The paper undertakes the problem of managing exploitation support of aviation equipment in terms of spare parts and subassemblies taking into account variable conditions, resulting from different intensity of aircraft and helicopter operation. It covers the practical aspects of planning stocks of material resources in connection with the applicable operating systems and failure of aircraft at the airbase level. By using statistical elements and probabilistic models it indicates the possibility of increasing the availability of parts and aircraft components, which in the long run will make a positive impact on the level of equipment technical efficiency. The article points to the need to minimize the expenditure involved and to avoid redundant, useless aircraft spare parts and components. Therefore, it is aimed at increasing the efficiency of material management, improving safety and developing exploitation systems in terms of technical reliability.
This manuscript was dedicated to the IT logistics and operation support system of technical facilities in the military. At the beginning, there was a brief description of the integrated ZWSI RON IT system’s genesis and a characterization of the basic functions of the aforementioned system. The advantages of the IT system have been highlighted, which facilitates the process of controlling the logistics and the operation of technical facilities. Attention was also drawn to the key issues related to the analysis of primary operational characteristics, such as readiness, weapon reliability and military equipment. In the end, a proposal to solve the identified operational problems was submitted by formulating the assumptions for a modern IT system for the Polish Armed Forces.
The paper describes issues related to reliability of military vehicles based on recorded operational events. Seeking the quantification of reliability for exploiting vehicles in military units, an extensive analysis of factors shaping the reliability level was made, taking into consideration all phases of military vehicles existence and a peculiar character of the exploitation process of military vehicles. The importance of reliability research in the decision process optimization was emphasized, controlling the efficiency and availability of the exploitation system.
The paper presents the accuracy results of aircraft positioning using the DGLONASS method in the GBAS augmentation system in air transport. In the research test, the coordinates of Cessna 172 aircraft were recovered on the basis of the DGLONASS technique. The calculations were executed in RTKLIB software in RTKPOST library in module “DGPS/DGNSS”. The raw GLONASS data from the onboard Topcon HiperPro receiver and also from the REF1 physical reference station were utilized in the research test. In the paper, the standard deviations of aircraft coordinates and integrity HPL and VPL parameters were presented and described. In the paper, the obtained aircraft coordinates from the DGLONASS method were compared and verified with the DGPS solution. For this purpose, the RMS-3D term and difference of ellipsoidal height of aircraft were estimated in the paper. The average value of RMS-3D equals to 1.71 m, however the difference of ellipsoidal height amounts to 1.46 m, respectively.
Along with the growing technology, helicopters are equipped with increasingly complex avionics and operational control systems. Such devices use a variety of input signals in order to enhance their performance. Owing to the use of electronic control systems, modern helicopters have a wide range of possibilities, both in terms of manoeuvrability and combat. The article presents a case study of designing equipment control systems on the example of a radio altimeter, which is mounted onboard the W-3 “Sokół” helicopter. The primary assumption was to design a fuzzy controller using FuzzyLogic Toolbox in the Matlab software package that will facilitate similar results, and, above all, will eliminate the altitude measurement error resulting from the bank of a helicopter.
The article is a continuation of research into a stabilization system for the Unmanned Aerial Vehicle of vertical takeoff and landing. The stabilization system was designed on the basis of a fuzzy logic Mamdani type controller. In the framework of the research, the authors built a test stand with a Multi Rotor model, which allows “Hardware In The Loop” testing in real time. The control system was written in the Matlab/Simulink software and implemented to the Arduino microcontroller.
The article discusses the possibility of armour penetration by PGU 14 API shells fired from the GAU-8/A cannon. The considerations focus on questions with regard to the probability of armour penetration with the initially established conditions in the project. In the analysis, the authors took into account three parameters: armour thickness, armour slope and target distance. Based on the initial parameters, the authors estimated the probability of armour penetration. The designed a fuzzy expert system in the MATLAB software as well as conducting simulation of its performance in the Simulink programmes. The authors presented the performance of the system based on twenty samples for research, which simulate different thickness of the target armour, different distance from the target and different slope of the armour. The authors presented control surfaces, due to which it is possible to analyse the system performance. They also show the simulation process in the Simulink software package with the preset values. On the basis of the created controller, it is clear that a well-developed system, which had undergone testing and optimization, is capable of calculating near reality probability values. The designed system might improve fire effectiveness of ground targets during air training and combat tasks, as well as optimizing the consumption of air-to-ground armour piercing (AP) shells.
The paper attempts to present the current state of knowledge in the use of fuzzy logic in order to assess the reliability of technical objects over the past two decades. In world literature, one can recall three main trends related to the use of fuzzy logic in the reliability estimation. The first one deals mainly with an analysis and assessment of the risk of failure. In the second mainstream, the researchers try to analyse the human factor, which also influences system malfunction. The third group of reliability studies the possibility of using fuzzy logic for proper service planning and thus preventing damage. In each of the three mentioned trends, fuzzy logic complements the classic methods of estimating and predicting reliability.
The article deals with the subject of diagnosing the current system of pilot training on multi-role aircraft in Poland. The authors pay particular attention to changes in its organization, arising from the compromise between technology, needs and funds on the part of the organizers. The recommended perspective changes in its organization in Poland result from the past three years of research in the Air Force University and institutions engaged in the discussed issues. The issues continue the research process handled in the dissertation , resulting from analyses and comparisons with world trends in this respect. The obtained findings suggest that it is essential to achieve the planned outcomes of training pilots on multi-role aircraft, at the same time reducing time and costs. It is linked to the introduction of modern aircraft or equipment supporting the process of pilot training.
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.