Search

Turbojet engines are nowadays mostly controlled by full authority digital engine control (FADEC) systems using electronic engine control units. Microprocessor based control systems allow application of sophisticated control algorithms. The aim of the presentation is to show the state-of-the-art control systems and perspective algorithms based on integrated situational control methodology, which are aimed to increase the efficiency, reliability, and safety of operation of turbojet engines. Situational control is applied in this case in control and management of turbojet engines under all operational conditions including atypical ones using intelligent elements and strong integration with diagnostic systems. The concept of highly integrated control and diagnostic system is leading to a novel modular control framework with morphing structure and a degree of intelligence. It will be presented for application on general turbojet engines with specific implementation tested on a small turbojet engine in laboratory conditions as a proof of concept with positive results. These algorithms are designed as modular and robust with perspective applications in control of other large scale systems.

The state of present technologies in technical and also non-technical practice is represented by growing complexity of systems. A turbojet engine as a complex system is multidimensional highly parametric system with complex dynamics and strong non-linear behavior with stochastic properties. Its particular property is operation in a wide spectrum of changes of its operating environment (e.g., temperatures from -60 to +40 °C, different humidity, different pressures, etc.). If we want to secure optimal function of such system, it is necessary to develop models and control systems implementing the newest knowledge from the areas of automation, control technologies preferably with elements of artificial intelligence (AI). The present control systems and dynamic models are often limited to control or modeling of a complex system in its certain (operational) states. However, in practice the turbojet engine finds itself in very different operating conditions that influence its parameters of operation and characteristics. To create progressive control algorithms for a turbojet engine, it is necessary to design models in the whole dynamic spectrum of the modeled system including its erroneous states. Furthermore we need to design a control system that will secure operation converging towards optimality in all eventual states of working environment and also inner states of the system represented by its parameters. This leads to the need of having increased intelligence of control of turbojet engines that reduces workload of a pilot and also increases safety of operation. Safety represents a decisive factor in design of control systems of turbojet engines and is presently bound with increasing authority of them. The present trend designates such control systems as FADEC – Full Authority Digital Engine Control, however in reality such control systems have different levels of authority, intelligence and come in very different implementations. These are often not presented as they are intellectual properties of commercial companies. The article will be aimed on description of some present trends in development of FADEC systems and own proposals of methodologies leading towards design and implementation of a FADEC system with high level of intelligence able to solve all operational situations of a turbojet engine. This is strictly bound with presentation of modern methods of modeling of turbojet engines and the use of advanced methods of mainly sub-symbolic artificial intelligence. The proposed methods are all tested in real-world environment using a small turbojet engine MPM-20 in our laboratory setup. Therefore the article will also deal with approaches in digital real-time measurement of state parameters of this engine and design of control algorithms from engineering standpoint.

By the term of flight dynamics, we refer to the general study of performance, stability and control particularly for VX- 3 Unmanned Aerial Vehicle (UAV) during the flight. Each of these aspects of aircraft flight is described separately through the defined flight regime conditions and considering the specific aircraft configuration and geometry aspects. The calculation of an individual flight mode involves the analysis and definition of kinematic and dynamic parameters that are entered into the equations of motion derived from 2nd Newton's Law. The result of the calculated performance is shown in the diagram of the dependence of height and speed (H-V diagram) with a parametric representation of other quantities of interest. Performance diagram show the envelope, i.e. the operating area of an aircraft with optimal modes of interest and maximum operational limitations (e.g. maximum altitude or flight ceiling).

One of the praxeological problems of safe and sustainable air transport (airfreight transport/air cargo, and air passenger transport) is the prevention and management of risks by competent staff, with the support of modern information and communication technologies. This paper presents an educational information model and software for the airport network and information systems risk assessment, primarily intended for aviation education and training of professionals for ensuring safe and sustainable air transport. The solution to the problem is based on the application of the fuzzy logic method in the air transport environment. Based on a fuzzy expert model, the selected scenario, and the input data established separately for airport assets by a group of 23 experts from aviation practice and a university, the following three assessments of airport network information system assets were constructed: Asset A2 (meteorological information systems) has an insignificant risk with an estimated 0.1162, and assets A1 (air traffic control and management (ATM), navigational aids and approach) and A3 (runway monitoring system) received a low risk of airport network and information systems (NIS) security with ratings of 0.2623 and 0.2915, respectively. An airport NIS risk assessment was aggregated (0.2288), indicating a low degree of security risk to the airport&rsquo, s network and information systems. The aggregated risk assessment of airport NIS, including financial loss data, was calculated as 0.1438, representing a low degree of security risk to the airport&rsquo, s network and information systems. Scenarios for evaluating airport assets are changing for students during education. The results of the developed model and its software will be part of the Simulation Center of the Faculty of Aeronautics.

A diagnostic system is one of the key components securing the safety of operation of a turbojet engine. There are many different engineering approaches how to design engine diagnostic systems applied in real-world conditions. We propose a novel approach for a diagnostic system design to be applied on the object of a small turbojet engine using thermal diagnostics combined with a more traditional model based approach. The combination of these two approaches together with application of methods from the area of computational intelligence create a hybrid diagnostic system, which can be integrated with a control system of the engine. The article also deals with experimental validation of the designed diagnostic system on the object of a small turbojet engine iSTC-21v in laboratory conditions.

The purpose of the paper is to present a comprehensive expert model created to obtain the quantitative safety risks assessment of environmental projects’ implementation in the aviation sector, within the investment phase of the project life cycle. The successful implementation of aviation environmental projects depends also on the security risks of the projects, their implementation, and the team implementing them. The complex expert model will allow increasing the degree of validity of the decision on the security risks of project implementation in the aviation sector. On one hand, the developed model uses the quantitative estimates of the project on various indicators and it is based on different models, and on the other hand, it uses the experience, the knowledge and the expertise of the project, and the security experts in the subject area. The model is based on the neuro-fuzzy network. It enhances the accuracy and the objectivity of the project evaluation within the investment phase of the project life cycle. Copyright © 2020 Praise Worthy Prize - All rights reserved.

In order to efficiently control passenger aircraft in general., the control process is usually adapted according to flight situations. A system for selection of a particular flight situation contains complex decision making algorithm using a lot of sensors. The aim of the paper is to present a very simple., yet efficient approach of a basic flight phase classification., which is applicable in small unmanned airplanes., which have a limited computational and sensor capabilities. The flight phase selection system can be then implemented in an intelligent control and flight envelope protection system of such UAV., which are also presented in the paper.

Experimental identification as one of the possibilities of creating mathematical models of complex systems is a fast, simple and easy-to-use methodology. Even with a low percentage of knowledge of the modelled object (functionality, internal bonds, etc.) it is possible to obtain a mathematical model with high quality - similarity - verification. The disadvantage of experimental identification is the necessary existence of a functional complex system and a measuring - sensing apparatus. The Laboratory of intelligent control systems of aircraft engines has four full-featured functional systems - small and micro turbo compressor aviation jet engines. Experimental identification of small jet engines based on the measured transition characteristic is being researched using these engines. The question and topic of this article is to verify the possibilities and ways of creating mathematical models by experimental identification based on the acquired - measured transition characteristics for the smallest category of aircraft engines - micro turbo-compressor jet engine and evaluate obtained simulation models of different complexity.

Information about temperature distribution in the thermal field can serve as one of the major parameters for turbojet engine diagnostics and can contribute to extended technical lifetime of the engine. The aim of the submitted paper is to perform a basic analysis of the thermal field distribution during various operational modes of a small turbojet engine. As the object for thermal field investigation, a small turbojet engine iSTC-21v, installed in a laboratory, was used. The thermal field has been captured by a thermographic camera. The article presents an analysis of temperature distribution in various nodes of the small turbojet engine, defining critical parts of the engine during its operation, which can be further analyzed for diagnostic purposes. It is expected that this analysis can also be applicable for high power jet engines.

In this paper, a mobile application and a server-side system is designed for remote physical system monitoring. The proposed design is usable for any system with data acquisition system from National Instruments or a system that can create a Socket connection. The application itself is the top layer of the data acquisition chain oriented on the client side. Proposed applications use the UDP protocol to transfer audio, video and data content through the network.

Improvements in reliability, safety, and operational efficiency of aeroengines can be brought in a cost-effective way using advanced control concepts, thus requiring only software updates of their digital control systems. The article presents a comprehensive approach in modular control system design suitable for small gas turbine engines. The control system is based on the methodology of situational control; this means control of the engine under all operational situations including atypical ones, also integrating a diagnostic system, which is usually a separate module. The resulting concept has been evaluated in real-world laboratory conditions using a unique design of small turbojet engine iSTC-21v as well as a state-of-the-art small turbojet engine TJ-100. Our results show that such advanced control system can bring operational quality of an engine with old turbocompressor core iSTC-21v on par with state-of-the-art engines.

This paper presents an alternative teaching method through a virtualized remote laboratory for engineers in aviation, mechanics, control and analytics. In practical conditions, it is difficult for students to access a physical turbojet engine in a testing facility and study its operation on-site. Either the operation rooms lack the space for observers and operators, or only some specific personnel are permitted to access the operation room, thus rendering the students unable to gain practical experiences on-site.

This paper presents the preparation work and first testing of a real-time monitoring application framework. The framework has been proposed and created for a small turbojet engine iSTC-21V. The main motivation is to provide data for educational purposes in a nearby multimedia lecture room and to wider public that is not able to access the laboratory, due to lack of room in the laboratory or travel distance. To complete this task, we took hold of our first concept and created three joint applications. LabView application for sending measured data using UDP protocol, staging server service (UDP receiver and WebSocket) for distributing data to multiple clients at a time and a sample client web application for receiving and presenting the data (WebSocket). The system is currently not in operation and will be tested after the beginning of the semester.

Adaptive sampling using a neural network and a fuzzy regulator is described as applied to computer network traffics. The objective of this approach is to maximally reduce the amount of data to be processed with preservation of acceptable measurement accuracy. The results of experimental verification of sampling efficiency are also presented that are based on the traffic data archive of a real computer network.

This paper deals with the calculation of 3D flow in a gas turbine and a nozzle with variable geometry of small jet engine ISTC-21V placed in a laboratory LIRSLM at Faculty of Aeronautics. It was used methods of meshing around the geometry of the CAD model and the CFD calculations for viscous flow. The resulting data was then compared to the measured in the laboratory and calculated from the analytical model of the engine. The evaluation has proved the credibility of the calculation to be used as additional knowledge of engine parameters.

How to use an old turbo-compressor (turboshaft) engine and transfer it into a laboratory system used for design and development of progressive control, diagnostic and modeling algorithms transforming it into an intelligent turbo-compressor engine? The intelligent turbo-compressor engine currently designated as iSTC-21v is a small turbojet engine with a single sided radial compressor, bound combustion chamber, single stage un-cooled turbine and variable exhaust nozzle. The engine is equipped with a real-time measurement and intelligent digital control system using two degrees of freedom (fuel supply and exhaust nozzle diameter). The article describes transformation of an old TS-20/21 engine into such engine, which is suitable for laboratory use, research in different areas of cybernetics with perspective applications in different areas of technical practice like unmanned aerial vehicles, ground auxiliary energetic units, generators, etc. The article is aimed to be inspirative also for hobby engine builders, scale modelers and people who work with small turbo-compressor engines.

The goal of this article is to develop a linear mathematical model for a small scale turbojet engine with variable convergent nozzle, and validate it on existing laboratory hardware owned by the authors’ Departments.Control of gas turbine engines plays an essential role in the safety of aviation. Although its role is constantly expanding, ranging from pilot workload reduction to detailed diagnostics, the basic competence is to regulate the thrust output of the power plant with maximum available accuracy, rapidity, stability, and robustness. The linear quadratic control is one possible solution for the above mentioned criteria.Although civil aircraft engines include fixed exhaust nozzle geometry, in military applications the exhaust nozzle geometry is also adjustable to reach optimum efficiency due to better matching of individual engine components, etc.In the present article the authors deduce the members of state space governing equations to acquire the basis of the LQ control.The established model is based on the physical laws describing the operational behavior of the engine as well as its complexity should be reduced to an acceptable level where still enough details remain to reflect the nature of the controlled object.

This contribution presents a proposal and practical implementation of a digitally controlled fuel system for control of fuel supply into a small turbojet engine, iSTJ-21V. In the past, for the purposes of fuel metering to the engine MPM-20, which was a previous version of the iSTJ-21V, the servo valve LUN 6743 was used. However, this solution has several disadvantages such as increased strain on the fuel pump and non-linear characteristics. The new fuel control system was tested on a measuring stand and implemented into microcontroller platform and tuned during full operation of the engine. As microcontroller platform the 32 bit NXP LPC1768 microcontroller was chosen. The contribution consists of the principle of control of a small turbojet iSTJ-21V engine and a summary of the results in a graphical form. The main contribution of this work is to create a digitally controlled fuel system with sufficient accuracy control of fuel supply to the engine the need to increase its effectiveness and application of modern control algorithms at a higher level.

Increased redundancy of systems has always been one of the key points to increase reliability and safety of operation of aircraft engines. A special class of such engines is represented by small turbo-compressor engines suitable for propulsion of small aircraft or ground and laboratory use. Specifics of such engines demand design of specialized approaches in order to increase redundancy of their sensor/control systems, thus increasing their operational reliability and safety. The paper proposes general architectures for cost effective approaches to increase the redundancy of sensor and control systems by application of virtual sensor channels and intelligent selectors. The virtual channels are represented by neural networks fusing data from other sensors to dynamically compute the backed up parameter. Intelligent selectors form decision making elements that select the correctly operating control channel. The integration of these two elements creates an intelligent highly redundant sensor and control system suitable for small turbo-compressor engines.

This paper provides a description of a hybrid method for automated evaluation of qualitative parameters. The method is presented on an example of efficiency evaluation by planning experiments with specified set of key performance indicators in case of a turbojet engine in laboratory of intelligent control systems of jet engines (LIRS LM). The implementation of this example is done in form of a state of the art information system concept, created particularly for managing research related data, information and knowledge in from a single research field. The paper also denotes further possibilities in creating prediction models for qualitative parameters that may be used in intelligent data-driven or quality-driven control of the respective system. Other possibility is to expand the key concept of the information system, and utilize the knowledge gained from the results in training of operators and experimenting personnel.

Small turbo-compressor engines represent a specific class of such engines with application in small aircraft and as auxiliary energetic units. Energetic efficiency and high safety standards are nowadays key factors in practical applications of small turbo-compressor engines. One approach to achieve these aims is to design and utilize progressive control algorithms. As turbo-compressor engines represent a non-linear systems operating in a broad range of environments and inner conditions, taking the adaptive approach in controller design can be beneficial. The presented article tests and evaluates different basic approaches in adaptive controller design for a small turbo-compressor engine with modeled altitude and speed characteristics.

In order to achieve higher efficiency and to explore new progressive approaches in control of turbo-jet engines with more than one degree of freedom, the experimental turbojet engine MPM-20 has to be expanded with flexible geometry exhaust nozzle. The article is aimed at design of a mechanism, which would control the variable geometry exhaust nozzle of the engine allowing its practical application. Selection and precise analysis of the appropriate actuator for the needs of digital control of exhaust nozzle and design of the appropriate modifications for its practical use in laboratory conditions are presented. The presented design is usable for similar class of such engines in laboratory conditions.

Progressive development of turbojet engine requires focus not only on improving performance, but also high reliability and safety are very important. That's why we put more and more emphasis on concepts like diagnostics and backup, which represent the basic techniques and methods that contribute to increased safety of any complex system. The article deals with the design of diagnostics/backup system, which uses majority method and backup through computational models that take advantage of experimental identification methods and neural networks. The proposed system for jet engines was subsequently tested in laboratory conditions (LIRS LM-Laboratory of Intelligent Control Systems of Jet Engines) on a small turbojet engine MPM-20, where confirmed its functionality and reliability.

The article is focused on diagnostics in the field of aviation turbo-jet engines. Evaluation of their technical status, and potential failures and pre-failure processes can be improved by monitoring their thermally loaded components. Part of the research in the given area also involves mathematical modeling of the channel measuring the exhaust gases temperature, using neural networks to compensate for dynamic errors of slow thermocouples used in such measurements.

Controlling position of an aircraft in its trajectory is a matter of high precision. The requirement on precision is becoming a priority primarily in the phase of landing, when the aircraft is in automated mode of landing controlling/maintaining lateral deviation along the trajectory by autopilot. The contribution is describing shaping and modeling control signals in the stage of final approach for landing. It proposes a system that can eliminate the interfering high-frequency defects of lateral control system stabilizing aircraft deviation during the landing maneuver and simulating the effects of filters onto the feedback dynamics.

The paper deals with design of an intelligent supervisory system usable in the area of engineering applications of small turbojet engines. Such supervisory system consists of diagnostic and control system applied in different phases of the engine’s operation. In order to design it we need to know the object and its models that will be realized by means of situational modeling concept and neural networks. Diagnostic system will be based on these types of models applied into the majority voting method of online diagnostic. Intelligent supervisory system will also include off-line pre-start diagnostics for such engine with perspective health monitor database.

This paper presents a general description of behavior of a complex thermodynamic system, represented by a small turbojet engine MPM 20. The main aim is to provide basic constraints of chosen measured parameters. Obtained results will be used in future data filtering, to recognize faulty output sensor values, critical situations and normal engine operation field. According to these constraints the engines' operational envelope can also be defined by means of measured parameters. Also using constraints, we may divide the engine operation into several operational modes. These modes are dependent on the absolute value of a measured parameter, a coefficient of two parameters, or a coefficient calculated by more than two parameters.

Summary form only given. The Laboratory of Intelligent Control Systems of Aircraft Engines has been built around the idea of design implementation and testing of progressive algorithms in the areas of identification, modeling, control and diagnostics of complex systems. As such complex system a class of small turbojet engines suitable for laboratory experiments and utilization has been used, the engine MPM-20 derived from turbo-starter TS-20 in particular. Such small turbojet engines exhibit similar dynamic behavior as normal sized engines and have many properties of complex systems like non-linear characteristics, variable cross bindings, broad operational range, non stationary parameters and elements of stochastic behavior.

The article deals with basic description of turboprop engines as a special class of turbine engines - advanced approaches in its modeling and control. The article will deal with description of analytical and experimental approaches in modeling of individual parts of the engine with description of their thermo-dynamics and states. Such engines are systems with two degrees of freedom and demand advanced control algorithm in case of control with single control lever. The article will deal with design of such control algorithm with perspective use of advanced control methods. Such approaches will increase efficiency, fuel consumption, safety and control comfort for the pilot.

The main thesis of this paper considers the possibilities and difficulties of switching from hydromechanical engine control to FADEC (digital) engine control. Regarding different specifications and elements in system, possible errors, advantages and disadvantages, each method has its specific properties of behavior in specific environments and applications. When considering our controlled system, the MPM-20 small turbojet engine, it is a challenge to propose functional control system with backups and with slight possibility of errors during or before operation. In this paper we propose methods of backups for specific elements, prestart diagnostics and on-line diagnostics.

The article is focused on diagnostics in the field of aviation turbo-jet engines. Evaluation of their technical status, and potential failures and pre-failure processes can be improved by monitoring their thermally loaded components. Part of the research in the given area also involves mathematical modeling of the channel measuring the exhaust gases temperature, using neural networks to compensate for dynamic errors of slow thermocouples used in such measurements.

The paper deals with modeling and diagnostics of complex systems. In the area of modeling, the authors describe dynamic models of dependence of speed upon fuel flow supply of a small turbojet engine MPM-20. The first model is done with use of neural networks and the second is a linear model. Both models are then methodologically incorporated into the diagnostic and backup system of the optical sensor measuring the speed of the engine.

This article is concentrated on research of magnetic aura of aircraft engine MPM 20 during its operating modes. Next aim of this article is description of usability of magnetic aura for MPM 20 situational control by fuzzy controller.

Mathematical modeling represents an efficient method allowing us to examine properties of a researched object [1]. Realization of mathematic models has become a fundamental part of design of many complex systems. By use of simulation, we can experiment with mathematical model similarly as with the real object without the risk of critical states and with much lower expenses. Modeling represents experimental process that asserts to the examined original, the real object (or the modeled system) unambiguously another physical or abstract system. The article deals with approach to virtual modeling of a compressor in a small turbojet engine. This article will present design of analytic model of a jet engine (MPM-20 engine in particular) and its graphical depiction into its compressor characteristics.

The article deals with modern concepts of control systems used in turbojet engines. We specifically aim on description of control systems using methods and concepts of artificial intelligence, which can bring a new quality in terms of operation and safety of turbojet engines' operation. We also propose a design of intelligent control system for small turbojet engine MPM-20 within the scope of methodology of situational control together with exploration of macro and micro situations concepts.

The growing demands on safety authority and intelligence of control systems requires new approaches in design. One approach that is usable and potentially effective are anytime control algorithms that can be used in the area of modeling and control [6, 11, 14, 15]. Use of such algorithms allows the system to flexibly react on changes of outer environment and be able to survive deficiency of time, information and resources.

Mathematical modeling represents and efficient method allowing us to examine properties of a researched object [1]. Realization of mathematic models has become fundamental part of design of many complex systems. By use of simulation, we can experiment with mathematical model similarly as with the real object without the risk of critical states and with much lower expenses. Modeling represents experimental process that asserts to the examined original, the real object (or the modeled system) unambiguously another physical or abstract system. The article deals with approach to virtual modeling of a compressor in a small turbojet engine.

The article deals with full authority digital engine control (FADEC) systems and possibilities of application of concepts and methods of artificial intelligence in such control system. FADEC represents a framework where the most modern methods of artificial intelligence can be applied. This represents a great potential for increase of reliability, efficiency and overall quality of control of turbojet engines. We are trying to design and implement a FADEC control system for our small experimental turbojet engine MPM 20.

The article deals with basics of modeling of our small experimental turbojet engine MPM 20 and the following design of a complex situational control system with elements of anytime control algorithms bound with a developed analytical model of the engine. By use of advanced algorithms using methods of artificial intelligence in a robust framework to achieve the aims of reliability and high efficiency, we are trying demonstrate their usability and proficiency in the area of turbojet engines. All the tests and data come from measurements on a real object of our experimental small turbojet engine and are therefore a good step to be used on normal sized engines.

Small turbojet engines represent a special class of turbine driven engines. They are suitable for scientific purposes and research of certain thermodynamic processes ongoing in turbojet engines. Moreover such engines can be used for research in the area of alternative fuels and new methods of digital control and measurement. Our research, which is also presented in this article, is headed toward these aims. We evaluate and propose a system of digital measurement of a particular small turbojet engine - MPM 20. Such engine can be considered as highly non-linear large scale system. According to obtained data and experiments we propose different model models of the engine and design of situational control algorithms for the engine with use of certain methods of artificial intelligence as new methods of control and modeling of large scale systems.

Small turbojet engines represent a special class of turbine driven engines. They are suitable for scientific purposes and research of certain thermodynamic processes ongoing in turbojet engines. Moreover such engines can be used for research in the area of alternative fuels and new methods of digital control and measurement. Our research, which is also presented in this article, is headed toward these aims. We evaluate and propose a system of digital measurement of a particular small turbojet engine - MPM 20. Such engine can be considered as highly non-linear large scale system. According to obtained data and experiments we propose different approaches to modeling of the engine with use of analytic experimental and certain methods of artificial intelligence as new methods of modeling of large scale systems.

Small turbojet engines represent a special class of turbine driven engines. They are suitable for scientific purposes and research of certain thermodynamic processes ongoing in turbojet engines. Moreover such engines can be used for research in the area of alternative fuels and new methods of digital control and measurement. Our research, which is also presented in this article, is headed toward these aims. We evaluate and propose a system of digital measurement of a particular small turbojet engine -MPM 20. Such engine can be considered as highly non-linear large scale system. According to obtained data and experiments we propose different model models of the engine and design of situational control algorithms for the engine with use of certain methods of artificial intelligence as new methods of control and modeling of large scale systems.

Aircrafts' turbo-compressor engines may be considered as very complex systems with many mutual and also positive feedbacks. Another characteristic of such systems is that they operate in a very large range of outer environment parameters which causes very different behaviour within their working conditions. Critical susceptibility to erroneous states where requirements for reliability are set to highest degree, it is necessary to secure control of such engines in their every state and secure their operation under every environmental or engine conditions. Situational control methods offer such tools to secure not just stabilization of an engine, but its control, using different control strategies for different working conditions.

Small turbojet engines represent a special class of turbine driven engines. They are suitable for scientific purposes and research of certain thermodynamic processes ongoing in turbojet engines. Moreover such engines can be used for research in the area of alternative fuels and new methods of digital control and measurement. Our research, which is also presented in this article, is headed toward these aims. We evaluate and propose a system of digital measurement of a particular small turbojet engine - MPM 20. Such engine can be considered as highly non-linear large scale system. According to obtained data and experiments we propose situational model and situational control algorithms for the engine with use of certain methods of artificial intelligence as new methods of control of large scale systems.