Aerospace technic and technology最新文献

{"title":"Математична модель розрахунку аеродинамічних сил, утворюваних роторним рушієм для пропульсивних крил","authors":"Bohdan Komarov, Dmytro Zinchenko","doi":"10.32620/aktt.2023.4.02","DOIUrl":"https://doi.org/10.32620/aktt.2023.4.02","url":null,"abstract":"The subject of the study is the modeling and obtaining of aerodynamic characteristics and determining the aerodynamic forces acting on an aircraft with a propulsive wing using a mathematical model. The research is based on mathematical methods and proposes a comprehensive model that accurately describes the interaction of airflow with wing and rotor propulsion. The aim of this study is to find solutions for faster calculations and approximate analysis of wings and aircraft that use them, compared to CFD methods. The task is to find methods that can perform calculations based only on geometric shapes and a minimal set of data that can be obtained by the researcher. The article begins with a review of previous research in the field of aerodynamics, demonstrating the need for the development of new models to better understand the aerodynamic forces generated by wing and rotor propulsion. A new mathematical model is considered, using methods based on Bernoulli's equation and taking into account parameters such as wing shape, angle of attack, airflow velocity, and rotor propulsion characteristics. This article describes the mathematical equations and approaches used to model aerodynamic forces. They include physical laws such as Newton's laws, the conservation of mass and momentum, and basic aerodynamic equations. Validation of the model was conducted by comparing the obtained results with experimental data. To verify the correctness of the presented claims, a series of computational experiments using numerical methods are performed to calculate the dynamic characteristics for different wing and rotor propulsion configurations, and the obtained data are compared. Through careful experiments and data analysis, the research results are expected to provide valuable insights into the practical implementation of an integrated tangential fan system in a wing by evaluating its efficiency, limitations, and potential advantages. This work can help engineers determine optimal wing and rotor propulsion configurations to achieve better aerodynamic efficiency and ensure the desired flight characteristics. This research can make an important contribution to the development of aviation technology and to the improvement of aircraft with rotor propulsion. Conclusions: the article proposes a new mathematical model for calculating the aerodynamic forces generated by wing and rotor propulsion and demonstrates its speed and efficiency by comparing it with experimental data. This research is just the first step in creating a mathematical framework. To improve calculation results and enable automation for greater variability in shape, the panel-vortex method with the consideration of flow acceleration over panel surfaces is more suitable. However, even at this stage, the research results can contribute to the development and optimization of aircraft structures with propulsive devices embedded in the wing design.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126813627","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ідентифікація параметрів математичних моделей та визначення діагностичних ознак","authors":"Tran Manh Hung","doi":"10.32620/aktt.2023.4sup1.11","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup1.11","url":null,"abstract":"In this article, the object of research is two main units of the AR20N aggregate – electrohydraulic amplifier (EHA) and power cylinder (PC). Detection of the occurrence and development of faults in them will be considered on the basis of the identification of parameters of the developed mathematical models. The main objectives of the research were to identify the parameters of mathematical models of EHA and PC using different steps of time quantization, determination of the optimal step of time quantization for numerical integration of differential equations; determination of diagnostic features that have the most probable influence on the operation of aggregate units at the occurrence of various faults. For achievement of the set objectives the following tasks were solved: mathematical models of EHA, PC, and simulation model of the aggregate research on the test bench were developed; identification of parameters of mathematical models of EHA and PC by the method of least squares (MLS) was carried out; the permissible step of time quantization was determined; upper and lower permissible limits of the identifiable parameters for a serviceable aggregate were determined; a methodology for determining the diagnostic features that are most probable to determine the emerging faults of the aggregate has been developed. Methods are used for this purpose: analytical, numerical, statistical, hydraulic systems theory, and system identification theory. The following results were obtained: differential equations describing the displacements of the distributive spool (DS) of the EHA and the output link (OL) of the PC; algorithms for identifying the parameters of mathematical models by MLS; the permissible step of time quantization was determined; and a technique for determining the diagnostic features using the Shewhart diagnostic chart for the parameters of mathematical models was developed. The scientific and practical novelty of the obtained results consists of the following: mathematical models of EHA and PC of the aggregate have been developed; simulation model of the aggregate on the test bench has been developed; simulation of various faults of the aggregate units has been carried out and identification of parameters of mathematical models of these units has been carried out; changes of estimations of parameters of mathematical models of EHA and PC depending on changes of each influencing factor have been obtained; upper and lower permissible limits of parameters and average values of these parameters have been determined; diagnostic features that are most probable to influence aggregate performance have been determined. It is shown that time quantization step D t = 0.01 (c) provides the determination of DS and OL displacements with errors of 1.914×10-6mm and 2.157×10-5 mm.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"23 4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125635712","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Особливості застосування альтернативних палив у теплових двигунах","authors":"O. Andriets, O. Shevchenko, Valery Ohmakevych, Mykhailo Khyzhniak","doi":"10.32620/aktt.2023.4sup1.05","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup1.05","url":null,"abstract":"The subject of the study is the use of alternative fuels and hydrogen in heat engines in different concentrations at different operating modes. The purpose of this study is to decarbonize various types of transport, especially aviation, to increase the energy efficiency and environmental performance of heat engines. Task: to investigate the use of such alternative fuels as biofuels, synthetic fuels, hydrogen and hydrogen mixtures. The use of aviation fuels shows that they must satisfy the relevant requirements, so the choice of alternative fuels must satisfy these requirements with the improvement of their characteristics, first in terms of energy efficiency and environmental indicators. To do this, starting with the ground test of a modern aircraft engine, Rolls-Royce conducted tests on an early conceptual demonstrator using green hydrogen. Green hydrogen was created by wind and tidal energy to prove that hydrogen could be the zero carbon aviation fuel of the future with zero carbon emissions. After analyzing the early ground test concept, the developers are planning a series of further bench tests leading to a full-scale ground test of a green hydrogen jet engine with the goal of achieving zero net carbon emissions from the engine Research Methods. According to the recommendations of the IPCC on the use of scarce fuel, the coefficients of harmful emissions (EI) are calculated for some types of aircraft for the Landing Take Off (LTO) cycle (landing / takeoff). Harmful emissions are calculated using the same method when alternative fuels are used in engines Since jet fuel emissions play an important role in the greenhouse effect, new technologies are being introduced to reduce emissions, among which one of the most effective and environmentally friendly is the use of biofuels, as biofuels are produced using modern biological processes. In this study, an experimental study of the influence of hydrogen addition on a traditional internal combustion diesel engine was conducted. The results. It was determined that the supply of small additions of gaseous hydrogen to the diesel manifold increases the efficiency of the engine at nominal and, largely, at partial modes of operation. The environmental parameters of the diesel engine are improved: the concentration of nitrogen oxides in the exhaust gases decreases, the soot content decreases by 30-40% and by 35%. A calculation method for the quantitative assessment of harmful emissions when using alternative fuels in aircraft engines is defined. Conclusions. The practical significance of the obtained results is that the obtained dependencies can be used when choosing the type of fuel for heat engines and determining the optimal concentration of an alternative fuel such as hydrogen to increase energy efficiency and improve the environmental performance of heat engines.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133102683","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Progress in electric propulsion numerical simulation","authors":"Sai Vigness Ramasamy, L. Bazyma","doi":"10.32620/aktt.2023.4.07","DOIUrl":"https://doi.org/10.32620/aktt.2023.4.07","url":null,"abstract":"Electric propulsion has been developed since the early 1960s, and its use onboard satellites, orbiting platforms, and interplanetary probes have increased significantly in the 21st century. The need for a detailed understanding of the working physics and a more accurate assessment of performance to create innovative designs has stimulated the development of several numerical simulation codes. The choice of method for modelling a specific thruster should be dictated by the physical characteristics of the flow in the device, and by the level of accuracy required from the simulation. There are various conditions in different types of thrusters. This means that different methods and computer codes must be developed for each of the different thrusters. The successful development of physically accurate numerical methods for simulating gas and plasma flows in electric propulsion thrusters can significantly improve the design process of these devices. In recent years, numerical simulations have increasingly benefited the basic understanding and engineering optimization of electric thrusters. This is due to several concurrent contributions: the evolution of computer hardware that has allowed the representation of multidimensional geometries and multiscale phenomena; implementation of sophisticated new algorithms and numerical diagnostic tools; and availability of new collisional and surface interaction data. There are two main directions for future work to continue to improve the numerical modelling of electric thrusters. First, the numerical methods themselves must be improved in terms of their physical accuracy and computational speed. The second main direction for improvement in the simulations involves more accurate determination of physical parameters that are required by the numerical formulations. This paper outlines efforts to develop models of various electrical propulsion concepts, from the first attempts in the early 90s to the latest sophisticated multidimensional simulations.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"87 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114331207","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Закони керування авіаційним газотурбінним двигуном з турбовентиляторною приставкою","authors":"Serhii Tovkach","doi":"10.32620/aktt.2023.4sup1.10","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup1.10","url":null,"abstract":"The main aspects of the general task of integrating an aviation engine (AE) with a turbofan additional unit (TAU) of a multi-mode aircraft are the selection of the scheme and design parameters of the AE with the TAU (including parameters of the work process), as well as methods and means of automatic control of the AE with the TAU for better matching its characteristics with certain flight modes. These two tasks are closely interrelated: on the one hand, when determining the appearance of the aircraft and its power plant (PP), it is necessary to consider what means will ensure the adaptation of its characteristics to the variable flight mode, and on the other hand, the purpose of the aircraft, its parameters and parameters of the PP, and the flight modes mostly determine the choice of control laws. The subject of the research is the formation of the laws of control of the aviation gas turbine engine with TAU. The goal is to improve the dynamic characteristics of the aviation gas turbine engine by applying adaptive control of the gas turbine engine with the use of wireless information exchange technologies. Objectives: to generalize the concept of adaptive control at the stage of determining the appearance of an engine with TAU; to determine the methods of regulating the GTE with TAU and their influence on the speed characteristics; to describe the process of formation of the laws governing AE with TAU; to investigate thermal processes in order to find functional dependencies in the optimal control of gas turbines with TAU. Research methods: system analysis, mathematical and computer modeling were used in the formation of control laws; the methods of philosophical knowledge were used to build an approach to the design of adaptive control systems of gas turbines with TAU. The theory of aircraft engines, the theory of differential equations, difference grids, and numerical methods were used to optimize the control of gas turbines with TAU. Results: methods of regulating the GTE with TAU and their influence on the speed characteristics of the aviation engine; formulas for researching the thermal processes of the working blades of the GTE with TAU in order to form the influence of the regulator on the executive mechanisms. Scientific and practical novelty: formation of a paradigm for the development of models of adaptive control of GTE with TAU, considering different flight modes of the aircraft and engine operation modes. The selection of control laws using multi-parameter optimization methods for finding the relationship between structural and component schemes of the gas generator and turbofan additional unit. The character of the engine thrust change depending on the input temperature is shown, which in turn, will allow to increase the efficiency of the fan and obtain a thrust reserve. The research directions of the temperature field and stress field were formed.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124767467","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Формування динамічних моделей газотурбінних двигунів для використання в системах автоматичного керування та контролю","authors":"Sergiy Yepifanov, Oleksii Bondarenko","doi":"10.32620/aktt.2023.4.06","DOIUrl":"https://doi.org/10.32620/aktt.2023.4.06","url":null,"abstract":"The subject of the study is the process of forming a mathematical model (MM) of an aviation gas turbine engine, which provides the calculation of parameters of the work process in stable and transient operating modes for use in the evaluation of dynamic characteristics, in the analysis and synthesis of automatic engine and aircraft control systems, as part of aviation simulators, and in on-board control and diagnostics algorithms. The goal is to substantiate the structure and methodology of MM formation, intended for use in real and accelerated time scale systems. Task: formulation of requirements for MM, substantiation of the interaction between static and dynamic submodels, substantiation of the composition of arguments and the way of considering the influence of external conditions, as well as the position of the elements of the mechanization of the gas flow duct. For this, the methods of the theory of airjet engines are used. The following results were obtained: the requirements for MM of aircraft gas turbine engines designed to solve the problems of engine and aircraft control were formulated, and the structural forms of MM were substantiated, which ensure high accuracy of modeling with minimal complexity and the possibility of real-time implementation. The scientific and practical novelty of the obtained results is as follows: the requirements for dynamic MM of aircraft engines have been summarized, the problems of structural implementation and combination of static and dynamic submodels, the rational selection of their input parameters and considering the influence of external conditions on static and dynamic characteristics have been analyzed, the software implementation of MM in in the Matlab Simulink environment of a two-shaft turbofan engine and compared the simulation results obtained using the developed simplified MM and the original nonlinear thermo-gas-dynamic model based on the solution of the joint operation equations of components. It is shown that in the working range of modes, the MM error does not exceed 5%, the dynamic errors of the rotor rotation frequencies are less than 4%, the compressor pressure and gas temperature are less than 7%, or the thrust is less than 10%. Errors in estimating the duration of acceleration and deceleration of the engine are within 0.2...0.6 s.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130343993","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Вплив температурного перепаду на ступінь підвищення тиску у вентиляторному контурі турбовентиляторної приставки ГТД","authors":"Roman Maiboroda","doi":"10.32620/aktt.2023.4sup2.09","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup2.09","url":null,"abstract":"The subject of this study is the working process in a turbofan attachment of a gas turbine engine. The object of study is the fan part of the impeller of a turbofan attachment. The aim of this study was to evaluate the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. To achieve this goal, the following tasks were solved: to simulate the flow in a turbofan attachment; to calculate the dependence of the degree of pressure increase in the fan part of the impeller of the turbofan attachment on the Mach number for the operating mode at altitudes of 0 km, 9 km and 11 km; to evaluate the temperature difference in the two-tier impeller of the turbofan attachment. The study was carried out by the method of numerical experiment. Results: The dependence of the degree of pressure increase of the fan circuit of the turbofan attachment on the Mach number at the inlet is obtained, taking into account the effect of hot gases of the turbine circuit of the turbofan attachment. It is shown that the flow of hot gases affects the degree of pressure increase in the fan circuit. The presence of the turbine part of the two-tier impeller leads to a slight deterioration in the characteristics of the fan part. The degree of pressure increase is reduced by 0.2 ... 4.8 %. The greatest influence is manifested in the operating mode H = 11 km. Visualization of the flow velocity field in the fan part of the turbofan unit showed that during the operation of the turbine circuit, the nature of the leakage in the fan part changes by approximately 50% of the blade height. An increase in temperature contributes to the intensification of the energy of the boundary layer around the lower part of the blade of the fan circuit, which has a positive effect on the reduction of zero velocity zones during the flow. Scientific novelty and practical significance: new data were obtained on the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. The results obtained can be used to optimize the turbofan attachment of a gas turbine engine.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"57 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132354601","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Порівняльний аналіз систем програмування мікроконтролерів серії STM32 у виробах авіаційного застосування","authors":"Serhii Vialov, Andrii Dunai","doi":"10.32620/aktt.2023.4sup2.08","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup2.08","url":null,"abstract":"The subject of the research is the software development environment for STM32 series microcontrollers, which play an important role in the electronic support of modern aviation and are an integral part of the development process of aircraft systems. Goal. The selection of the most current STM32 series microcontroller programming system for aviation products. Tasks. Overview of major popular software development environments for STM32 microcontrollers such as STM32CubeIDE, VisualGDB, IAR Embedded Workbench for ARM, Keil MDK, Arm Development Studio, and Simulink. Various aspects of programming systems are considered, including software development, feature availability, and integration with development tools and environments. Research methods. Carrying out a comparative analysis; separation of the characteristic features of the use of programming environments in avionic devices using the example of JSC \"Element\". In view of the use of environments in the field of avionics, special attention was paid to certification and reliability using examples of safety standards, verification, and testing tools. The results. It was found that code debugging, memory analysis, code optimization, and other basic functions are inherent to all considered development environments. Distinguishing features inherent in individual programming environments are identified, including microcontroller robot simulation, high performance and compilation speed, open source code, optimization, support from the manufacturer, and a wealth of documentation, including user manuals, code examples, support forums, training courses, webinars, and articles from development companies. Conclusions (scientific and practical novelty). The results of the analysis provide important conclusions regarding the better choice of STM32 microcontroller programming systems in aviation products. The comparisons and analyses made will help software developers choose the most suitable programming system for their specific needs. A conclusion was made about the feasibility of using development environments such as IAR Embedded Workbench for ARM and STM32CubelIDE for developing aviation software based on STM32.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"123 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114608026","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ринок та перспективи газотурбінних двигунів для важких транспортних гелікоптерів","authors":"Vadym Nerubaskyi","doi":"10.32620/aktt.2023.4sup1.01","DOIUrl":"https://doi.org/10.32620/aktt.2023.4sup1.01","url":null,"abstract":"The subject of this study is the current state of the market and prospects for the development of heavy transport helicopters and their power plants. This article provides a classification of helicopters and a segment of medium-heavy and heavy helicopters with gas turbine engines. The field of application of such helicopters is briefly described. The purpose of this article is to evaluate the activities of Element JSC in the field of developing electronic control systems for gas turbine engines for heavy class helicopters. Such systems for Element JSC, in particular, are RDTs-2500 and RDTs-450M-117B units for TV3-117VMA-SBM-1B series turboshaft engines, created by Motor Sich JSC. Objective: To provide information on the main types of heavy helicopters manufactured and operated today, as well as a description of the gas turbine engines installed on these helicopters. The field of application of such helicopters is briefly described. The segment of heavy helicopters with gas turbine engines is the largest in terms of money on the world market of civil helicopters, and the forecast of deliveries of such helicopters for the next 5-7 years is given. Most helicopter models are not completely new developments, but have been improved over many years. Characteristic design features of heavy helicopters with gas turbine engines, features of the arrangement of units and equipment are given. The main structural and structural features of gas turbine engines of various manufacturers and the types of helicopters on which they are installed are given. Brief information on Russian and Ukrainian gas turbine engines - VK-2500 and TV3-117VMA-SBM-1B is provided separately. The results. Despite the active development of eVTOL technologies in the sector of small rotorcrafts, the development and improvement of gas turbine engines continues. Heavy helicopters of both traditional and non-traditional designs are being developed. Conclusions. Modernization of the design and \"remotorization\" of the Mi-8 helicopter is a good opportunity for \"Motor-Sich Helicopters\", but it needs its own developments. Many promising Ukrainian developments were canceled due to the war. Analysis of the technical characteristics of TVaD for heavy helicopters shows that domestic engines are almost in no way inferior to their European and American competitors. Promising TVaD of SE \"Ivchenko-Progress\" AI-130 with a capacity of 3,000 hp. can become an even more attractive proposition.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"449 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123054451","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Температурна характеристика електричного опору тензометра при вимірюванні статичних та термічних напружень деталей при температурі до 700 °С","authors":"Serhiy Kryhin, Yuriy Husyev, Yuriy Torba","doi":"10.32620/aktt.2023.4.01","DOIUrl":"https://doi.org/10.32620/aktt.2023.4.01","url":null,"abstract":"An overview of the existing methods of measuring static stresses at elevated temperatures, at which it is problematic to use classical strain gauges, and methods of compensating the imaginary temperature deformation was performed. Namely: the use of multi-component alloys, the manufacture of active and compensatory sensitive elements from different alloys, which should theoretically compensate for each other's shortcomings. In practice, this can be sufficiently achieved only in a narrow temperature range. The described primary transducer is a rectangular strain-gauge rosette for measuring static and thermal stresses in structural parts operating under extreme conditions at temperatures up to 700°C. This sensor is a two-layer rosette consisting of two sensitive elements (SE), the main axes of which are rotated relative to each other by 90°. The lower SE perceives the main deformation of the part, and the upper one, located above the lower one, plays the role of a temperature-compensating electrical resistance of the element and simultaneously registers the transverse deformation of the part. SE rosettes were made of a wire with a diameter of 30 microns of the Х20Н80 alloy and fixed to each other and to the part using Ц-165-32А cement. The experimental study consisted in determining the temperature characteristics of the resistance of both the lower and the upper SE of the studied strain gauge associated with the temperature expansion of the part-strain gauge system as well as with the shunting of the insulator-connector and the change in the specific resistance of the SE material. Experimental determination of apparent strain gauge deformation at different temperatures was performed. To determine the influence of the coefficient of linear expansion of the material of the part on the change in the resistance of the SE, strain gauges were attached to samples of various materials. The change in the apparent deformation of the strain gauge in the temperature range from room temperature to 700 °C is shown. Its maximum value for the ceramic sample was less than 350 µm/m, for the 30ХГСА steel sample it was less than 1000 µm/m, and for the ВЖЛ14Н-ВІ alloy sample it was less than 750 µm/m. Dependencies were obtained that allow corrections to be made in the result of a real study of the stressed state of the part to achieve the maximum accuracy of measurements.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124631591","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}