Pub Date : 2024-07-10DOI: 10.18287/2541-7533-2024-23-2-40-48
L. A. Klimakova
The problem of ensuring the specified thermo-dimensional stability of structures from laminated polymer composite materials for the service life period is considered. A method of reliability-oriented design of a thermo-dimensionally stable composite structure is proposed, according to which its design parameters are set with regard to the possibility of obtaining thermal strain properties under specific processing and the changes of these properties for the operational conditions and duration of using the article as intended. Within the framework of the presented approach, the features of design upon the dimensional accuracy and stability criterion when meeting the requirements of strength and stiffness are discussed, an algorithm of a packaged solution of the design task is given.
{"title":"Reliability-oriented design of PCM thermodimensionally stable space structures","authors":"L. A. Klimakova","doi":"10.18287/2541-7533-2024-23-2-40-48","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-2-40-48","url":null,"abstract":"The problem of ensuring the specified thermo-dimensional stability of structures from laminated polymer composite materials for the service life period is considered. A method of reliability-oriented design of a thermo-dimensionally stable composite structure is proposed, according to which its design parameters are set with regard to the possibility of obtaining thermal strain properties under specific processing and the changes of these properties for the operational conditions and duration of using the article as intended. Within the framework of the presented approach, the features of design upon the dimensional accuracy and stability criterion when meeting the requirements of strength and stiffness are discussed, an algorithm of a packaged solution of the design task is given.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"13 6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141659028","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 : 2024-07-10DOI: 10.18287/2541-7533-2024-23-2-109-120
A. A. Zolotov, V. V. Rodchenko, E. V. Gusev, I. A. Karyagin
The problem of monitoring the performance of technical systems is considered, corresponding to the stage of final control during the production of a product, as well as the stage of testing the product before its use. Based on the generalization and development of the existing approaches, models and methods for monitoring the performance of complex technical systems were developed, and models for predicting the parameters of their control were proposed. Methods of optimizing the number of tests of units of technical systems when monitoring their performance were developed. Methods for estimating the optimal level of the total defect rate are proposed. The efficiency of the proposed approaches is illustrated using a specific numerical example. The methods and models presented in the article can be useful for engineering and technical workers of design bureaus, research institutes, research and production associations and enterprises in ensuring the reliability of products and technical systems.
{"title":"Forecasting the parameters of performance monitoring of complex technical systems","authors":"A. A. Zolotov, V. V. Rodchenko, E. V. Gusev, I. A. Karyagin","doi":"10.18287/2541-7533-2024-23-2-109-120","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-2-109-120","url":null,"abstract":"The problem of monitoring the performance of technical systems is considered, corresponding to the stage of final control during the production of a product, as well as the stage of testing the product before its use. Based on the generalization and development of the existing approaches, models and methods for monitoring the performance of complex technical systems were developed, and models for predicting the parameters of their control were proposed. Methods of optimizing the number of tests of units of technical systems when monitoring their performance were developed. Methods for estimating the optimal level of the total defect rate are proposed. The efficiency of the proposed approaches is illustrated using a specific numerical example. The methods and models presented in the article can be useful for engineering and technical workers of design bureaus, research institutes, research and production associations and enterprises in ensuring the reliability of products and technical systems.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"51 20","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141659963","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 : 2024-07-10DOI: 10.18287/2541-7533-2024-23-2-157-166
A. E. Sundukov, E. V. Shakhmatov
Gearbox is the most stressed component in an aircraft gas-turbine engine. This implies the need for finding ways to monitor its technical condition. Practice shows that the most efficient method is vibration-based diagnostics. However, this method requires the use of sophisticated measurement systems and highly skilled personnel. This paper shows that errors of gear coupling manufacture and assembly, characteristics of machine operating mode, design factors, frequency modulation of the carrier of the engine rotor speed in the stationary mode of its operation, and wear of teeth flanks determine the width of the spectral component of the gearbox output shaft speed. Using the results obtained from the developed model of the width of gear tooth spectral component, ratios for width of the spectral component of the signal of the “standard” tachometric speed sensor of the gearbox output shaft speed and the corresponding spectral component of its vibration were obtained. Models for repaired and newly manufactured gearboxes and gearboxes with tooth flank wear were proposed. This allowed the development of a number of new diagnostic indicators of a defect. Several examples of the use of these new diagnostic indicators are given for the gearbox of one of turbo-prop engines. The results obtained provide an opportunity to assess the gearbox technical condition in operation.
{"title":"Modelling width of the spectral component of a gas-turbine engine gearbox output shaft speed","authors":"A. E. Sundukov, E. V. Shakhmatov","doi":"10.18287/2541-7533-2024-23-2-157-166","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-2-157-166","url":null,"abstract":"Gearbox is the most stressed component in an aircraft gas-turbine engine. This implies the need for finding ways to monitor its technical condition. Practice shows that the most efficient method is vibration-based diagnostics. However, this method requires the use of sophisticated measurement systems and highly skilled personnel. This paper shows that errors of gear coupling manufacture and assembly, characteristics of machine operating mode, design factors, frequency modulation of the carrier of the engine rotor speed in the stationary mode of its operation, and wear of teeth flanks determine the width of the spectral component of the gearbox output shaft speed. Using the results obtained from the developed model of the width of gear tooth spectral component, ratios for width of the spectral component of the signal of the “standard” tachometric speed sensor of the gearbox output shaft speed and the corresponding spectral component of its vibration were obtained. Models for repaired and newly manufactured gearboxes and gearboxes with tooth flank wear were proposed. This allowed the development of a number of new diagnostic indicators of a defect. Several examples of the use of these new diagnostic indicators are given for the gearbox of one of turbo-prop engines. The results obtained provide an opportunity to assess the gearbox technical condition in operation.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"110 12","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141835519","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 : 2024-07-10DOI: 10.18287/2541-7533-2024-23-2-132-142
S. Prikhodko, V. S. Sidorenko, D. Korotych
The creation of new and improvement of existing machines and mechanisms requires the development of drive engineering and the creation of new drive systems capable of competing with currently known circuit solutions. Under these conditions, the creation of combined pneumatic-mechanical drives is an important scientific and technical task. The purpose of this work is to increase the speed at a given accuracy of auxiliary movements of the target mechanisms of technological machines by creating a pneumatic-mechanical drive with improved energy and dynamic characteristics. The technical solution of a positioning pneumatic-mechanical drive of executive movements of technological equipment is presented, mathematical and computer models are developed. In this case, the method of solving the differential equation in the SimInTech program is used. As a result, an oscillogram of transients is obtained. The developed models allow for dynamic analysis of pneumatic-mechanical systems.
{"title":"Investigation of the dynamic characteristics of the pneumatic-mechanical drive of the installation movements of machine mechanisms","authors":"S. Prikhodko, V. S. Sidorenko, D. Korotych","doi":"10.18287/2541-7533-2024-23-2-132-142","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-2-132-142","url":null,"abstract":"The creation of new and improvement of existing machines and mechanisms requires the development of drive engineering and the creation of new drive systems capable of competing with currently known circuit solutions. Under these conditions, the creation of combined pneumatic-mechanical drives is an important scientific and technical task. The purpose of this work is to increase the speed at a given accuracy of auxiliary movements of the target mechanisms of technological machines by creating a pneumatic-mechanical drive with improved energy and dynamic characteristics. The technical solution of a positioning pneumatic-mechanical drive of executive movements of technological equipment is presented, mathematical and computer models are developed. In this case, the method of solving the differential equation in the SimInTech program is used. As a result, an oscillogram of transients is obtained. The developed models allow for dynamic analysis of pneumatic-mechanical systems.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"27 11","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141660760","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 : 2024-07-10DOI: 10.18287/2541-7533-2024-23-2-62-73
A. V. Sychev, I. V. Arbuzov, Y.A. Ravikovich
The article discusses a method for calculating, as a first approximation, the take-off weight of a light aircraft with a hybrid power plant based on piston and electric engines. A brief overview of organizations dealing with hybrid power plants is given. The influence of the degree of hybridization of the power plant on the take-off weight of the aircraft is shown. The degree of hybridization of a power plant is understood as a relative value characterizing the distribution of the total power of all engines installed on the aircraft between piston and electric engines. The main parameters necessary to determine the take-off weight of an aircraft to a first approximation are presented. The take-off weight of the aircraft is determined to a first approximation from the equation of its existence. Statistical data of aircraft with different types of power plants are provided on the basis of which calculations are carried out. As a first approximation, the relative mass of the hybrid power plant is determined by analyzing the statistical data of light aircraft with piston and electric engines, from which the corresponding graphs are constructed. After the calculations, conclusions were drawn about the optimal range of characteristics of a light aircraft with a hybrid power plant.
{"title":"Method of first-approximation calculation of take-off weight of a light aircraft with a hybrid propulsion system","authors":"A. V. Sychev, I. V. Arbuzov, Y.A. Ravikovich","doi":"10.18287/2541-7533-2024-23-2-62-73","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-2-62-73","url":null,"abstract":"The article discusses a method for calculating, as a first approximation, the take-off weight of a light aircraft with a hybrid power plant based on piston and electric engines. A brief overview of organizations dealing with hybrid power plants is given. The influence of the degree of hybridization of the power plant on the take-off weight of the aircraft is shown. The degree of hybridization of a power plant is understood as a relative value characterizing the distribution of the total power of all engines installed on the aircraft between piston and electric engines. The main parameters necessary to determine the take-off weight of an aircraft to a first approximation are presented. The take-off weight of the aircraft is determined to a first approximation from the equation of its existence. Statistical data of aircraft with different types of power plants are provided on the basis of which calculations are carried out. As a first approximation, the relative mass of the hybrid power plant is determined by analyzing the statistical data of light aircraft with piston and electric engines, from which the corresponding graphs are constructed. After the calculations, conclusions were drawn about the optimal range of characteristics of a light aircraft with a hybrid power plant.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"36 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141659060","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 : 2024-04-17DOI: 10.18287/2541-7533-2024-23-1-38-54
O. Lukyanov, V. H. Hoang, V. A. Komarov, D. V. Nazarov, E. Kurkin, J. G. Quijada Pioquinto, V. Chertykovtseva
The paper describes possibilities of increasing the energy efficiency and reducing the takeoff weight of unmanned medium-heavy vertical takeoff and landing aerial vehicles of the airplane type. The authors propose a new hybrid type of unmanned aerial vehicle with a hybrid propulsion system, its aerodynamic design, method of realization of vertical takeoff/landing and cruising mode of flight which make it possible to reduce the takeoff weight of the aircraft, the weight of the basic propulsion system and the mass growth factor in comparison with the existing unmanned aerial vehicle of similar class, made according to the previously known technical solutions. The authors propose a methodology for optimizing the parameters of the configuration of the unmanned aerial vehicle considering the peculiarities of the implementation of vertical takeoff. The paper presents calculations of characteristics of vertical takeoff and landing unmanned aerial vehicles of existing types and the new hybrid type. The authors give quantitative estimates of improving unmanned aerial vehicle characteristics due to the new proposed technical solutions.
{"title":"Reducing energy consumption of vertical take-off and landing unmanned aerial vehicle using hybrid technical solutions","authors":"O. Lukyanov, V. H. Hoang, V. A. Komarov, D. V. Nazarov, E. Kurkin, J. G. Quijada Pioquinto, V. Chertykovtseva","doi":"10.18287/2541-7533-2024-23-1-38-54","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-1-38-54","url":null,"abstract":"The paper describes possibilities of increasing the energy efficiency and reducing the takeoff weight of unmanned medium-heavy vertical takeoff and landing aerial vehicles of the airplane type. The authors propose a new hybrid type of unmanned aerial vehicle with a hybrid propulsion system, its aerodynamic design, method of realization of vertical takeoff/landing and cruising mode of flight which make it possible to reduce the takeoff weight of the aircraft, the weight of the basic propulsion system and the mass growth factor in comparison with the existing unmanned aerial vehicle of similar class, made according to the previously known technical solutions. The authors propose a methodology for optimizing the parameters of the configuration of the unmanned aerial vehicle considering the peculiarities of the implementation of vertical takeoff. The paper presents calculations of characteristics of vertical takeoff and landing unmanned aerial vehicles of existing types and the new hybrid type. The authors give quantitative estimates of improving unmanned aerial vehicle characteristics due to the new proposed technical solutions.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":" 9","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140692406","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 : 2024-04-17DOI: 10.18287/2541-7533-2024-23-1-80-92
A. A. Khramov
The problems of optimizing the trajectory motion of the first stage of an aerospace system according to the criterion of the maximum of the final mass are considered. The control is the angle of attack and thrust of the engines. Control optimization is carried out on the trajectory section from the point of bringing the first stage to the launch area until the motion parameters required for separation of the space stage are reached. The Pontryagin’s maximum principle is used to determine optimal control programs. The solution of the problem without restrictions on the modes of motion is carried out using the example of acceleration and climb of the first stage of the RASCAL aerospace system. A method is proposed for determining approximate optimal control in a problem with a limitation on the altitude range of the engines with separate optimization of the active and passive sections and the search for the optimal point of their coupling. Changes in control program, trajectory, and fuel consumption are discussed when limiting the maximum flight altitude in the active section.
{"title":"Optimization of trajectory motion of the first stage of an aerospace system","authors":"A. A. Khramov","doi":"10.18287/2541-7533-2024-23-1-80-92","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-1-80-92","url":null,"abstract":"The problems of optimizing the trajectory motion of the first stage of an aerospace system according to the criterion of the maximum of the final mass are considered. The control is the angle of attack and thrust of the engines. Control optimization is carried out on the trajectory section from the point of bringing the first stage to the launch area until the motion parameters required for separation of the space stage are reached. The Pontryagin’s maximum principle is used to determine optimal control programs. The solution of the problem without restrictions on the modes of motion is carried out using the example of acceleration and climb of the first stage of the RASCAL aerospace system. A method is proposed for determining approximate optimal control in a problem with a limitation on the altitude range of the engines with separate optimization of the active and passive sections and the search for the optimal point of their coupling. Changes in control program, trajectory, and fuel consumption are discussed when limiting the maximum flight altitude in the active section.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":"137 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140693720","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 : 2024-04-17DOI: 10.18287/2541-7533-2024-23-1-109-122
V. Avgustinovich, T. A. Kuznetsova, A. A. Sukharev
One of the most important gas turbine engine components is the combustion chamber, the main source of harmful emissions. The study is devoted to the central issues of designing and testing of an automatic control system of harmful emissions and pressure pulsations in flame tubes of a gas turbine plant with a capacity of 16 MW GTP-16 based on a PI-controller with a built-in neural network mathematical model of a low-emission combustor (LEС). Algorithms for a neural network controller of emission of nitrogen oxides and carbon monoxide into the atmosphere, as well as pressure pulsations in the LEC’s flame tubes were developed. The algorithms are given in a graphical programming environment and integrated into the automatic control system of GTP-16, implemented on the PXI NI hardware and software platform. The performance of the emission controller was checked during bench tests on the GTP-16 simulator with LEС neural network model serving as a virtual emission sensor. The errors in estimating the emission of nitrogen and carbon oxides and pressure pulsations in the flame tubes were determined. The normality of the error distribution of the developed nitrogen oxide emission model was proven. A conclusion about the prospects of using neural networks for the development of an adaptive control system of emissions and flame tube pressure pulsations for LECs of the gas turbine plants was drawn.
燃烧室是燃气涡轮发动机最重要的部件之一，也是有害排放物的主要来源。本研究的核心问题是设计和测试一套自动控制系统，以 PI 控制器和内置的低排放燃烧器 (LEС) 神经网络数学模型为基础，控制 16 兆瓦 GTP-16 燃气轮机发电厂火焰管中的有害排放物和压力脉动。针对氮氧化物和一氧化碳向大气中的排放以及低排放燃烧器火焰管中的压力脉动，开发了神经网络控制器算法。这些算法在图形编程环境中给出，并集成到在 PXI NI 硬件和软件平台上实现的 GTP-16 自动控制系统中。在将 LEС 神经网络模型作为虚拟排放传感器的 GTP-16 模拟器上进行的台架测试中，对排放控制器的性能进行了检验。确定了估算氮氧化物和碳氧化物排放量的误差以及火焰管中的压力脉动。证明了所开发的氮氧化物排放模型误差分布的正态性。最后得出结论：利用神经网络开发燃气轮机厂低压燃烧器排放和火焰管压力脉动自适应控制系统的前景广阔。
{"title":"Neural network controller of a gas turbine plant low emission combustor","authors":"V. Avgustinovich, T. A. Kuznetsova, A. A. Sukharev","doi":"10.18287/2541-7533-2024-23-1-109-122","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-1-109-122","url":null,"abstract":"One of the most important gas turbine engine components is the combustion chamber, the main source of harmful emissions. The study is devoted to the central issues of designing and testing of an automatic control system of harmful emissions and pressure pulsations in flame tubes of a gas turbine plant with a capacity of 16 MW GTP-16 based on a PI-controller with a built-in neural network mathematical model of a low-emission combustor (LEС). Algorithms for a neural network controller of emission of nitrogen oxides and carbon monoxide into the atmosphere, as well as pressure pulsations in the LEC’s flame tubes were developed. The algorithms are given in a graphical programming environment and integrated into the automatic control system of GTP-16, implemented on the PXI NI hardware and software platform. The performance of the emission controller was checked during bench tests on the GTP-16 simulator with LEС neural network model serving as a virtual emission sensor. The errors in estimating the emission of nitrogen and carbon oxides and pressure pulsations in the flame tubes were determined. The normality of the error distribution of the developed nitrogen oxide emission model was proven. A conclusion about the prospects of using neural networks for the development of an adaptive control system of emissions and flame tube pressure pulsations for LECs of the gas turbine plants was drawn.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":" 30","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140691198","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 : 2024-04-17DOI: 10.18287/2541-7533-2024-23-1-7-20
V. A. Zelenskiy, M. A. Kovalev, D. N. Ovakimyan, V. S. Kirillov
A generalized kinematic scheme of the installation of quadcopter motors is presented and its main advantages are described. In accordance with the scheme, a mathematical model of the kinematics of the quadcopter was developed. The model was implemented in the MatLab software environment. The presented mathematical expressions are used to calculate kinematic characteristics, such as the values of the thrust of the motors and the reverse effect of the motors on the body of the quadcopter. The comparison of the obtained data with the experimental characteristics showed a 5% deviation of the magnitude of the dependence of the thrust on the average value of the voltage on the motors and a 30% deviation of the magnitude of the dependence of the motor action on the thrust magnitude.
{"title":"Mathematical model of a generalized quadcopter kinematic scheme and its software implementation","authors":"V. A. Zelenskiy, M. A. Kovalev, D. N. Ovakimyan, V. S. Kirillov","doi":"10.18287/2541-7533-2024-23-1-7-20","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-1-7-20","url":null,"abstract":"A generalized kinematic scheme of the installation of quadcopter motors is presented and its main advantages are described. In accordance with the scheme, a mathematical model of the kinematics of the quadcopter was developed. The model was implemented in the MatLab software environment. The presented mathematical expressions are used to calculate kinematic characteristics, such as the values of the thrust of the motors and the reverse effect of the motors on the body of the quadcopter. The comparison of the obtained data with the experimental characteristics showed a 5% deviation of the magnitude of the dependence of the thrust on the average value of the voltage on the motors and a 30% deviation of the magnitude of the dependence of the motor action on the thrust magnitude.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":" 46","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140692866","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 : 2024-04-17DOI: 10.18287/2541-7533-2024-23-1-93-108
K. V. Shaposhnikov, S. A. Degtyarev, M. K. Leontiev, S. V. Anisimov
A method for developing a numerical rotor model and its further verification based on the results of virtual static structural and modal tests was proposed. Approbation of the method was performed on a model of a low pressure rotor of a high-bypass turbofan engine constructed in a software system for rotor dynamics simulation DYNAMICS R4. Refined on the basis of the results of virtual static structural tests, the model of the rotor main force action line showed good agreement in frequencies and mode shapes with the results of a finite element model, obtained during a virtual modal test.
{"title":"Verification of aero-engine numerical rotor models based on virtual static structural and modal tests","authors":"K. V. Shaposhnikov, S. A. Degtyarev, M. K. Leontiev, S. V. Anisimov","doi":"10.18287/2541-7533-2024-23-1-93-108","DOIUrl":"https://doi.org/10.18287/2541-7533-2024-23-1-93-108","url":null,"abstract":"A method for developing a numerical rotor model and its further verification based on the results of virtual static structural and modal tests was proposed. Approbation of the method was performed on a model of a low pressure rotor of a high-bypass turbofan engine constructed in a software system for rotor dynamics simulation DYNAMICS R4. Refined on the basis of the results of virtual static structural tests, the model of the rotor main force action line showed good agreement in frequencies and mode shapes with the results of a finite element model, obtained during a virtual modal test.","PeriodicalId":265584,"journal":{"name":"VESTNIK of Samara University. Aerospace and Mechanical Engineering","volume":" 31","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140690918","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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