition system adapted from turbine engine (semiconductor spark plug), powder charge ignition (handgun cartridges), detonation primer ignition using pentryt, and high voltage discharge (plasma jet). The appearance of detonation type combustion was identified on the basis of combustion gas pressure run, measured using piezoelectric sensors at a frequency of 1 MHz.
Źródło:: Journal of KONES; 2012, 19, 2; 25-34
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Report on the implementation of the POIG project „turbine engine with a detonation combustion chamber”
Autorzy:: Kalina, P.
Wolański, P.
Balicki, W.
Perkowski, W.
Rowiński, A.
Powiązania:: https://bibliotekanauki.pl/articles/241703.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: combustion
rotating detonation
turbine engine
Opis:: This article contains a description of the work carried out under the UDA-POIG 01.03.01-14-071/09-10 project titled “A turbine engine with a detonation chamber”. The work carried out during the project involved 14 construction, research and calculation tasks. Various research stands designed to analyse the process of mixture formation, initiation of detonation and research of rotating detonation in combustion chambers were constructed. Test stand for examining a turboshaft engine with detonation combustion chamber was built. Those test stands allowed powering the combustion chambers and the engine with both liquid and gaseous fuels, simultaneously or separately. At the same time, REFLOPS software, which could calculate the propagation of a detonation wave was created, and used in the design of further versions of combustion chambers. Data from the experiments was used to verify the calculations and models created in the mentioned software. GTD-350 engine was used as the base; the structure of which (combustion chamber situated outside the turbine-compressor unit) facilitated modifying the shape of the detonation combustion chamber. During the research, great emphasis was placed on the safety of researchers. Working with hydrogen in high temperatures and JET-A1 fuel, which was additionally heated, and the usage of the oxy-acetylene detonators forced extreme caution, and full compliance with developed procedures. The project was divided into 14 tasks that were often conducted simultaneously in a 20-person team implementing the project. The work was completed by performing comparative studies between conventional engine with deflagration combustion chamber, and modified engine with a detonation combustion chamber. During the completion of the project, it was the first working demonstrator engine with detonation combustion chamber in the world.
Źródło:: Journal of KONES; 2016, 23, 2; 177-184
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Balancing energy processes in turbine engines
Autorzy:: Balicki, W.
Głowacki, P.
Szczeciński, S.
Korczewski, Z.
Kozakiewicz, A.
Szczeciński, J.
Powiązania:: https://bibliotekanauki.pl/articles/258928.pdf
Data publikacji:: 2014
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: turbine engines
aeronautic and marine propulsion systems
energy balance
mechanical loss
Opis:: The article discusses the issue of balancing energy processes in turbine engines in operation in aeronautic and marine propulsion systems with the aim to analyse and evaluate basic operating parameters. The first part presents the problem of enormous amounts of energy needed for driving fans and compressors of the largest contemporary turbofan engines commonly used in long-distance aviation. The amounts of the transmitted power and the effect of flow parameters and constructional properties of the engines on their performance and real efficiency are evaluated. The second part of the article, devoted to marine applications of turbine engines, presents the energy balance of the kinetic system of torque transmission from main engine turbines to screw propellers in the combined system of COGAG type. The physical model of energy conversion processes executed in this system is presented, along with the physical model of gasodynamic processes taking place in a separate driving turbine of a reversing engine. These models have made the basis for formulating balance equations, which then were used for analysing static and dynamic properties of the analysed type of propulsion, in particular in the aspect of mechanical loss evaluation in its kinematic system.
Źródło:: Polish Maritime Research; 2014, 4; 48-56
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Introduction to Alvis modelling language
Wprowadzenie do języka modelowania Alvis
Autorzy:: Szpyrka, M.
Matysik, P.
Mrówka, R.
Witalec, W.
Baniewicz, J.
Balicki, K.
Powiązania:: https://bibliotekanauki.pl/articles/152699.pdf
Data publikacji:: 2011
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: język modelowania Alvis
formalna weryfikacja
systemy wbudowane
Alvis language
formal verification
embedded systems
Opis:: Alvis is a novel modelling language designed for embedded systems. It combines both high level programming language used to define agents behaviour with hierarchical graphical modelling language used to define interconnections between agents. The paper presents a survey of the most important features of the language.
Alvis jest nowym językiem modelowania przeznaczonym do rozwijania systemów wbudowanych. Łączy w sobie cechy języków programowania wysokiego poziomu z hierarchicznym językiem modelowania połączeń między agentami. Podstawowym elementem języka Alvis są agenty, które mogą działać współbieżnie, komunikować się ze sobą, czy też współzawodniczyć o zasoby dzielone. Dynamika poszczególnych agentów jest opisywana w warstwie kodu używającej do tego celu języka programowania wysokiego poziomu (połączenie natywnych konstrukcji języka Alvis i języka funkcyjnego Haskell). W warstwie graficznej definiowane są połączenia między agentami wskazujące, które agenty się ze sobą komunikują i jaki jest kierunek tej komunikacji. Warstwa ta ma postać grafu hierarchicznego, co pozwala rozwijać systemu wbudowane metodą od ogółu do szczegółu lub odwrotnie. Formalną reprezentacjąmodelu w języku Alvis jest graf LTS (Labelled Transition System), który reprezentuje wszystkie osiągalne stany i przejścia między nimi. Graf ten jest stosowany do formalnej weryfikacji modelu. Artykuł zawiera przegląd najistotniejszych cech języka Alvis.
Źródło:: Pomiary Automatyka Kontrola; 2011, R. 57, nr 9, 9; 1086-1089
0032-4140
Pojawia się w:: Pomiary Automatyka Kontrola
Dostawca treści:: Biblioteka Nauki

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