Aerospace technic and technology最新文献

{"title":"Air traffic control students’ aspiration levels distributions","authors":"S. Borsuk, O. Reva, L. Sahanovska","doi":"10.32620/aktt.2023.3.08","DOIUrl":"https://doi.org/10.32620/aktt.2023.3.08","url":null,"abstract":"This paper proposes an analysis of an air traffic control students’ survey describing self-assessment of their workload levels. The workload is defined as the number of aircraft simultaneously under control. The survey is performed over the gird with axes represented with aircraft number, their correspondent, and utility/satisfaction levels. The aspiration level values are calculated using workload differences. The safety background of risks in aviation activities is described. Risk and aspiration level links are highlighted. The aspiration level notion for the proposed research is inferred. Survey details and conditions are explained. The differences in four quarters at the workload charts specified by respondents are explained. The aspiration level parameters and basic statistics calculated for respondents are presented. Appropriate goodness-of-fit tests are performed with different sets of initially received answers. Whole samples and subsamples are considered. It is shown that for the full sample considered, the outlet removal provides significant increase of p-value, thus allowing to change the hypothesis approval status. Sub-samples list includes the whole sample without outlets and the whole sample aspiration level calculated for only positive values according to y-axis. Additionally, other values were considered. Namely regret values, i.e., the values on the descending half of the charts and a mixture of regret and aspiration level values in regard that is higher. Normal and exponential distribution significances are proven for the different options mentioned above. It is shown that the general chi-squared method provides the latter mixture to be insignificantly exponential, whereas specific Fisher’s test approves the significance of the data. The role of air traffic control students’ aspiration level in their estimation and possible education strategy personalization is described. The importance of human factor consideration during similar survey performance is once again proven. The connection of regret with aspiration level in a mixture is discussed. The conclusions on the results are provided. Further research directions are proposed.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114487834","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Unsteady incompressible laminar boundary layer: time and space variable molecular viscosity","authors":"P. Lukianov, L. Song","doi":"10.32620/aktt.2023.3.06","DOIUrl":"https://doi.org/10.32620/aktt.2023.3.06","url":null,"abstract":"The subject of this work is two approaches to describe the laminar unsteady flow of an incompressible fluid in the boundary layer. In the first approach, the viscosity of the fluid and the acceleration with which the plane is set in motion are considered constant. In essence, this is Rayleigh's problem. The solution obtained on the basis of these assumptions asymptotically converges to the well-known self-similar Stokes solution. It is important that the solutions of Stokes and Rayleigh asymptotically at large values of time correspond to the disappearance of shear stresses between the liquid and moving plane after acceleration. A paradox emerges the equations derived by Stokes to describe internal friction indicate the absence of the same friction between a moving body and fluid. Since research using the calculus of variation methods revealed that the molecular viscosity inside the stationary boundary layer should depend on the distance to the moving surface, the corresponding non-steady problem was considered. As a result, as before for the steady case, solutions describing both non-gradient and gradient flows of incompressible fluid in the boundary layer are obtained. The asymptotic analysis of the transition to steady flow testifies the consistency of these solutions. For the case of non-gradient flow, a comparison of the classical solution with the solution corresponding to the extreme fluid flow rate carried by the moving surface is made. It is shown that according to the solution obtained on the basis of the calculus of variation approach, the shear stress on the surface does not disappear anywhere after the motion becomes steady but, as expected, acquires a constant value. The research methods are purely theoretical and the results are analyzed by comparison with available theoretical and experimental data and compliance with the fundamental laws of physics, in particular the law of conservation of energy. These methods are based on the construction of analytical mathematical models, which are differential equations in partial derivatives supplemented with appropriate physical initial and boundary conditions. In addition, Euler's differential equations for the extreme of functional theory are used (in this paper, this is the extreme of fluid flow rate across the cross-section of the boundary layer). When solving these equations, the well-known Fourier method of variable separation is used. Arbitrary functions of time arising during partial integration (by one of the variables – the spatial coordinate) are determined from the conditions of asymptotic convergence of the solutions of non-steady problems to the corresponding solutions of steady problems. Conclusions. The presented results are of fundamental importance for understanding the physics of the flow around aircraft parts, as they indicate the contradiction of the existing idea of the reversibility of direct and inverse problems: the motion of a body in a still fluid and the flow of ","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"74 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125905154","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Структурні особливості детонаційного потоку","authors":"O.S. Aksonov, O.E. Zolotko","doi":"10.32620/aktt.2023.3.05","DOIUrl":"https://doi.org/10.32620/aktt.2023.3.05","url":null,"abstract":"The subject of this research is the processes that occur during the formation and propagation of a detonation wave in a flat channel. The goal of this work is to study the features of the complex multiform structure of the detonation wave and its influence on the integral parameters of the detonation flow. The task of the research was to identify regularities during the formation process and propagation of the detonation wavefront, establish the nature of the influence of the detonation front structure on the processes that occur in the zone of stable flow parameters, and analyze the gas-dynamic parameters of the flow at the final stage of the process - at the stage of propagation of rarefaction waves. The main research method is mathematical simulation using CFD technologies (ANSYS Fluent package). The main results of the study: it was established that the values of gas-dynamic parameters at the triple points of shock waves are significantly greater than the corresponding values at the Neumann peak, and in the areas between the triple points are significantly smaller; the values of the parameters averaged over the cross-section of the detonation wave front almost do not differ from the values of the parameters at the Neumann peak; the propagation velocity of the detonation wave averaged over the cross-section of the flow also corresponds to the calculated velocity according to the Chapman-Jouguet model; outside the zone of chemical reaction, the formation of triple configurations is impossible, therefore the speed of the detonation wave front will be lower than the values of Chapman-Jouguet, which will affect the further processes of propagation of the detonation; the processes of formation and propagation of the detonation wave front in a certain way influence the distribution of steady flow parameters, while the wave processes spread to the Taylor zone, which leads to significant turbulence of the wall layer; due to the turbulence of the wall layer, the intensity of convective heat fluxes into the channel wall increases. Conclusion: the obtained results are in good agreement with the results of known experimental studies and can be used in the calculation of the integral impulse characteristics of the detonation engine chamber and in the design of its cooling system.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125083574","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Підвищення ефективності робочого циклу паливного шестерного насоса високого тиску за рахунок використання струминного насоса в якості ступеня підкачування","authors":"I. Romanenko, Oleksandr Bilohub","doi":"10.32620/aktt.2023.2.04","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.04","url":null,"abstract":"This article analyzes the possibility of increasing the efficiency of the gear pump operating cycle by using a jet pump as a booster stage. The design of gear pumps is performed for one mode, and most often, it is a mode with minimum speed and high consumption relative to rotation speed. For gas turbine engines, this is the take-off mode, in which the aircraft operates for a few minutes of the entire flight cycle. In other modes, the pump capacity is excessive, reaching more than twice the value in some operational conditions. Due to the excess capacity, overflow valves are used to synchronize the operation of the engine and pump. This approach is a classic solution, but it creates additional mechanical losses and, as a result, reduces the efficiency of the operating cycle of the pump. Therefore, there is a need to improve the matching of engine requirements and pump performance. In this article, a solution that can improve the operating cycle of pumping units within the framework of a classical drive box assembly was analyzed. In the introductory section, the generalized flight cycle of a transport aircraft is analyzed. Based on the results, the modes were determined for which the design calculations of the jet pump were performed. First, the relative characteristics of pressure increase and efficiency are considered. The geometric and operational boundary conditions are accepted considering the fuel overflow relative to the generalized flight cycle. The obtained characteristics are used as a basis for selecting the geometric ratio for the modes with the highest pressure and efficiency. Based on these results, the geometric dimensions of the main sections and the value of the pressure increase at the outlet of the jet pump were obtained. Based on the characteristics of the pressure increase behind the jet pump, the relative characteristics of the reduction in power consumption in the gear pump shaft were obtained. Considering the level of overflow and operating time, the use of a jet pump will save about 50% of the energy input. This is a direct improvement in the operating cycle, and the increased pump inlet pressure will also reduce bearing wear, increase cavitation resistance, and reduce wear from cavitation erosion.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131832433","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A method for reducing parasite drag of medium transport helicopter","authors":"Mykhaylo Kybalnyy, Oleksii Prytula, Sergii Degtiarenko, Kateryna Izviekova","doi":"10.32620/aktt.2023.2.05","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.05","url":null,"abstract":"At present, more and more stringent emission requirements are being imposed on helicopters. Carbon dioxide emissions are a function of fuel consumption, and fuel consumption is directly dependent on the power required for a helicopter cruise flight. The power, required for horizontal flight of a helicopter directly depends on the design of the fuselage and other non-lifting elements, and accordingly, on parasite drag. Therefore, the desire to reduce parasite drag is expected and understandable. Helicopter parasite drag reduction was hailed as one of the key topics of the Seventh Clean Sky Framework Conference. For sixty years of research on this topic, a tremendous amount of experience has been accumulated. In particular, it was found that the main contributors to the total parasite drag of the helicopter were the main rotor hub and swashplate. The subject matter of this article is the study of the parasite drag of the hub and swashplate of a medium passager/transport helicopter Mi-8/17. This study aimed to develop methods to reduce the parasite drag of the Mi-8/17 helicopter. Mi-8/17 is the most mass-produced twin-engine helicopter in the world. Currently, more than 4,5 thousand units are in operation around the world. Therefore, the task of reducing parasite drag for this helicopter is very relevant. Modern methods of computation fluid dynamics (CFD) are used. Modern methods of computational fluid dynamics with an acceptable degree of accuracy make it possible to consider the interference phenomena of the components of the hub, swashplate, and helicopter fuselage, which is not always possible, to obtain correctly during expensive wind tunnel tests. During the work, the following results were obtained. An analysis was made of the contribution of each element of the design of the hub and the main rotor swashplate to the total parasite drag. A method for reducing the parasite drag of a helicopter using a mast fairing is proposed. Several variants of the mast fairing were considered, and the most effective one was chosen. The effect, as well as its degree of influence, of the airflow blown by the fan cooling the air-oil radiators, on the general parasite drag of the helicopter was revealed. The results of the studies, given in this article have been implemented in the production.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"108 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127061183","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Preliminary analysis of noisy image lossy compression by discrete atomic transform-based coder","authors":"Viktor O. Makarichev, B. Kovalenko, V. Lukin","doi":"10.32620/aktt.2023.2.07","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.07","url":null,"abstract":"Remote sensing provides data (images) important for many modern applications. Image number and average size tend to increase. This makes their transfer via communication lines, storage, and dissemination problematic. Thus, compression should be applied where lossy compression is mostly used. Most methods of lossy compression assume that images do not contain noise. Meanwhile, images are often noisy, and this should be considered in the design and performance analysis of image compression techniques. Lossy compression has already been studied by several coders. However, it has not been investigated for the recently proposed atomic transform-based techniques that possess several advantages, in particular, the ability to provide privacy of compressed data. The main subject of this paper is the peculiarities of noisy image lossy compression by an atomic transform-based coder. Our goal is to analyze whether the considered compression method provides the noise filtering effect and the so-called optimal operation point. The task is to obtain rated distortion curves for the atomic transform-based coder applied to noisy images and to analyze their behavior for several performance characteristics such as quality metrics and compression ratio. In the first order, the monotonicity of the main dependence is of interest. The main results are as follows. First, it is shown that the dependencies have non-monotonic behavior and the appearance of analogs of optimal operation point is possible, at least, for such metric as maximal absolute error. Second, there is a specific dependence of compression ratio on a parameter called UBMAD that controls compression. Experiments have been performed on several noisy test images having different complexity and contaminated by noise of different intensities. In conclusion, it is demonstrated that one more coder might have optimal operation points for images having a rather simple structure. However, at the moment, it is difficult to predict its existence and the corresponding coder parameters.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"91 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126046780","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Аналіз випадків державного тероризму щодо повітряних суден цивільної авіації","authors":"Vadym Stratonov, A. Musiienko, A. Ruban, Veronika Parokinna, Maksym Galata","doi":"10.32620/aktt.2023.2.01","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.01","url":null,"abstract":"The subject matter of study in the scientific article is cases of state terrorism (ST) that were committed against civil aviation aircraft. The goal is to conduct a comprehensive analysis of acts of unlawful interference related to ST. The tasks to be solved are: to analyze cases of ST against civil aviation objects, determine patterns and factors that contribute to ST, determine potential methods of implementation of acts of ST against civil aviation in the future, and propose recommendations for countering acts of unlawful interference and promising directions for future research. The methods used are: analysis, comparison, and generalization. The following results were obtained. Because of the conducted research, we have determined a list of ST acts committed against civil aviation facilities. The main methods and means of ST were determined during the analysis of the specified cases. By comparing the ways of performing these acts of unlawful interference and the existing means and measures to prevent terrorist attacks in civil aviation, a hypothesis was put forward that potential acts of ST against civil aviation in the future will have a hybrid nature. We have considered potential sources of danger. Among such threats are some countries that, pursuing their political goals, can use some methods: recruitment of employees of airport complexes; use of portable anti-aircraft missile systems; use of weapons and other devices manufactured using technologies that will prevent their detection. Among the measures that require constant control are also: inspections regarding possible connections of employees of civil aviation facilities with terrorist states or their representatives and constant maintenance of effective communication between airline management and the department of civil aviation in order to exchange information on possible cases of terrorist attacks. Conclusions. The scientific novelty of the results obtained is as follows: cases of ST committed against civil aviation facilities were analyzed; the main danger of committing acts of ST came from dictatorial regimes trying to achieve their political goals; we have proposed a list of hybrid threats that may become the main methods of conducting acts of terrorism in the coming years; we have identified areas of research, the results of which will help to increase the level of protection of terrorist acts related to ST.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132167440","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Вплив форми крила на характеристики при використанні інтегрованої роторної силової установки літака","authors":"Bohdan Komarov, Dmytro Zinchenko, Oleksandr Andrieiev","doi":"10.32620/aktt.2023.2.02","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.02","url":null,"abstract":"The subject of the study is the optimization of aerodynamic characteristics by improving the wing profile shape for the fan-wing configuration. The aim of this work is to find a more universal wing shape suitable for various aircraft. The task is to compare the characteristics of three wings with the same rotor engine installed in the nose section, including the base wing used in most previous studies by scientists. Sources suggested that this profile is not well-suited for rotor engines with a large aspect ratio. Experimental methods were used to measure the dynamic characteristics of three wing profiles: a flat curved profile with a cut-out in the rear wing section, a flat lower surface profile, an S-shaped profile with a lower surface bend in the rotor area, and a two-bend contour with a cut-out in the rear wing section on top and bottom. The results showed an improvement in characteristics compared with wing-rotor engine schemes used in previous cases. Specifically, an increase in the flow velocity at the wing exit of 3...8 % depending on the power plant operating mode was found, which led to an increase in lift up to 20 % depending on the flight mode, and an increase in thrust up to 16 %. Conclusions. The proposed S-shaped profile with a lower surface bend in the area of the rotor hub, and a profile with two bends in the contour with a cut in the rear part of the wing from the top and bottom contours have the most optimal and balanced characteristics. In the future, it is planned to manufacture these profiles using composite materials to reduce weight and install them on the aircraft prototype, replacing the rotor structure with a more flexible one using more flexible materials such as PETG plastic for the synchronization of the installed rotor motors, which is necessary to increase reliability and backup the rotor drive. Additionally, several sections with independent engines are planned to be made on each wing console to counteract rotor rupture in the event of engine failure. Due to significant advantages over the standard profile shape and minor structural complexity, the manufacture of more complex profile shapes can find wide applications in aircraft designed according to the fan-wing scheme.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"72 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125216788","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Дистанційне зондування як ефективний інструмент проєктування доріг","authors":"Svitlana Danshyna, Sergey Andrieiev","doi":"10.32620/aktt.2023.2.08","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.08","url":null,"abstract":"The subject of this study is the process of engineering and geodetic surveys for developing road projects. The purpose of this article is to improve the efficiency of the process of engineering and geodetic research in road design by implementing remote data from various sources and their systematization and algorithmization of use. The task is to analyze the preparatory and field stages of the process to determine possible ways of increasing its efficiency. Focusing on information flows, to develop an information model of the process of engineering and geodetic surveys and the corresponding scientific and methodological support for road design to introduce advanced technologies for collecting data about the terrain, which reduce the time of surveys and increase the accuracy of the results obtained. For this, the following methods are used: system and structural analysis, set theory, and DFD modeling. Scientific results have been obtained. The requirements of the current legislation regarding searches and the best experience of their conduct have been systematized. A set-theoretic model of information flows of the process of engineering and geodetic surveys is proposed, with the involvement of structural modeling approaches that make it possible to combine remote data from different sources and consider the dynamics of their changes and the logic of interaction. The IDEF0 model, which considers remote sensing data as a source of accurate and up-to-date information, has been developed, and the data flow diagram algorithmizes the mechanism of their combination to obtain the necessary topographical and geodetic materials. The developed scientific and methodical support for information support of road design creates a structure of information technology for engineering and geodetic surveys. Its experimental use has confirmed the reduction of the time for performing geodetic works while simultaneously increasing the accuracy of the obtained geometric and geodetic parameters, which are necessary for the formation of objective conclusions when forming the estimate of the road project, determining the scope of works, etc. Conclusions. The results of the bibliographic search confirmed that the effectiveness of the topographic-geodetic survey procedure in road design is complicated by the large size of the geographical areas to be surveyed, complex engineering and geological conditions, or the presence of restrictions on the duration of work and financial resources. This leads to the need to practically implement into the project-research organizations new approaches based on highly productive methods of collecting information about the area. The scientific and methodological provision of information support for road design has been developed, in particular, the structure of the information technology of engineering and geodetic surveys. Its experimental use has confirmed the reduction of the time required to perform searches and the improvement of the acc","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127078563","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Моделювання комплексного формування запасів військової техніки в зоні воєнного конфлікту з використанням компонентного методу","authors":"Oleg Fedorovych, L. Lutai, Yuliia Malieieva, Iaroslav Zamirets, Tetiana Pisklova","doi":"10.32620/aktt.2023.2.06","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.06","url":null,"abstract":"The task of researching the multi-component composition of military equipment (tanks, artillery, aviation equipment, etc.) for supplying and forming the necessary stockpiles of weapons and their components in the military conflict zone to establish military parity of forces, is developed and solved. The research relevance is related to a comprehensive solution to the problem of forming the necessary stockpiles of weapons and their components in the combat zone, under the conditions of military threats. The purpose of this study is to use the component method to represent weapons and their components in the process of complex supply of military equipment to the combat zone for creating military parity of forces. The problems of the supply of weapons and their components in martial law conditions, which are associated with the complex multi-component structure of military equipment, the limited capabilities of manufacturers and suppliers of weapons, and the logistical risks of supply in conditions of military threats, are analyzed. A multi-layered component structure of military equipment is proposed for the systematic presentation of weapons and their components in the process of supply and formation of reserves in the combat zone. The logistics of the weapons and their component supply from army warehouses and military equipment from manufacturers’ warehouses are analyzed. The limited capabilities of manufacturers and suppliers of military equipment lead to the complication of the formation of necessary military equipment stockpiles in the military conflict zone, which can affect the nature of hostilities (transition from offensive to defensive actions). The lack of military equipment leads to the need to form defense orders for the creation and production of new types of weapons, including those with increased combat capability characteristics (range, accuracy, damage zone, etc.). Therefore, for the creation of new weapons or the modernization of existing models, it is proposed to use the multi-component architecture of a modern model of military equipment, considering the possible types of components (reusable, adaptive, new). An algorithm for the formation of a multi-component and multi-layered architecture of modern weapons using a precedent approach is proposed. For this, a precedent database is created, which is used to search for existing reusable components. Both quantitative and qualitative assessments of proximity are used in the process of searching in the database of precedents to assess the proximity of components. The model was created to optimize the logistic costs of supplying weapons and their components to the combat zone. The quantities of weapons and their components, the time of supply, and the risks of supply in conditions of military threats are used as supply indicators. The requirements for the supply of military equipment in the conditions of the risks of martial law are formed. The scientific novelty of the study is rel","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"92 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125003924","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}