Pub Date : 2023-05-10DOI: 10.18287/2541-7533-2023-22-1-75-84
I. Kolesnikov, P. Koropets, D. Manturov, Ye. V. Shakhmatov
The features of a nonlinear model of the indenter-coating tribosystem of a tribometer are considered. It is shown that with an increase in the amplitude of harmonic perturbation, the dynamic system goes through the stage of doubling the cycle and passes into the regime of deterministic chaos. At the exit from chaos, it is possible to establish various synergistic regimes that stably retain their parameters even with a multiple decrease in the amplitude of the disturbance. A block diagram of the implementation of the evolutionary model is presented. As a result of the formation of equilibrium roughness, the motion of the system is a strange attractor. To substantiate the randomness of the strange attractor, an analysis of the amplitude-frequency characteristic of the ideal regenerative delay element with a gain factor less than unity, was carried out. The physical meaning of the strange attractor is that in a cyclic mode, a nonlinear dynamic system whose cycle time exceeds the period of natural oscillations by more than two orders of magnitude cannot come to the beginning of a new cycle with exactly the same parameters as to the beginning of the current cycle.
{"title":"Features of dynamic processes in the “indentor – coating” system during tests on a tribometer","authors":"I. Kolesnikov, P. Koropets, D. Manturov, Ye. V. Shakhmatov","doi":"10.18287/2541-7533-2023-22-1-75-84","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-1-75-84","url":null,"abstract":"The features of a nonlinear model of the indenter-coating tribosystem of a tribometer are considered. It is shown that with an increase in the amplitude of harmonic perturbation, the dynamic system goes through the stage of doubling the cycle and passes into the regime of deterministic chaos. At the exit from chaos, it is possible to establish various synergistic regimes that stably retain their parameters even with a multiple decrease in the amplitude of the disturbance. A block diagram of the implementation of the evolutionary model is presented. As a result of the formation of equilibrium roughness, the motion of the system is a strange attractor. To substantiate the randomness of the strange attractor, an analysis of the amplitude-frequency characteristic of the ideal regenerative delay element with a gain factor less than unity, was carried out. The physical meaning of the strange attractor is that in a cyclic mode, a nonlinear dynamic system whose cycle time exceeds the period of natural oscillations by more than two orders of magnitude cannot come to the beginning of a new cycle with exactly the same parameters as to the beginning of the current cycle.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127669929","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}
Pub Date : 2023-05-10DOI: 10.18287/2541-7533-2023-22-1-121-131
Перспективы Модернизации, Управления Процессом, Электрохимической Размерной, Обработки Профиля Пера, ПО Методу, Двухстороннего Копирования
The paper discusses the features of machining of a compressor blade airfoil. The problem of airfoil deformations under the action of residual stresses that negatively affect the accuracy of the relative position of the airfoil relative to the blade root is discussed. Methods of compensating for the effect of permanent deformations on the accuracy in blade machining and the impossibility of using this approach when the compressor blade is included in the duplex mode technology of electrochemical machining are specified. The analysis of the pattern of electrochemical machining of the blade airfoil with adjustment of the auxiliary technological base developed by the authors and the use of segmented electrodes showed the effectiveness of its use in order to compensate for airfoil deformations. We suggest measuring the interelectrode gaps in the machining chamber after refixturing the base in order to reduce the total machining time. We also suggest using the modernized electrochemical machining scheme when designing a CNC machine for the machining of a blade airfoil.
{"title":"Prospects of improving control over the process of electrochemical machining of the blade airfoil profile using the duplex mode method","authors":"Перспективы Модернизации, Управления Процессом, Электрохимической Размерной, Обработки Профиля Пера, ПО Методу, Двухстороннего Копирования","doi":"10.18287/2541-7533-2023-22-1-121-131","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-1-121-131","url":null,"abstract":"The paper discusses the features of machining of a compressor blade airfoil. The problem of airfoil deformations under the action of residual stresses that negatively affect the accuracy of the relative position of the airfoil relative to the blade root is discussed. Methods of compensating for the effect of permanent deformations on the accuracy in blade machining and the impossibility of using this approach when the compressor blade is included in the duplex mode technology of electrochemical machining are specified. The analysis of the pattern of electrochemical machining of the blade airfoil with adjustment of the auxiliary technological base developed by the authors and the use of segmented electrodes showed the effectiveness of its use in order to compensate for airfoil deformations. We suggest measuring the interelectrode gaps in the machining chamber after refixturing the base in order to reduce the total machining time. We also suggest using the modernized electrochemical machining scheme when designing a CNC machine for the machining of a blade airfoil.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133336347","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}
Pub Date : 2023-05-10DOI: 10.18287/2541-7533-2023-22-1-51-62
V. Blinov, I. Zubkov
The paper presents the results of one of the stages of creating a model of assessing and forecasting the operating characteristics of a transonic compressor due to erosive wear. A numerical model of a transonic compressor stage is constructed and verified to substantiate its applicability in calculating various degrees of blade erosive wear. The article contains a review of the basic approaches for turbulence simulation, their application area and basic features connected with 3D-flow simulation in turbomachines. The parameters and settings of the numerical model are shown. The CFD-obtained results are presented and compared with the experimental data and results of other researchers. By this comparison the accuracy of the CFD-obtained overall performance and the quality of modeling local processes are determined. Possible ways of improving the models accuracy are also specified.
{"title":"Verification of a transonic stage CFD model for assessing the erosion wear influence on the operation of the axial compressor","authors":"V. Blinov, I. Zubkov","doi":"10.18287/2541-7533-2023-22-1-51-62","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-1-51-62","url":null,"abstract":"The paper presents the results of one of the stages of creating a model of assessing and forecasting the operating characteristics of a transonic compressor due to erosive wear. A numerical model of a transonic compressor stage is constructed and verified to substantiate its applicability in calculating various degrees of blade erosive wear. The article contains a review of the basic approaches for turbulence simulation, their application area and basic features connected with 3D-flow simulation in turbomachines. The parameters and settings of the numerical model are shown. The CFD-obtained results are presented and compared with the experimental data and results of other researchers. By this comparison the accuracy of the CFD-obtained overall performance and the quality of modeling local processes are determined. Possible ways of improving the models accuracy are also specified.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117278381","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-97-108
V. S. But, A. Kobelev, S. Karpeev
Microcells were designed for subsequent modeling of piezoelectric and optical elements on their basis. The development of piezoelectric and optical elements from microcells was carried out and models were prepared for 3D printing. These designs can be used in practice as piezoacoustic or piezoelectric sensors if piezoelectric powder is added to their composition, for example, in ultrasonic flow meters, or used to create optical structures, for example, diffractive optical elements. The key characteristics and coefficients of piezoelectric structures, such as dielectric constant, conversion coefficient, dielectric loss coefficient, mechanical Q-factor, frequency constant, electromechanical coupling coefficient, piezoelectric charge coefficient, piezoelectric stress coefficient, elastic compliance coefficient, degradation rate, Curie point are analyzed. Elements produced by 3D printing will have properties different from those of elements produced by standard methods. These structures open up new opportunities for the development of ultrasonic research, mechanical engineering and instrument making.
{"title":"Development of microstructures for the formation of metamaterial properties of piezoelectric elements","authors":"V. S. But, A. Kobelev, S. Karpeev","doi":"10.18287/2541-7533-2022-21-4-97-108","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-97-108","url":null,"abstract":"Microcells were designed for subsequent modeling of piezoelectric and optical elements on their basis. The development of piezoelectric and optical elements from microcells was carried out and models were prepared for 3D printing. These designs can be used in practice as piezoacoustic or piezoelectric sensors if piezoelectric powder is added to their composition, for example, in ultrasonic flow meters, or used to create optical structures, for example, diffractive optical elements. The key characteristics and coefficients of piezoelectric structures, such as dielectric constant, conversion coefficient, dielectric loss coefficient, mechanical Q-factor, frequency constant, electromechanical coupling coefficient, piezoelectric charge coefficient, piezoelectric stress coefficient, elastic compliance coefficient, degradation rate, Curie point are analyzed. Elements produced by 3D printing will have properties different from those of elements produced by standard methods. These structures open up new opportunities for the development of ultrasonic research, mechanical engineering and instrument making.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128297903","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-33-43
S. L. Panchenko, T. V. Gras'ko
The tasks performed by modern military aircraft are currently expanding, as they are solved both in the air and in the aerospace, at high altitudes and at high flight speeds. However, in this case, the use of turbojet engines operation on aviation kerosene is not possible because of the high temperatures of aircraft structural elements due to aerodynamic heating that leads to the destruction of kerosene and the impossibility of using it as fuel. It is necessary to search for alternative fuel options, one of which is cryogenic fuel. This article substantiates the possibility of using cryogenic fuel, in particular hydrogen, for aerospace plane engines. Hydrogen has higher energetic qualities compared to aviation kerosene. The necessity of cooling the air before it enters the engine at high flight speeds of the aircraft has been proved. A design of the heat exchanger for cooling the air entering the compressor is proposed, and a method for its thermal calculation is developed, which is necessary when designing the structural layout of aerospace plane propulsion system.
{"title":"Methodology for thermal calculation of the heat exchanger for cooling the air at the intake of the aerospace plane engine compressor","authors":"S. L. Panchenko, T. V. Gras'ko","doi":"10.18287/2541-7533-2022-21-4-33-43","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-33-43","url":null,"abstract":"The tasks performed by modern military aircraft are currently expanding, as they are solved both in the air and in the aerospace, at high altitudes and at high flight speeds. However, in this case, the use of turbojet engines operation on aviation kerosene is not possible because of the high temperatures of aircraft structural elements due to aerodynamic heating that leads to the destruction of kerosene and the impossibility of using it as fuel. It is necessary to search for alternative fuel options, one of which is cryogenic fuel. This article substantiates the possibility of using cryogenic fuel, in particular hydrogen, for aerospace plane engines. Hydrogen has higher energetic qualities compared to aviation kerosene. The necessity of cooling the air before it enters the engine at high flight speeds of the aircraft has been proved. A design of the heat exchanger for cooling the air entering the compressor is proposed, and a method for its thermal calculation is developed, which is necessary when designing the structural layout of aerospace plane propulsion system.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130044879","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-44-51
D. Pushkarev, D. Y. Kiselev, Y. Kiselev
The possibility of using neural networks in aviation is shown, in particular in products intended for use in aviation technology. The possibility of using neural networks throughout the entire life cycle of aviation equipment products is analyzed. The advantages that can be obtained using neural networks are described. The main stages of creating a neural network model are analyzed and a description of each stage is presented. The difficulties associated with the practical application of models based on artificial intelligence are shown. The calculation of the operation of a lever-float valve is presented and a neural network model is made for its calculation using real operation and test data.
{"title":"Calculation of aircraft lever-float valves using neural networks","authors":"D. Pushkarev, D. Y. Kiselev, Y. Kiselev","doi":"10.18287/2541-7533-2022-21-4-44-51","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-44-51","url":null,"abstract":"The possibility of using neural networks in aviation is shown, in particular in products intended for use in aviation technology. The possibility of using neural networks throughout the entire life cycle of aviation equipment products is analyzed. The advantages that can be obtained using neural networks are described. The main stages of creating a neural network model are analyzed and a description of each stage is presented. The difficulties associated with the practical application of models based on artificial intelligence are shown. The calculation of the operation of a lever-float valve is presented and a neural network model is made for its calculation using real operation and test data.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134402824","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-88-96
N. M. Blazhnov, E. A. Borisenkova, M. Khardin
The paper provides a short review of the history of the development of native and foreign regulatory requirements of testing for sulfide stress corrosion cracking. Systematic ambiguity (duplicated in the reviewed regulatory requirements) in the choice of test environment parameters and its influence on the interpretation of the results was revealed. A series of laboratory tests, the purpose of which was to specify the choice of the most favorable combinations of parameters (pH2S/pH combinations) of the test medium was conducted.
{"title":"Resistance of products made of steel 20GL to sulfide stress corrosion cracking","authors":"N. M. Blazhnov, E. A. Borisenkova, M. Khardin","doi":"10.18287/2541-7533-2022-21-4-88-96","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-88-96","url":null,"abstract":"The paper provides a short review of the history of the development of native and foreign regulatory requirements of testing for sulfide stress corrosion cracking. Systematic ambiguity (duplicated in the reviewed regulatory requirements) in the choice of test environment parameters and its influence on the interpretation of the results was revealed. A series of laboratory tests, the purpose of which was to specify the choice of the most favorable combinations of parameters (pH2S/pH combinations) of the test medium was conducted.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121483684","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-76-87
E. V. Aryshensky, V. Aryshensky, A. Drits, F. Grechnikov, A. A. Ragazin
The study addresses the effect of thermal treatment on the mechanical properties and grain size of magnesium rich alloys with small scandium additions 1570, 1580 and 1590. The effect of preheat temperature (within 260440 С range) and soaking time (within 2 100 hours range) on yield strength, tensile strength and relative elongation of the alloys under investigation was analyzed. Mechanical properties were determined using uniaxial tensile tests in accordance with ISO 6892-1. In addition, for some modes the microstructure was studied for Al3Mg2 -phase presence and distribution by optical metallography methods depending on thermal treatment conditions. The studies demonstrated that supersaturated solid solution in the 1570 alloy decomposes faster in the entire studied temperature range, and after 48 hours soaking, its strength properties start degrading. At the same time, the 1580 and 1590 alloys are much more thermally stable, with slightly lower yield strength after long soaking time, while tensile strength remains unchanged. The conditions of 260 C annealing temperature are not favorable for plastic properties, severely degrading (due to -phase formation) in the 1570 and 1580 alloys. Plastic properties degradation is not so evident at higher soaking temperature, however, the 1590 alloy maintains the highest plasticity indices.
{"title":"Thermal treatment effect on the mechanical properties of 1570, 1580 and 1590 aluminum alloys","authors":"E. V. Aryshensky, V. Aryshensky, A. Drits, F. Grechnikov, A. A. Ragazin","doi":"10.18287/2541-7533-2022-21-4-76-87","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-76-87","url":null,"abstract":"The study addresses the effect of thermal treatment on the mechanical properties and grain size of magnesium rich alloys with small scandium additions 1570, 1580 and 1590. The effect of preheat temperature (within 260440 С range) and soaking time (within 2 100 hours range) on yield strength, tensile strength and relative elongation of the alloys under investigation was analyzed. Mechanical properties were determined using uniaxial tensile tests in accordance with ISO 6892-1. In addition, for some modes the microstructure was studied for Al3Mg2 -phase presence and distribution by optical metallography methods depending on thermal treatment conditions. The studies demonstrated that supersaturated solid solution in the 1570 alloy decomposes faster in the entire studied temperature range, and after 48 hours soaking, its strength properties start degrading. At the same time, the 1580 and 1590 alloys are much more thermally stable, with slightly lower yield strength after long soaking time, while tensile strength remains unchanged. The conditions of 260 C annealing temperature are not favorable for plastic properties, severely degrading (due to -phase formation) in the 1570 and 1580 alloys. Plastic properties degradation is not so evident at higher soaking temperature, however, the 1590 alloy maintains the highest plasticity indices.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127720538","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-66-75
A. S. Russkikh, V. Salmin
The article is devoted to the development of a methodology for designing a space transport system that has, in comparison with traditional injection scenarios, higher characteristics of the mass of the payload to be launched into high-energy orbits, including a geostationary one. The method is implemented by the systematization of design calculations and proposals for the rational design of interorbital vehicles with a combined propulsion system and the development of an algorithm for creating an electronic model of an interorbital vehicle in an automated designing PTC Creo system. The article considers algorithms for calculating the design parameters of the electric rocket transport module and ballistic parameters of the spacecraft flight to the target orbit. A method of forming conceptual design of an electric rocket transport module based on the obtained design parameters is also proposed. An electronic model of an electric rocket module was developed in a three-dimensional modeling system. The model displays the structural design of the module in accordance with the design parameters obtained and satisfies the design requirements imposed by other components of the space transport system. The proposed method makes it possible to design a space transport system that includes a DM upper stage and an electric rocket transport module designed to implement a combined payload injection scenario.
{"title":"Methodology of designing a space transport system including a “DM” chemical upper stage and an electric rocket transport module","authors":"A. S. Russkikh, V. Salmin","doi":"10.18287/2541-7533-2022-21-4-66-75","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-66-75","url":null,"abstract":"The article is devoted to the development of a methodology for designing a space transport system that has, in comparison with traditional injection scenarios, higher characteristics of the mass of the payload to be launched into high-energy orbits, including a geostationary one. The method is implemented by the systematization of design calculations and proposals for the rational design of interorbital vehicles with a combined propulsion system and the development of an algorithm for creating an electronic model of an interorbital vehicle in an automated designing PTC Creo system. The article considers algorithms for calculating the design parameters of the electric rocket transport module and ballistic parameters of the spacecraft flight to the target orbit. A method of forming conceptual design of an electric rocket transport module based on the obtained design parameters is also proposed. An electronic model of an electric rocket module was developed in a three-dimensional modeling system. The model displays the structural design of the module in accordance with the design parameters obtained and satisfies the design requirements imposed by other components of the space transport system. The proposed method makes it possible to design a space transport system that includes a DM upper stage and an electric rocket transport module designed to implement a combined payload injection scenario.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"2007 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127308133","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}
Pub Date : 2023-01-18DOI: 10.18287/2541-7533-2022-21-4-118-130
V. A. Romanenko
Approximate analytical models are proposed for two types of multi-channel queuing systems with partial mutual assistance between channels and waiting in limited-size and unbounded queues. The incoming flow of requests is a superposition of several simplest flows. It is assumed that normative numbers of channels for servicing a customer that differ depending on the flow of incoming customer requests are established. In the systems of the first type the normative number of channels is not necessary: a customer is accepted for servicing if there are free channels in the system and the number of channels is smaller than the normative one. Service time is distributed exponentially with the average inversely proportional to the number of allocated channels. In systems of the second type the service of a customer is always performed by the channels of the normative number. Service time can be distributed arbitrarily (not only exponentially) with the average irrespective of the number of allocated channels. The paper presents the results of comparative analysis of the results of dealing with some tasks of designing service systems in a wide range of input data using simulation modelling and calculations based on approximate analytical models that allowed evaluating the application area of the latter and making a conclusion about their satisfactory accuracy. Examples of the use of models of technological processes of airport ground handling as queuing systems of the considered types are given.
{"title":"Approximate models of air transport queueing systems with partial mutual assistance between service channels","authors":"V. A. Romanenko","doi":"10.18287/2541-7533-2022-21-4-118-130","DOIUrl":"https://doi.org/10.18287/2541-7533-2022-21-4-118-130","url":null,"abstract":"Approximate analytical models are proposed for two types of multi-channel queuing systems with partial mutual assistance between channels and waiting in limited-size and unbounded queues. The incoming flow of requests is a superposition of several simplest flows. It is assumed that normative numbers of channels for servicing a customer that differ depending on the flow of incoming customer requests are established. In the systems of the first type the normative number of channels is not necessary: a customer is accepted for servicing if there are free channels in the system and the number of channels is smaller than the normative one. Service time is distributed exponentially with the average inversely proportional to the number of allocated channels. In systems of the second type the service of a customer is always performed by the channels of the normative number. Service time can be distributed arbitrarily (not only exponentially) with the average irrespective of the number of allocated channels. The paper presents the results of comparative analysis of the results of dealing with some tasks of designing service systems in a wide range of input data using simulation modelling and calculations based on approximate analytical models that allowed evaluating the application area of the latter and making a conclusion about their satisfactory accuracy. Examples of the use of models of technological processes of airport ground handling as queuing systems of the considered types are given.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123870530","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}
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