Temat: aircraft system - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

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

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Skocz do pozycji: 3.

Tytuł:: Przegląd ekologicznych militarnych i cywilnych systemów zasilania
The overview of ecologic military and civilian power systems
Autorzy:: Michalak, Sławomir
Kowalczyk, Henryk
Gębura, Andrzej
Tokarski, Tomasz
Powiązania:: https://bibliotekanauki.pl/articles/38914031.pdf
Data publikacji:: 2024
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: ogniwo wodorowe
ogniwo paliwowe
PEM
ogniwo metanolowe
DMFC
panel fotowoltaiczny
PV
elastyczny panel fotowoltaiczny
EPF
system naziemny
system lotniczy
system zasilania elektrycznego
statek powietrzny
system łączności
hydrogen cell
fuel cell
methanol cell
photovoltaic panel
elastic photovoltaic panel
on-board system
aircraft system
electric power system
aircraft
communication system
Opis:: Pozyskiwanie energii elektrycznej jest istotnym wyzwaniem XXI wieku. Na świecie w elektroenergetycznych projektach cywilnych coraz silniej dominują tendencje proekologiczne: energia wiatru, promieniowania słonecznego i energia elektryczna z tzw. baterii wodorowych i ich mutacji. W zastosowaniach wojskowych wykorzystanie tego typu źródeł również jest korzystne, gdyż znacznie poprawia możliwości maskowania, m.in. umożliwia zmniejszenie poświaty termicznej i natężenia hałasu. Autorzy artykułu opracowali przegląd ekologicznych systemów zasilania oraz przedstawili aktualny stan wdrożeń.
Obtaining electrical energy is a substantial challenge for the 21st century. The world is increasingly dominated by pro-ecological tendencies: wind energy, solar radiation and electric energy from the so-called hydrogen batteries and their mutations. In military applications, using these source types is also beneficial since it substantially improves camouflage possibilities, e.g., it enables the reduction of the thermal afterglow and noise intensity. The manuscript’s authors developed the overview of pro-ecological power systems and presented the current state of implementations.
Źródło:: Journal of KONBiN; 2024, 54, 1; 33-46
1895-8281
2083-4608
Pojawia się w:: Journal of KONBiN
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Aircraft docking guidance system to the gate using fuzzy logic
Autorzy:: Żurawski, P.
Grzesik, N.
Kuźma, K.
Powiązania:: https://bibliotekanauki.pl/articles/243957.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fuzzy logic
fuzzy expert system
aircraft taxiing
aircraft steering
Opis:: The article presents the concept of automated final process of aircraft taxiing to the gate at the terminal. On the basis of an analysis of the possibilities of aircraft taxiing in civil airports, the authors attempted at optimizing this process. The main objective of the project is to reduce the taxiing time, consequently reducing fuel consumption as well as the rotation time. As a result of the work, the authors designed a controller based on fuzzy logic, which, depending on the initial parameters, calculates the set values for the execution system of aircraft control in the horizontal plane and for the taxi speed. The controller receives two input signals, which determine two output signals. The designed controller allows comprehensive and fully automated aircraft steering. The project relies on data with regard to the apron class D, suited to handle aircraft with a wingspan of up to 52 m and the characteristics of a Boeing 767-200 in speed taxiing and the maximum turn of the nose gear. The measurements of the apron have been adopted in accordance with international regulations in the ICAO DOC 9157 “Aerodrome Design Manual”. The maximum deviation of the nose gear from the centre line was assumed 2.5 m in each direction and a safe distance behind the immobile aircraft equal to 25 m. The length of the Boeing aircraft 767-200 is below 48 m, therefore the input boundary parameters are equal to +/- 2.5 m from the centre line and 80 m from the designated aircraft stand (nose gear). The article presents the project of the controller and its optimization. The authors simulated the controller operation in the package MATLAB “Simulink”. The article ends with data analysis and final conclusions.
Źródło:: Journal of KONES; 2018, 25, 3; 549-556
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Optimisation of aircraft maintenances in the polish armed forces
Autorzy:: Kowalski, M.
Waślicki, P.
Żak, J. M.
Powiązania:: https://bibliotekanauki.pl/articles/246572.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft
maintenance system
optimisation task
Opis:: Maintaining the aircrafts (AC) of the Polish Armed Forces in operating condition is determined by adequate resources to secure maintenance and repairs possessed by the companies implementing these tasks on them. The article characterises and then describes formally the Aircrafts Maintenance System in the Polish Armed Forces. The assumptions of the aircraft maintenance system model, proposed model structure, and mapping of aircraft maintenance performance were described. The most important elements (such as data, decision variables, boundary conditions and assessment criterion function) of an optimisation task aimed at minimising the executed aircraft maintenances’ costs were formulated. For this purpose, the record of evaluation criterion functions of the companies performing aircraft maintenance was shown. The article was completed with a conclusion, which underlined the importance of the proposed optimisation model. The optimisation model proposed in the article allows evaluating the aircraft maintenances’ organisation and their parameters. The formal record concerns both in the case of one-dimensional maintenance (one aircraft type) and multi-dimensional one (various aircraft types).
Źródło:: Journal of KONES; 2016, 23, 4; 225-235
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

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: 7.

Tytuł:: Selected aspects of technical readiness related to the exploitation system of trainer aircraft in military aviation
Autorzy:: Uchman, Z.
Powiązania:: https://bibliotekanauki.pl/articles/245240.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: technical readiness of aircraft
aviation training system
technical exploitation system
Opis:: One of the problems becoming increasingly important in the exploitation process of each technical object is effectiveness expressed as a ratio of the value of obtained results to the related expenditure. There are several criteria to evaluate the effectiveness of the exploitation process. However, in their selection, it is necessary to take into account the characteristics not only connected with a concrete object or system, but also with a model of its use. In civil aviation, especially in case of airlines and various kinds of service companies, the effectiveness of exploitation system of the aircraft fleet is assessed primarily in economic terms. However, in military aviation, due to its characteristics, slightly different criteria must be applied. In practice, the effectiveness of such systems is usually assessed based on the index of technical exploitation readiness, which specifies the system readiness to execute the agreed tasks within predetermined time. This paper presents selected aspects of technical readiness related to the exploitation system of trainer aircraft in military aviation. The issues connected with determining the total flying time, conducted within the framework of the training cycle, are discussed. The factors affecting the state of technical readiness related to the exploitation system of the aviation technology as well as methods for determining the required number of aircraft to perform the tasks planned for a given period and the index of available service life resources.
Źródło:: Journal of KONES; 2014, 21, 4; 505-513
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: The study of the technical service impact on the aircraft technical readiness
Autorzy:: Uchman, Z.
Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/245912.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: exploitation system efficiency
aircraft technical readiness
technical services
Opis:: The efficiency of the aircraft exploitation process is a problem, to which more and more attention is paid not only in the commercial aviation, but also in the military one. One of the factors, which have a direct impact on its level, is the operated aircraft or helicopter technical readiness that is the ability of airworthiness when there is a need to use them in order to perform specific aviation tasks. In turn, the aircraft technical readiness level is affected by a number of factors, the most important of which include its characteristics, technical service system and logistical security system. This paper is devoted to the issue connected with the aircraft technical readiness assessment as well as identification of factors, which have an impact on its level, and also their impact level analysis. Furthermore, the particular attention was paid to technical services. The research results of a few types of aircraft in terms of the technical service malfunction and damage impact on their technical readiness level were also presented. At the end, the importance of such an approach and the possible use in practice were emphasised.
Źródło:: Journal of KONES; 2016, 23, 2; 397-406
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: The use of fuzzy expert system for an automatic control of the propulsion system in the aircraft ZLIN 143LSi
Autorzy:: Krok, B.
Grzesik, N.
Kuźma, K.
Powiązania:: https://bibliotekanauki.pl/articles/242523.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fuzzy logic
fuzzy expert system
propulsion system
aircraft Zlin 143LSi
Opis:: The article discusses the manner of controlling the propulsion system in the aircraft Zlin 143LSi, which is equipped with a piston engine driving a variable-pitch propeller. All the operating procedures are carried out manually by the pilot in accordance with the flight manual. The authors attempted at developing the project of a controller based on fuzzy logic, whose main goal was automating the control system of the propulsion unit, thus lowering the level of difficulty of pilotage, and increasing the economics of the operation. The project was made in an interactive environment FuzzyLogic Toolbox of the MATLAB programme. In the analysis, three input parameters were taken into account, exerting an impact on changing the rotational speed of the propeller: the charging pressure of the propulsion unit expressed in inches of mercury, the speed of the aircraft (TAS) in knots and the angle of attack, at which the flight is made, expressed in degrees. On the basis of the above-mentioned input signals, the rotation speed of the propeller was determined, by changing the blade pitch and the recommended angle of attack for the parameters in order to make an optimal use of the data of the flight conditions. The article presents the project of the controller and its optimization. The authors simulated the controller operation in the package MATLAB “Simulink”. The article ends with data analysis and final conclusions.
Źródło:: Journal of KONES; 2018, 25, 3; 307-314
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Design and optimisation of exhaust system of light turboprop airplane
Autorzy:: Stalewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/247804.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turboprop aircraft
exhaust system
ejector
computer-aided design
optimisation
Opis:: Innovative exhaust system for light turboprop airplane has been developed and optimised. Apart from the basic function of removing exhaust from turboprop engine, the system supports cooling of the engine bay. To do this, the system removes hot air from the engine bay, utilising the ejector-pump effect, where the exhaust stream generates under-pressure, sucking the hot air through the ejector slot and removes the air together with the exhaust gases. The design and optimisation of the exhaust system has been conducted based on computational methods of Computer-Aided Design and Optimisation and Computational Fluid Dynamic. Three-dimensional analysis of flow around the airplane (including effect of propeller) and inside the exhaust system was conducted by application of URANS solver ANSYS FLUENT. Using these software the trajectories of exhaust particles, both inside the exhaust ducts and outside the airplane, have been determined. Parametric model of the designed exhaust system has been developed using the in-house software PARADES. As design parameters the diameter, length and direction of exhaust ducts as well as few parameters describing a shape of the ejector, have been established. The optimisation process aimed at designing of the exhaust system, which removes the exhaust gases possibly far away from the airframe, especially during a descent flight of the airplane. Additional objectives were maximisation of the mass flow rate of hot air sucked through the ejector and minimisation of the drag force generated by external part of the exhaust system. The optimised exhaust system should have also fulfilled requirements of permissible total-pressure losses inside the exhaust ducts. The optimised exhaust system has been implemented on the light turboprop airplane and validated during flight tests.
Źródło:: Journal of KONES; 2016, 23, 2; 341-348
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: The application of the BSSD Iono-Free linear combination method in the processing of aircraft positioning
Autorzy:: Ćwiklak, Janusz
Grzegorzewski, Marek
Krasuski, Kamil
Powiązania:: https://bibliotekanauki.pl/articles/247076.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: GPS system
aircraft positioning
BSSD Iono-Free linear combination
air navigation
Opis:: The article presents the results of research into the use of the differentiation technique of BSSD (Between Satellite Single Difference) observations for the Iono-Free LC combination (Linear Combination) in the GPS system for the needs of aircraft positioning. Within the conducted investigations, a positioning algorithm for the BSSD Iono-Free LC positioning method was presented. In addition, an experimental test was conducted, in which raw observational data and GPS navigation data were exploited in order to recover the aircraft position. The examination was conducted for the Cessna 172 and the on-board dual-frequency receiver Topcon HiperPro. The experimental test presents the results of average errors of determining the position of the Cessna 172 in the XYZ geocentric frame and in the ellipsoidal BLh frame. Furthermore, the article presents the results of DOP (Dilution of Precision) coefficients, the test of the Chi square internal reliability test and the HPL and VPL confidence levels in GNSS precision approach (PA) in air transport. The calculations were performed in the original APS software (APS Aircraft Positioning Software) developed in the Department of Air Navigation of the Faculty of Aeronautics at the Polish Air Force University.
Źródło:: Journal of KONES; 2019, 26, 3; 15-21
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Wpływ czasu eksploatacji systemu elektroenergetycznego statku powietrznego na jakość energii w stanach nieustalonych
The effect of the operation time of the aircraft power system on power quality in transient states
Autorzy:: Michalak, Sławomir
Tokarski, Tomasz
Powiązania:: https://bibliotekanauki.pl/articles/38913844.pdf
Data publikacji:: 2024
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostyka
starzenie
system elektroenergetyczny
statek powietrzny
jakość energii
stan nieustalony
samoregulacja
zdolność do lotu
bezpieczeństwo latania
diagnostics
aging
power system
aircraft
power quality
transient state
self-regulation
airworthiness
flying safety
Opis:: W pracy omówiono znaczenie parametrów energii elektrycznej w stanach nieustalonych dla oceny zdolności sieci elektroenergetycznej statku powietrznego do samoregulacji. Wykazano, iż na jakość energii elektrycznej systemu elektroenergetycznego statku powietrznego wpływa czas jego eksploatacji. Zmiany starzeniowe wynikające z długotrwałej eksploatacji systemu elektroenergetycznego powodują pogorszenie parametrów energii elektrycznej, a to wpływa bezpośrednio na zdatność do lotów oraz bezpieczeństwo latania. Zachowanie normatywnych parametrów energii w stanach nieustalonych jest bardzo istotne dla zapewnienia prawidłowej eksploatacji statku powietrznego. W artykule opisano metodę pomiarów jakości energii elektrycznej w stanach nieustalonych, a na przykładzie systemu elektroenergetycznego prądu stałego samolotu Su-22 przedstawiono istotę diagnostyki jego sieci w stanach nieustalonych. Zaprezentowano również przykładowe wyniki badań, przeprowadzonych przez autorów, dotyczących zmian parametrów energii elektrycznej w stanach nieustalonych samolotu Su-22, uzyskane w czasie jego wieloletniej eksploatacji.
The paper presents the importance of electricity parameters in transient states for assessing the ability of an aircraft's power grid to self-regulate. It has been shown that the quality of electrical energy of an aircraft's power system is influenced by its operating time. Aging changes resulting from long-term operation of the power system cause deterioration of electrical energy parameters, which directly affects airworthiness and flying safety. Maintaining standard energy parameters in transient states is very important to ensure proper operation of the aircraft. The article describes the method of measuring the quality of electricity in transient states, and using the example of the DC power system of the Su 22 aircraft, the essence of its network diagnostics in transient states is presented. Also presented are sample results of research conducted by the authors regarding changes in electrical energy parameters in transient states of the Su 22 aircraft, obtained during its many years of operation.
Źródło:: Journal of KONBiN; 2024, 54, 1; 47-63
1895-8281
2083-4608
Pojawia się w:: Journal of KONBiN
Dostawca treści:: Biblioteka Nauki

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