Wyniki wyszukiwania - Biblioteka Nauki

1

Project of aircraft attack avionics on - board control system with air - task efficiency estimation subsystem based on fuzzy logic (rockets subsystem in A-G missions)

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Grzesik N.

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2013

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tom Vol. 20, No. 1

119--125

EN

In this article author presents the project of aircraft attack avionics on-board control system with fuzzy efficiency of air-task estimation subsystem (rockets subsystem in A-G missions). Conducting extensive analysis and preliminary studies and very wide range of applications of fuzzy logic, the author found that its properties could also be used in aviation. Author’s study referred to the development of fuzzy expert aircraft attack avionics on-board control system project used by pilot during the air task (air combat task with use of rockets). One of the projects was presented in the publication. It has been developed based on Matlab (Fuzzy Logic Toolbox) and Simulink software. Complicity of the project and some mathematical calculations required relevant assumptions, which are also reported. At the end author describes his vision about operation of the system and conclusions. Schematic diagram of aircraft attack avionics system and rockets on-board control subsystem with fuzzy efficiency of air-task estimation subsystem, fuzzy efficiency estimation subsystem schematic diagram, inference and defuzification in rule viewer, fuzzy efficiency estimation control surfaces, dependence of the efficiency of the air- task on the distance from the target for „Rockets fuzzy controller” are presented in the paper.

2

Applying AIM-9X on MiG-29 : Initial Analysis of MiG-29 Weapon System Modernizations

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Grzesik N.

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2012

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tom Vol. 3, Nr 1 (7)

83-90

EN

Author, in this article, describes technical realizability of assembly AIM-9X missile on MiG-29, gives also in the introduction information about aircraft modernizations necessity. Second and third part of the article consist of technical, physical and operating data of AIM-9X air to air missile, LAU-129A/A missile launcher and missile launcher adapter. Fourth part contains mechanical and electric adaptations. Fifth part includes description of weapon control system and blocks locations. Conclusions end the publication. This article is integral part of author’s scientific research and cooperation with Armament Market Analyzing Office of Ministry of Defense.

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Ocena możliwości wykorzystania zbiorów rozmytych w badaniu efektywności pokładowych systemów sterowania (kierowania) bronią współczesnych samolotów wielozadaniowych

63%

Adamski M. , Grzesik N.

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tom Nr 1

15--33

PL

Poniższa publikacja jest próbą odpowiedzi na pytanie: czy istnieje możliwość wykorzystania zbiorów rozmytych w badaniu efektywności pokładowych systemów wspomagających, ze wskazaniem na system sterowania (kierowania) bronią, nowoczesnego samolotu wielozadaniowego? Dokonano analizy wybranych współczesnych, polskich i zagranicznych statków powietrznych oraz analizy współczesnego pola walki pod kątem nielinearności, a także zakresu wykonywanych zadań i dostępnego uzbrojenia, uwzględniając jednocześnie środki przeciwdziałania i mobilność przeciwnika. Przestawiono również charakterystykę, a także cechy systemów rozmytych umożliwiające zastosowanie w lotnictwie wojskowym.

4

Ocena kosztów wykonania zadania lotniczego z zastosowaniem nieadaptacyjnych sterowników rozmytych

63%

Grzesik N. , Adamski M.

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tom Nr 2

93--99

PL

Ze względu na coraz szersze zainteresowanie i zastosowanie teorii zbiorów rozmytych w wielu dziedzinach nauki i techniki, autorzy podjęli próbę przedstawienia projektu nieadaptacyjnego sterownika rozmytego oceniającego koszty wykonania zadania lotniczego. Krok po kroku przestawiono projekt sterownika rozmytego, który przy wykorzystaniu odpowiedniej ilości i jakości informacji, mógłby być praktycznie wykorzystany.

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Measurement methods for determining the parameters of injectors in internal combustion engines

63%

Grzesik N. , Zaremba R.

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tom Vol. 21, No. 4

153--159

EN

The general principle of internal combustion engine operation has not changed since the engine structure was first developed. However, the system of blending the air and fuel into a mixture with the parameters ensuring effective fuel combustion processes has been evolving over the years. In the simplest engines, the fuel-air mixture was produced in the inlet manifold i.e. in the carburettor systems while the more advanced motors were equipped with the system of Single Point Injection (SPI), and further on with the Multi-Point Injection (MP!) where each of the cylinders has its own individual injector. The Multi-Point Injection (MPI) system has evolved into a Gasoline Direct Injection (GDI) system where the injector sprays fuel directly into the combustion chambers. Presently, due to the restrictive regulations governing the issues of exhaust gases ' composition and emissions, manufacturers of the engines used mainly in the automotive industry apply the system of multi-point indirect injection to the intake manifold or the system of direct fuel injection to the combustion chambers. In both systems, these are the injectors dosing precise amounts offuel, which are the most important, and the most accurate elements of the system. The article presents the injectors' macro- and microscopic parameters used for the purpose of the fuel dispersants' technical condition and performance assessment. Additionally, it refers to direct and optical methods of microscopic parameters measurement enabling fuel spray diagnostics.

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The use of fuzzy expert system for an automatic control of the propulsion system in the aircraft ZLIN 143LSi

51%

Krok B. , Grzesik N. , Kuźma K.

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2018

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tom Vol. 25, No. 3

307--314

EN

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.