Pub Date : 2023-12-28DOI: 10.18287/2541-7533-2023-22-4-86-98
A. Y. Myasnikov
The article presents theoretical foundations of designing the components of an aircraft onboard cable network, proposed as a methodology for solving the problems of designing onboard equipment. The composition of the initial and developed technical documentation for the aircraft onboard cable network is determined. The article also shows the relationship between the stages of designing the onboard cable network and the stages of designing the aircraft. The formulation of the general task of creating the components of an onboard cable network is presented as a number of particular subtasks of a lower level of complexity. The method for solving the problem is based on a number of transformations performed with the original documentation in order to develop technical documentation for the introduction of the onboard system into the complex of onboard equipment. A number of successive transformations of the proposed bundle model using the apparatus of topology and multiset theory made it possible to form a model of the components of the onboard cable network of an aircraft that gives a detailed view of its future design. The proposed scientific approach to the design of aircraft onboard cable network components created the prerequisites for minimizing the heuristic component in the process of designing aircraft onboard cable network components.
{"title":"Theoretical aspects of designing the components of an aircraft onboard cable network","authors":"A. Y. Myasnikov","doi":"10.18287/2541-7533-2023-22-4-86-98","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-4-86-98","url":null,"abstract":"The article presents theoretical foundations of designing the components of an aircraft onboard cable network, proposed as a methodology for solving the problems of designing onboard equipment. The composition of the initial and developed technical documentation for the aircraft onboard cable network is determined. The article also shows the relationship between the stages of designing the onboard cable network and the stages of designing the aircraft. The formulation of the general task of creating the components of an onboard cable network is presented as a number of particular subtasks of a lower level of complexity. The method for solving the problem is based on a number of transformations performed with the original documentation in order to develop technical documentation for the introduction of the onboard system into the complex of onboard equipment. A number of successive transformations of the proposed bundle model using the apparatus of topology and multiset theory made it possible to form a model of the components of the onboard cable network of an aircraft that gives a detailed view of its future design. The proposed scientific approach to the design of aircraft onboard cable network components created the prerequisites for minimizing the heuristic component in the process of designing aircraft onboard cable network components.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"7 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-12-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139150680","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 : 2023-12-28DOI: 10.18287/2541-7533-2023-22-4-99-111
V. V. Eremenko, A. E. Mikhailov, A. B. Mikhailova, M. O. Goryukhin, D. Krasnoperov
The accuracy of a CFD model of a turbo-machine might depend on a number of factors: turbulence model, quality of the mesh model, boundary conditions, solver settings, consideration of secondary geometric factors, etc. The purpose of this work is to develop practical recommendations for CFD calculations of centrifugal compressors based on the validation of a model of NASA High Efficiency Centrifugal Compressor experimental radial compressor stage. Results of a grid independence test are presented, and the optimal grid size for the High Efficiency Centrifugal Compressor stage is identified as comprising 3 million elements. CFD-calculations of an experimental stage were performed with different turbulence models. The obtained data was compared with the NASA experimental data considering integral (total pressure ratio, mass flow rate, adiabatic efficiency) and differential parameters (static pressure distribution downstream the vaned diffuser). The required CFD computational time for different turbulence models was calculated. Based on the results of this research, recommendations were formulated for the application of SST, k–ε, BSL EARSM and GEKO turbulence models for numerical modeling of centrifugal compressors.
涡轮压缩机 CFD 模型的精度可能取决于多个因素：湍流模型、网格模型质量、边界条件、求解器设置、次要几何因素考虑等。这项工作的目的是根据 NASA 高效离心压缩机实验性径向压缩机级模型的验证结果，为离心压缩机的 CFD 计算提出实用建议。本文介绍了网格独立性测试的结果，并确定了高效离心压缩机级的最佳网格大小为 300 万个元素。使用不同的湍流模型对实验级进行了 CFD 计算。考虑到积分参数（总压比、质量流量、绝热效率）和微分参数（叶片扩散器下游的静压分布），将所获得的数据与 NASA 的实验数据进行了比较。计算了不同湍流模型所需的 CFD 计算时间。根据研究结果，提出了应用 SST、k-ε、BSL EARSM 和 GEKO 湍流模型进行离心压缩机数值建模的建议。
{"title":"Comparative analysis of turbulence model influence in numerical simulation of an experimental radial compressor stage","authors":"V. V. Eremenko, A. E. Mikhailov, A. B. Mikhailova, M. O. Goryukhin, D. Krasnoperov","doi":"10.18287/2541-7533-2023-22-4-99-111","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-4-99-111","url":null,"abstract":"The accuracy of a CFD model of a turbo-machine might depend on a number of factors: turbulence model, quality of the mesh model, boundary conditions, solver settings, consideration of secondary geometric factors, etc. The purpose of this work is to develop practical recommendations for CFD calculations of centrifugal compressors based on the validation of a model of NASA High Efficiency Centrifugal Compressor experimental radial compressor stage. Results of a grid independence test are presented, and the optimal grid size for the High Efficiency Centrifugal Compressor stage is identified as comprising 3 million elements. CFD-calculations of an experimental stage were performed with different turbulence models. The obtained data was compared with the NASA experimental data considering integral (total pressure ratio, mass flow rate, adiabatic efficiency) and differential parameters (static pressure distribution downstream the vaned diffuser). The required CFD computational time for different turbulence models was calculated. Based on the results of this research, recommendations were formulated for the application of SST, k–ε, BSL EARSM and GEKO turbulence models for numerical modeling of centrifugal compressors.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"5 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-12-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139149422","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 : 2023-12-28DOI: 10.18287/2541-7533-2023-22-4-52-58
V. V. Eremina, I. O. Erkov, A. A. Zhuravlev, I. V. Maslov, N. I. Pyrinov
The correct installation of antenna-feeder devices on board a small spacecraft and the choice of their parameters make it possible to ensure the solution of target problems with high quality. The main problematic issues of placement of antenna-feeder devices of the on-board equipment of the radio link for the transmission of target information on the SSC “AIST-2T” and the adopted design solutions are considered.
{"title":"Features of the use of directional fixed antennas of a high-speed radio link on a small spacecraft AIST-2T","authors":"V. V. Eremina, I. O. Erkov, A. A. Zhuravlev, I. V. Maslov, N. I. Pyrinov","doi":"10.18287/2541-7533-2023-22-4-52-58","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-4-52-58","url":null,"abstract":"The correct installation of antenna-feeder devices on board a small spacecraft and the choice of their parameters make it possible to ensure the solution of target problems with high quality. The main problematic issues of placement of antenna-feeder devices of the on-board equipment of the radio link for the transmission of target information on the SSC “AIST-2T” and the adopted design solutions are considered.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"298 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-12-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139152503","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-42-56
Y. Klebanov, V. Murashkin, A. M. Brazhnikova
The purpose of this work was to develop effective methods for calculating the wear rate of raceways and roller bearings under dynamic loads. The wear of the working surfaces of rolling bearings in many practical cases is an important critical factor affecting their performance and durability. However, only a limited number of publications are devoted to this issue. In most of them, Archard's law, which has been experimentally confirmed during hydrodynamic friction of bearing steels, is used to calculate the wear rate of the contacting surfaces. Based on this law, the article presents a method of direct step-by-step calculation of the wear rate at variable contact loads and sliding speeds. In accordance with it, the change in the normal force, sliding speed and thickness of the oil film in contact is determined in the dynamic calculation of the bearing, and the finite element method is used to calculate the contact pressure field. The multi-mass model of bearing dynamics includes a contact friction model that allows adequately reproducing the conditions of hydrodynamic contact of solids. The direct calculation method involves a large number of calculations that make the impact of individual factors on the wear rate opaque. Therefore, along with it, a method for calculating the wear rate by averaged parameters is proposed. Using these two methods, the wear calculations of the raceway of the inner ring and the rollers of a double-row tapered roller bearing were performed. The comparison of the results confirms the acceptable accuracy of the calculation according to the averaged parameters.
{"title":"Step-by-step simulation of wear of working surfaces in roller bearings","authors":"Y. Klebanov, V. Murashkin, A. M. Brazhnikova","doi":"10.18287/2541-7533-2023-22-2-42-56","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-42-56","url":null,"abstract":"The purpose of this work was to develop effective methods for calculating the wear rate of raceways and roller bearings under dynamic loads. The wear of the working surfaces of rolling bearings in many practical cases is an important critical factor affecting their performance and durability. However, only a limited number of publications are devoted to this issue. In most of them, Archard's law, which has been experimentally confirmed during hydrodynamic friction of bearing steels, is used to calculate the wear rate of the contacting surfaces. Based on this law, the article presents a method of direct step-by-step calculation of the wear rate at variable contact loads and sliding speeds. In accordance with it, the change in the normal force, sliding speed and thickness of the oil film in contact is determined in the dynamic calculation of the bearing, and the finite element method is used to calculate the contact pressure field. The multi-mass model of bearing dynamics includes a contact friction model that allows adequately reproducing the conditions of hydrodynamic contact of solids. The direct calculation method involves a large number of calculations that make the impact of individual factors on the wear rate opaque. Therefore, along with it, a method for calculating the wear rate by averaged parameters is proposed. Using these two methods, the wear calculations of the raceway of the inner ring and the rollers of a double-row tapered roller bearing were performed. The comparison of the results confirms the acceptable accuracy of the calculation according to the averaged parameters.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114070057","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-91-104
Многопозиционный Контроль, С Помощью, Лазерного Трекера, Перемещений Элементов, Крупногабаритной Конструкции, В Процессе, Статического Нагружения, Н. А. Сазонникова
One of the most important tasks in the manufacturing of aerospace products is the control of their geometric parameters at various stages of production and assessment of their compliance with the requirements of design documentation. The use of laser automated measuring systems makes it possible to increase the measurement speed and to use the product digital model as a reference point. The best results in solving such problems can be obtained using laser automated measuring systems, such as laser scanners and laser trackers. In this paper a two-position measurement system is applied to control the aluminum alloy fuel component tank of the designed launch vehicle with two modes of static loading, corresponding to different transportation conditions. In this case, the linear dimension error should not exceed 150 m. A mathematical model of a multi-position measuring system is constructed and measurement uncertainty equations are obtained. In this case, the error function value that represents the difference between the errors in determining the coordinates of the reference points and the controlled points of the measurement object should be minimal. This mathematical model will be further used for numerical modeling that will allow selecting the optimal configuration of a measuring system for multi-position control of the tank geometric parameters in the static loading process.
{"title":"Multi-position control of movements of large-sized structural elements during static loading using a laser tracker","authors":"Многопозиционный Контроль, С Помощью, Лазерного Трекера, Перемещений Элементов, Крупногабаритной Конструкции, В Процессе, Статического Нагружения, Н. А. Сазонникова","doi":"10.18287/2541-7533-2023-22-2-91-104","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-91-104","url":null,"abstract":"One of the most important tasks in the manufacturing of aerospace products is the control of their geometric parameters at various stages of production and assessment of their compliance with the requirements of design documentation. The use of laser automated measuring systems makes it possible to increase the measurement speed and to use the product digital model as a reference point. The best results in solving such problems can be obtained using laser automated measuring systems, such as laser scanners and laser trackers. In this paper a two-position measurement system is applied to control the aluminum alloy fuel component tank of the designed launch vehicle with two modes of static loading, corresponding to different transportation conditions. In this case, the linear dimension error should not exceed 150 m. A mathematical model of a multi-position measuring system is constructed and measurement uncertainty equations are obtained. In this case, the error function value that represents the difference between the errors in determining the coordinates of the reference points and the controlled points of the measurement object should be minimal. This mathematical model will be further used for numerical modeling that will allow selecting the optimal configuration of a measuring system for multi-position control of the tank geometric parameters in the static loading process.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"73 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130130820","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-33-41
E. G. Berestovitsky, Y. F. Gladilin, N. Pyalov
Currently, when creating the actuators of deep-sea vehicles and other technical facilities, there is a tendency to accommodate the elements of the hydraulic drive outside the durable housing. Such hydraulic systems are subject to the risk of depressurization, which leads to the ingress of working fluid (mineral oils or synthetic working fluids) into seawater and flooding of the hydraulic system's working fluid with seawater. The ingress of the working fluid into seawater leads to the violation of environmental safety, and if seawater enters the internal cavities of the hydraulic system, they may be damaged, which will require long and expensive repair in the future. One of the possible ways to eliminate the listed consequences of depressurization of outboard hydraulic systems is the creation of hydraulic equipment using seawater as a working fluid. The cheapest design of such a regulatory body is the use of shut-off valves with elastic tubular control elements. The research carried out confirmed the possibility of creating low-noise regulators with elastic control elements. These regulators have better vibroacoustic characteristics than spool-type throttles with similar functional characteristics. Preservation of the operating characteristics of regulators with elastic regulating elements when working with working fluids of different viscosities (PGV liquid, mineral oil, tap water) was confirmed. Survivability of a regulator with elastic control elements during long-term tests was confirmed. As a result of the work carried out, research and technological groundwork was obtained that allows creating a device with elastic regulating elements, having a flow differential characteristic that meets modern requirements, a vibroacoustic characteristic that meets advanced requirements and sufficient reliability when working on clean working fluids.
{"title":"Development of hydraulic devices with elastic regulating elements","authors":"E. G. Berestovitsky, Y. F. Gladilin, N. Pyalov","doi":"10.18287/2541-7533-2023-22-2-33-41","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-33-41","url":null,"abstract":"Currently, when creating the actuators of deep-sea vehicles and other technical facilities, there is a tendency to accommodate the elements of the hydraulic drive outside the durable housing. Such hydraulic systems are subject to the risk of depressurization, which leads to the ingress of working fluid (mineral oils or synthetic working fluids) into seawater and flooding of the hydraulic system's working fluid with seawater. The ingress of the working fluid into seawater leads to the violation of environmental safety, and if seawater enters the internal cavities of the hydraulic system, they may be damaged, which will require long and expensive repair in the future. One of the possible ways to eliminate the listed consequences of depressurization of outboard hydraulic systems is the creation of hydraulic equipment using seawater as a working fluid. The cheapest design of such a regulatory body is the use of shut-off valves with elastic tubular control elements. The research carried out confirmed the possibility of creating low-noise regulators with elastic control elements. These regulators have better vibroacoustic characteristics than spool-type throttles with similar functional characteristics. Preservation of the operating characteristics of regulators with elastic regulating elements when working with working fluids of different viscosities (PGV liquid, mineral oil, tap water) was confirmed. Survivability of a regulator with elastic control elements during long-term tests was confirmed. As a result of the work carried out, research and technological groundwork was obtained that allows creating a device with elastic regulating elements, having a flow differential characteristic that meets modern requirements, a vibroacoustic characteristic that meets advanced requirements and sufficient reliability when working on clean working fluids.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130391203","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-57-66
Особенности Решения, Задач Прочности, При Динамическом, Нагружении Оборудования, Реакторной Установки, реальных конструкциях, РУ элементах, реактора, электронасосов
The paper presents tasks and approaches to their solutions in assessing vibration strength and dynamic safety of marine reactor equipment (for example: pumps, control driven rod mechanisms). The topicality of this work is determined by the experience of operating nuclear power plants. Development of digital computation models and computational analysis allowed us to exclude experimental validation of control driven rod mechanisms seismic resistance. A digital computational model was developed for validating the dynamic safety and life time of the seal pot of the reactor facility main circulation pump. The model included the main circulation pump and the framework of the reactor facility. Computational and experimental analysis of the vibration state of the control and protection system drives was also carried out.
{"title":"Special features of assessing the strength of nuclear reactor equipment under dynamic loads","authors":"Особенности Решения, Задач Прочности, При Динамическом, Нагружении Оборудования, Реакторной Установки, реальных конструкциях, РУ элементах, реактора, электронасосов","doi":"10.18287/2541-7533-2023-22-2-57-66","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-57-66","url":null,"abstract":"The paper presents tasks and approaches to their solutions in assessing vibration strength and dynamic safety of marine reactor equipment (for example: pumps, control driven rod mechanisms). The topicality of this work is determined by the experience of operating nuclear power plants. Development of digital computation models and computational analysis allowed us to exclude experimental validation of control driven rod mechanisms seismic resistance. A digital computational model was developed for validating the dynamic safety and life time of the seal pot of the reactor facility main circulation pump. The model included the main circulation pump and the framework of the reactor facility. Computational and experimental analysis of the vibration state of the control and protection system drives was also carried out.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115971638","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-7-20
V. Kurenkov, E. Pupkov, A. Kucherov
Design models and algorithms have been developed to estimate the spatial direction of the reorientation of spacecraft for optoelectronic observation of the Earths surface during object shooting, taking into account the relative movement of the surveillance objects in the field of view of the spacecraft. Modeling is simplified due to the choice of such coordinate systems in which the spacecraft is stationary and the surveillance objects move relative to it. The direction of rotation of the spacecraft with a given angular velocity is found at the point of the upcoming intersection of the optical axis of the observation equipment on the Earths surface with the surveillance object moving in the selected coordinate system. The models and algorithms were developed in order to expand the capabilities of Samara Universitys existing software package for evaluating the target indicators and design characteristics of observation spacecraft. Based on the developed re-targeting models, algorithms have been developed for selecting the sequence of shooting observation objects according to the criterion of their maximum number on the orbit of the spacecraft flight and counting the captured objects to assess the performance of survey. An example of the implementation of one of the graphic windows of the software with the developed models and algorithms is given, in which the process of re-targeting the spacecraft is visualized, which is one of the ways to verify the adequacy of the developed models and algorithms.
{"title":"Simulating the process of retargeting of optoelectronic Earth observation spacecraft during object shooting","authors":"V. Kurenkov, E. Pupkov, A. Kucherov","doi":"10.18287/2541-7533-2023-22-2-7-20","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-7-20","url":null,"abstract":"Design models and algorithms have been developed to estimate the spatial direction of the reorientation of spacecraft for optoelectronic observation of the Earths surface during object shooting, taking into account the relative movement of the surveillance objects in the field of view of the spacecraft. Modeling is simplified due to the choice of such coordinate systems in which the spacecraft is stationary and the surveillance objects move relative to it. The direction of rotation of the spacecraft with a given angular velocity is found at the point of the upcoming intersection of the optical axis of the observation equipment on the Earths surface with the surveillance object moving in the selected coordinate system. The models and algorithms were developed in order to expand the capabilities of Samara Universitys existing software package for evaluating the target indicators and design characteristics of observation spacecraft. Based on the developed re-targeting models, algorithms have been developed for selecting the sequence of shooting observation objects according to the criterion of their maximum number on the orbit of the spacecraft flight and counting the captured objects to assess the performance of survey. An example of the implementation of one of the graphic windows of the software with the developed models and algorithms is given, in which the process of re-targeting the spacecraft is visualized, which is one of the ways to verify the adequacy of the developed models and algorithms.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114694276","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-105-115
A. Y. Sundukov, Ye. V. Shakhmatov
Planetary gearboxes of aviation gas turbine engines are their most stressed units. Control of their technical condition under operating conditions by measuring the oil temperature and the presence of chips in it by a visual endoscopic method does not provide the required completeness of control. High vibration activity of gearboxes, especially in case of development of a widespread defect in the form of wear of tooth flanks, requires additional methods of assessment of their technical condition. The practice of operating such complex and stressed objects shows that vibroacoustic diagnostics is the most effective one. However, for aviation gas-turbine engines its use is connected with certain difficulties. First of all, it is the change of vibration intensity when the engine is relocated from the test bench to the object. At the engine manufacturer's stand, as a rule, the collection of experimental material for the development of methods of vibration-based diagnostics of defects is carried out. To overcome the above-mentioned problem, we suggest new methods for detecting diagnostic signs of tooth flank wear. Both vibration processes and signals of standard tachometric sensors of input and output gearbox shaft rotation frequency are used. A set of diagnostic features on the basis of frequency parameters is proposed. The use of some of them makes it possible to assess the technical condition of the engine gearbox during operation, for example in the performance of routine maintenance work.
{"title":"New methods for identifying diagnostic indicators of the technical condition of aircraft gas turbine engine reduction gearboxes","authors":"A. Y. Sundukov, Ye. V. Shakhmatov","doi":"10.18287/2541-7533-2023-22-2-105-115","DOIUrl":"https://doi.org/10.18287/2541-7533-2023-22-2-105-115","url":null,"abstract":"Planetary gearboxes of aviation gas turbine engines are their most stressed units. Control of their technical condition under operating conditions by measuring the oil temperature and the presence of chips in it by a visual endoscopic method does not provide the required completeness of control. High vibration activity of gearboxes, especially in case of development of a widespread defect in the form of wear of tooth flanks, requires additional methods of assessment of their technical condition. The practice of operating such complex and stressed objects shows that vibroacoustic diagnostics is the most effective one. However, for aviation gas-turbine engines its use is connected with certain difficulties. First of all, it is the change of vibration intensity when the engine is relocated from the test bench to the object. At the engine manufacturer's stand, as a rule, the collection of experimental material for the development of methods of vibration-based diagnostics of defects is carried out. To overcome the above-mentioned problem, we suggest new methods for detecting diagnostic signs of tooth flank wear. Both vibration processes and signals of standard tachometric sensors of input and output gearbox shaft rotation frequency are used. A set of diagnostic features on the basis of frequency parameters is proposed. The use of some of them makes it possible to assess the technical condition of the engine gearbox during operation, for example in the performance of routine maintenance work.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"46 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120891169","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 : 2023-06-28DOI: 10.18287/2541-7533-2023-22-2-67-78
Методика Индивидуального, Подбора Деталей, Для Селективной Сборки, Е. М. Халатов
A method for selecting parts and assembly units (hereinafter briefly referred to as parts) in sets for assembling a batch of electrohydraulic servo drives is presented, based on the measured (individual) mechanical and hydraulic characteristics of the parts. The preparatory stage is described: construction of a mathematical model of the product, determination of the parameters of parts and adjustments that have the greatest impact on the parameters of end products, formation of a system for assessing the quality of products in the batch, mathematical formulation of the task of selecting parts. The task of selecting parts is formulated as the assignment problem in the maximin formulation. A deterministic algorithm for solving the problem is presented, based on the branch and bound method and taking into account the fact that adjustments are made during the assembly of drives. A significant reduction in the number of steps (iterations) when searching for the optimal distribution of parts across assembly sets achieved due to the chosen mathematical formulation of the task, as well as due to the chosen strategy of selecting parts in the next assembly set. We suggest that an assembly set should include, first of all, the most troublesome parts the parameters of which do not allow obtaining a set, the projected quality indicator of which will be higher than the established value. At the same time, the negative impact of these parts on the product parameters is compensated by combining them with other parts in one assembly set. The results of mathematical modeling of assembling 992 drives with random formation of assembly sets and with individual selection of parts are presented. Modeling shows that as a result of implementing individual selection of parts in accordance with the described method, a significant reduction in the spread of parameters of end products within batches can be expected, as well as improvements in functional performance of the products. The presented method of individual selection of parts can be used in the assembly of various products.
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