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Current trend in aviation is to increase efficiency of all the aircraft’s systems. This leads to a reduction of fuel consumption which has also positive effect on emissions. One possibility how to reach this aim is to replace hydraulic and pneumatic system with an electrical power system. Because many on-board electrical loads are in the form of electrical drives, the special attention is given to electric motors and their electronic speed controllers / power converters. Furthermore, electric motors suitable for traction/propulsion are presented. Moreover, the various types of starter/generators suitable for on-board utilisation are compared in the paper.

This article analyzes the changes of on-board electrical power systems of modern transport aircraft with a higher degree of electrification, so-called MEA (More Electric Aircraft) compared to the traditional architectures, in the field of standardized electrical power parameters. Developments in this field are characterized by increased requirements for power of installed power sources and switching to higher voltage values and source units with a non-stabilized frequency value of the generated voltage, so-called frequency wild systems.

Priorities of on electronic airport security system involve timely information on unauthorized penetration or an attempt of entering the airport areas. Visible positioning of some of the system components is to divert potential perpetrators from attempting to penetrate airport facilities by way of signaling such events and also serving as a means of prevention.

The paper deals with the issue of Local Departure Control System (further only DCS) and its application in the airport environment. The authors submit their own DCS system solution supported by the Slovak Research and Development Agency under the contract no. VEGA-15-0527. The aim of the project was to design and then implement a solution that would meet the highest criteria of reliability, safety, and usability of the proposed solution in the field of its deployment. The primary target groups are local carriers, airlines, and airports operating in Slovakia with a special focus on regional low-cost companies and charter companies. Within the implementation of the project, algorithms of provided functions and activities of individual software modules were designed. Subsequently, the DCS hardware elements were optimally dimensioned, programmed, tested and tuned for the correct application code for the DCS system modules, as well as for CKI, Gate and PNL terminals.

The authors of this contribution are dealing with the potential of applied algorithmization as a methodology of improving efficiency and accelerating the process of designing as well as program implementation of simulation models for the purpose of computer-based modeling and simulation of airport processes. At this simulation, quality is built upon on a precisely defined model of airport processes are set forth by the authors as part of the process of designing a modern Departure Control System (DCS) of airports, which currently designated for automation of a complex management of processes in the field of passenger and baggage handling, the airports offer to individual air carriers. The resulting algorithms designed for the separate separate processes of the DCS will help the authors understand real processes taking place at the airport with the aim to optimize the course of actions at the airport operation. A precisely built model of airport processes is the prerequisite of proper implementation of the simulation, pointing out both the advantages and disadvantages of this models and their implementation in practice.

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 authors of the contribution are submitting the actual results of a design and implementation of a modular and local departure control system of the IMARA system with a primary focus on low-cost airlines. The reader has presented an explanation of the services and functions currently realized solutions for check-in and gate clients at airport terminals along with the methods and technologies used for the implementation of the individual software modules of the system. The introduced system enables variable configurations of the separate workplaces employed at passenger check-in and airplane boarding. Its variability makes it possible to allocate workplaces either by the plan of operation or the actual needs of the passenger handling company. The solution realized by the authors can also be used for simulation of real operation when dealing with both the passenger and baggage handling processes.

The aim of the experiment is to evaluate an effect of industrially used plasma sprayed coatings of the TBC on the heat transfer into the refractory material designed for aeronautical applications. This study uses basic structural material of combustion chambers — components of turbine engines highly thermally stressed during the operation by flow of hot gasses. Using the hot gasses from the gas burner, the operational conditions inside the combustion chambers are simulated. The use of the TBC coating shows positive effect on the alloy overheating reduction. The results demonstrated decrease of the temperature with values in the range of hundreds of °C for materials covered with the TBC. This phenomenon can contribute to the development of the new types of aircraft engines with higher operational temperature and better fuel economics.

Positioning on Mars is one of the critical aspects of every planetary mission. Current complex planetary exploration systems (orbital and surface) rely on complex navigation and positioning systems, which make these systems complicated, expensive and their missions dangerous. The project of the global navigation satellite system for Mars (proposed system name – FATIMA) can make this and even future manned missions more safe, less expensive and the whole positioning in real time more reliable. The GNSS can be used by more systems or users simultaneously. In this research paper we focus on possible positioning errors when such a system is used. This research is focused on the GDOP – Geometric Dilution of Precision as one of the main factors influencing the GNSS.

This contribution presents an analysis and application of Kalman filtering in the field of autonomous and satellite navigation integration for a flying object. This paper deals with properties of the linearized Kalman filter, applied error models and test functionality of the proposed algorithm. An issue of the used and analyzed error models is related with analysis of the sensor properties. Errors for particular inertial measurement units are selected and their implementation to error model of Kalman filter is evaluated. Error characteristics is followed by the analyzed error models for navigation system integration. The article presents a partial solution of dissertation thesis “Integration architectures of navigation systems”, where analysis of Kalman filter leads to proposal of the integrated navigation system for UAV (Unmanned Aerial Vehicle).

Content of this contribution is a MATLAB solution of GPS satellite position evaluation based on generated navigation messages of the satellites. Article is focused on issues of the navigation message information content, ephemeris and data processing for evaluation of the Cartesian and spherical satellite constellation. Except analysis of mathematical solutions, the focus is on the position visualization using MATLAB environment. The issue of satellite position and estimation of the ground object position is closely linked with research of navigation architectures for autonomous and satellite navigation systems on Department of Avionics, Faculty of Aeronautics in Kosice. Given MATLAB solution, which is described in this article, is used for education and also as the basic simulation tool for more complex research of Unmanned Aerial Vehicles (UAV) navigation.

Content of this contribution is an issue of inertial sensors errors, specification of inertial measurement units and generating of test signals for Inertial Navigation System (INS). Given the different levels of navigation tasks, part of this contribution is comparison of the actual types of Inertial Measurement Units. Considering this comparison, there is proposed the way of solving inertial sensors errors and their modelling for low – cost inertial navigation applications. The last part is focused on mathematical testing and simulations of the inertial navigation. Given issue is a partial result, which is part of dissertation thesis Integration architectures of navigation systems.

Aviation ergatic systems models are used in the design of concrete aviation systems and their adequacy is evaluated in the process of their design. Generally, a concrete ergatic process is realised with the help of simulation technology. Computer systems of recent and perspective flight simulators contain the architectures of hybrid information systems. Due to this, analogue as well as discrete methods of estimation of ergatic systems parametric sensitivity do not lose their practical importance.

Passenger handling is one of the most important activities any passenger is obliged to carry out prior to boarding the plane to depart. For the handling process to be safeguarded, it is inevitable to perform the services involved in it fast and efficiently so as to prevent idle times or delays during the procedures potentially resulting in delay of flight. By gradual development of the so-called web-based information technologies, some of the activities involved in the handling process can be delegated to the passengers themselves, thereby achieving a faster course of the passenger handling process. In this contribution the authors are dealing with the status quo of the on-line web-based check-in process in air transportation forecasting the expected course of events in these services in the future. Next, based on analyzing functions and characteristics of similar solutions available in the market, the authors are putting forward their new proposal of their own design of a self-service, on-line system of passenger handling with the aim to simplify and expedite the entire handling process. It is the aim of the authors to develop a competitive design in terms of costs as well as new function and services not offered by the hitherto existing with emphasis on improving efficiency of passenger handling at the airports. The resulting solution thanks to internet based technologies is platform independent and fully applicable to the process of airport passenger handling. To an equal extent, the solutions are being applied by the authors to the educational process, as a training tool for the preparation of the aviation personnel and also as part of simulation models for research in the field of airport processes optimization.

The high reliability of automatic control systems of aircraft is reflected in the practical implementation in order to reduce an already small number of elements, for example, connecting functional element checking and control circuits. Each of the elements of control, which represents a control circuit, also performs the function of the sensor control. It is similar to the element-node connections and can be a wave form that is used for controlling. This is the way how to use converters that perform functions such as comparators from which the output control signal passes to the input power member. The converters, power members, signalling devices and indicators, as well as programming elements are usually placed in the critical nodes and they are elements of not only embedded system checkings, but also backup elements of the aircraft automatic control system.

Aim of this paper is to discuss possible method, applicable to diagnostics of complex thermodynamic systems, in our case, the small turbojet engine. Our motivation is based on the fact that, the development of utility properties of aviation technologies, its improvement i.e. accessibility to users cannot be done without detailed observation and tests. In aircraft engine design, 40% of the problems are solved by testing. Therefore the financial cost of the product testing significantly affects the economy of the design development, e.g. production of an aircraft engine. The economy problem of a product placement on the market deepens, if the time and energy consumption is considered. For this reason, reducing the price and time, which significantly affects the output application effect, is a task solvable only by rationalization and organization of testing procedures. When accepting these conditions, one of the possible methods of control of a small turbo jet engine is the utilization of thermography. In order to utilize the thermography to diagnose the engine, multiple processing steps are necessary. These steps include thermal image inference correction, image preprocessing, segmentation and correlation analysis. We discuss these steps further in the paper, with main aim on the image inference correction.

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.

Due to maintain the flow of the check-in process of air passengers, it is essential that services that ensure this process have been carried as quickly and effectively. One of the major current problems in this area is the efficiency of clearance of a large number of passengers over the check-in counters. By the gradual development of so-called self check-in services eventually delegate some activities in check-in process to passengers and the entire clearance process to speed up. In this article the authors deal with current state of the use of self check-in services in the world and predict the expected evolution of these services in the future. Subsequently, the authors present a new design of self-service kiosk and graphical user interface (GUI) of application such self-service check-in kiosk based on the analysis of the functions and features of similar solutions available on the market and with considering all currently known IATA requirements and the criteria relating to disabled passengers in order to lighten the load check-in counters and thereby accelerated the clearance of the passenger at the airport. The aim of the authors was to create a cost competitive solution offering such new features and services that do not offer other solutions, with an emphasis on improving the efficiency of the check-in process of passengers at the airport.

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 describes the results of error analysis of the new inertial measurement unit ADIS16364 produced by Analog Devices. This error analysis concerns stochastic sensor errors identified by the Allan variance method. In order to improve the performance of the inertial sensors, the users are keen to know more details about the noise components in each axis for a better modelling of the stochastic parts to improve the navigation solution. The main contribution of this paper is to present data necessary for further inertial sensors signal processing by means of Kalman filtering. Santrauka Straipsnyje pateikiami naujojo inercinio matavimų bloko ADIS16364 klaidų analizės rezultatai. Aprašyta klaidų analizė yra susijusi su stochastinio jutiklio klaidomis, nustatytomis Allano variacijos metodu. Siekiant pagerinti inercinių jutiklių našumą, naudotojai yra linkę daugiau sužinoti apie kiekvienoje ašyje esančius komponentus, kad būtų pagerintas stochastinių dalių modeliavimas bei rasti pažangesni navigacijos sprendimai. Šiuo darbu siekiama pristatyti duomenis, kurie yra reikalingi tolimesniam inercinių jutiklių signalų apdorojimui panaudojant Kalmano filtravimą. Reikšminiai žodžiai: inercinis matavimo blokas,klaidų analizė,Allano variacija,inercinio jutiklio klaidos