Z. A. Yudina, M. I. Sinichenko, A. P. Ladigin, F. K. Sin'kovskiy, D. B. Usmanov
The important problem for rocket-space, aviation and transport equipment fields is designing high-resource electric pumps. Electric pumps are active energy conversion devices to provide the thermal control system operation. Electric pumps failure leads to fault of the interfaced equipment, system failures and significant economic damage accidents. The most unfavorable factor for electric pump reliability is vibration. That the reason of relevance, practicability and importance to research the electric pumps vibration activity, the reasons for the appearance of vibrations and ways to control them. The paper provides the main sources of electric pump of the spacecraft vibrations as mechanical, hydrodynamic and electrical. This paper presents the recommendations of foreign and domestic authors to control each vibration source. To solve the problem of reducing the electric pump vibration activity the research of the technical level of existing developments, results, main technical solutions and technical solutions trends was produced. The main directions of further electric pump vibration activity researches leading to decreasing of vibration activity were defined on this paper.
{"title":"The vibration origin in the electric pump of the spacecraft and methods to reduce them","authors":"Z. A. Yudina, M. I. Sinichenko, A. P. Ladigin, F. K. Sin'kovskiy, D. B. Usmanov","doi":"10.26732/j.st.2021.2.01","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.01","url":null,"abstract":"The important problem for rocket-space, aviation and transport equipment fields is designing high-resource electric pumps. Electric pumps are active energy conversion devices to provide the thermal control system operation. Electric pumps failure leads to fault of the interfaced equipment, system failures and significant economic damage accidents. The most unfavorable factor for electric pump reliability is vibration. That the reason of relevance, practicability and importance to research the electric pumps vibration activity, the reasons for the appearance of vibrations and ways to control them. The paper provides the main sources of electric pump of the spacecraft vibrations as mechanical, hydrodynamic and electrical. This paper presents the recommendations of foreign and domestic authors to control each vibration source. To solve the problem of reducing the electric pump vibration activity the research of the technical level of existing developments, results, main technical solutions and technical solutions trends was produced. The main directions of further electric pump vibration activity researches leading to decreasing of vibration activity were defined on this paper.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45321113","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}
An important stage in the development of temperature control interface modules for measuring instruments, implemented according to the main-modular principle of construction on the basis of a central instrument module and used as part of a measuring system on spacecraft for various purposes, is to ensure their noise-immune operation when the measuring system is exposed to a combination of various types of interference which determine the electromagnetic environment on the spacecraft. The article is devoted to the analysis of the characteristics of various types of interference affecting the measuring system, identifying the ways of their penetration into the temperature control interface module and determining the influence of the characteristics of these interference on the choice of measures to ensure the required noise immunity of the temperature control interface module as part of the measuring device. It is shown that the paths of interference penetration into the interface temperature control module depend on the frequency and time characteristics of the interference affecting the measuring system. Measures to mitigate these interference must be determined after assessing the danger of their penetration into the interface temperature control module for each path separately in the entire frequency range of their impact. Based on the results of such assessments, a set of reasonable measures should be determined to ensure the noise immunity of the interface temperature control module as part of the measuring device, implemented in combination at the design levels of the measuring system, the measuring device and the interface temperature control module.
{"title":"Features of ensuring noise immunity of interface modules for temperature control in measuring instruments of spacecraft","authors":"A. I. Gornostaev","doi":"10.26732/j.st.2021.2.04","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.04","url":null,"abstract":"An important stage in the development of temperature control interface modules for measuring instruments, implemented according to the main-modular principle of construction on the basis of a central instrument module and used as part of a measuring system on spacecraft for various purposes, is to ensure their noise-immune operation when the measuring system is exposed to a combination of various types of interference which determine the electromagnetic environment on the spacecraft. The article is devoted to the analysis of the characteristics of various types of interference affecting the measuring system, identifying the ways of their penetration into the temperature control interface module and determining the influence of the characteristics of these interference on the choice of measures to ensure the required noise immunity of the temperature control interface module as part of the measuring device. It is shown that the paths of interference penetration into the interface temperature control module depend on the frequency and time characteristics of the interference affecting the measuring system. Measures to mitigate these interference must be determined after assessing the danger of their penetration into the interface temperature control module for each path separately in the entire frequency range of their impact. Based on the results of such assessments, a set of reasonable measures should be determined to ensure the noise immunity of the interface temperature control module as part of the measuring device, implemented in combination at the design levels of the measuring system, the measuring device and the interface temperature control module.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48004942","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}
The purpose of the study is an analytical description of the section of the ballistic trajectory corresponding to the normal fall of the spacecraft on the surface of an atmosphereless planet. In this case, the motion of a normally falling body is characterized by an increasing acceleration of gravity. The problem of the speed, time and acceleration of the normal fall of a body on the planet's surface in the absence of an atmosphere is reduced to solving a second-order differential equation, which is solved by the standard method. A feature of the solution is the formal use of the tabular integral at an intermediate stage. It turned out, however, that his formula is unreliable, namely, the derivative of the right-hand side is not equal to the integrand. It follows from this that the possible existing solutions to this problem, based on the use of the indicated tabular integral, are incorrect. The article presents the correction of this tabular integral, which is an incidental result of the study. In this work, the time equation of motion of a body normally falling on the surface of the planet in the absence of an atmosphere, as well as the time equations of its speed and acceleration are obtained. The results obtained can be useful in calculating passive gravity assist during interplanetary flights and calculating the sheer fall of small celestial bodies and spent structural element s of spacecraft.
{"title":"Elements of ballistic calculation for spacecraft gravity assist","authors":"I. Popov","doi":"10.26732/j.st.2021.2.02","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.02","url":null,"abstract":"The purpose of the study is an analytical description of the section of the ballistic trajectory corresponding to the normal fall of the spacecraft on the surface of an atmosphereless planet. In this case, the motion of a normally falling body is characterized by an increasing acceleration of gravity. The problem of the speed, time and acceleration of the normal fall of a body on the planet's surface in the absence of an atmosphere is reduced to solving a second-order differential equation, which is solved by the standard method. A feature of the solution is the formal use of the tabular integral at an intermediate stage. It turned out, however, that his formula is unreliable, namely, the derivative of the right-hand side is not equal to the integrand. It follows from this that the possible existing solutions to this problem, based on the use of the indicated tabular integral, are incorrect. The article presents the correction of this tabular integral, which is an incidental result of the study. In this work, the time equation of motion of a body normally falling on the surface of the planet in the absence of an atmosphere, as well as the time equations of its speed and acceleration are obtained. The results obtained can be useful in calculating passive gravity assist during interplanetary flights and calculating the sheer fall of small celestial bodies and spent structural element s of spacecraft.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48612939","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}
Z. A. Yudina, M. I. Sinichenko, A. P. Ladigin, F. K. Sin'kovskiy, A. D. Kuznetsov
Improvement of heat transfer efficiency of the spacecraft thermal control subsystem constitutes a relevant problem for today space industry. Two phase thermal control system presents the most suitable solution for this problem. Implementation of reliable thermal control loop elements constitutes one the major prerequisites for reliability of thermal control systems featuring the operating pressure of 4.8 MPa and ammonia as heat fluid. This paper presents the design and test results of manual valve and fill and drain valve to be operated within the spacecraft two phase thermal control subsystem. The paper provides considerations and detailed description of the technical solutions adopted to ensure compliance with the specification requirements such as operating pressure and plug seat leak tightness under the operating pressure and 160 open/close cycles. Valve plug torque selection criteria are described. The employed design and technical solutions as well as qualification test results have proven that the units designed feature outstanding combination of performances such as leak tightness, life cycle with ammonia as heat fluid.
{"title":"Valve for two-phase fluid loop","authors":"Z. A. Yudina, M. I. Sinichenko, A. P. Ladigin, F. K. Sin'kovskiy, A. D. Kuznetsov","doi":"10.26732/j.st.2021.2.03","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.03","url":null,"abstract":"Improvement of heat transfer efficiency of the spacecraft thermal control subsystem constitutes a relevant problem for today space industry. Two phase thermal control system presents the most suitable solution for this problem. Implementation of reliable thermal control loop elements constitutes one the major prerequisites for reliability of thermal control systems featuring the operating pressure of 4.8 MPa and ammonia as heat fluid. This paper presents the design and test results of manual valve and fill and drain valve to be operated within the spacecraft two phase thermal control subsystem. The paper provides considerations and detailed description of the technical solutions adopted to ensure compliance with the specification requirements such as operating pressure and plug seat leak tightness under the operating pressure and 160 open/close cycles. Valve plug torque selection criteria are described. The employed design and technical solutions as well as qualification test results have proven that the units designed feature outstanding combination of performances such as leak tightness, life cycle with ammonia as heat fluid.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43563091","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}
A significant number of patents and publications in the open press show the intensity of the ongoing research to create new methods of synchronization and specialized ground-based equipment for frequency-time synchronization. The article considers the implementation of an autonomous synchronization system between ground-based satellite communication points, which is used in conditions of unfavorable reception or absence of signals from global navigation satellite systems. The paper presents studies on the assessment of the error of time synchronization of geographically separated ground points of satellite communications. The basics of constructing the receiving equipment of a radio engineering system are considered and the mutual correlation of the reference signal of the receiving equipment and the received input synchronization signal is calculated. The results of field tests of mutual synchronization equipment are presented, where the potential synchronization accuracy of equipment at ground objects with previously unknown coordinates was determined, while the synchronization equipment provided measurement of the signal propagation time from one ground object to another with the formation of universal time scales on points. The method of mutual synchronization of linked points is carried out by the duplex method at a frequency of 1065 MHz (request) and 625 MHz (response) by phase-code-manipulated signals with a base equal to 1023 and a duration of 0,1 ms.
{"title":"Estimation of the synchronization error for spaced-apart ground points of satellite communication","authors":"R. Kovalev, V. V. Kornienko, V. N. Ratushnak","doi":"10.26732/j.st.2021.2.05","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.05","url":null,"abstract":"A significant number of patents and publications in the open press show the intensity of the ongoing research to create new methods of synchronization and specialized ground-based equipment for frequency-time synchronization. The article considers the implementation of an autonomous synchronization system between ground-based satellite communication points, which is used in conditions of unfavorable reception or absence of signals from global navigation satellite systems. The paper presents studies on the assessment of the error of time synchronization of geographically separated ground points of satellite communications. The basics of constructing the receiving equipment of a radio engineering system are considered and the mutual correlation of the reference signal of the receiving equipment and the received input synchronization signal is calculated. The results of field tests of mutual synchronization equipment are presented, where the potential synchronization accuracy of equipment at ground objects with previously unknown coordinates was determined, while the synchronization equipment provided measurement of the signal propagation time from one ground object to another with the formation of universal time scales on points. The method of mutual synchronization of linked points is carried out by the duplex method at a frequency of 1065 MHz (request) and 625 MHz (response) by phase-code-manipulated signals with a base equal to 1023 and a duration of 0,1 ms.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48754450","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}
V. Blinov, V. M. Vladimirov, S. Kulinich, A. Nikiforov, D. N. Pridachin, D. Pchelyakov, O. Pchelyakov, L. Sokolov, D. V. Yarockiy
This article describes the features of the equipment developed at the Rzhanov Institute of Semiconductor Physics for conducting experiments on growing semiconductor heterostructures from molecular beams in outer space under the conditions of an orbital flight of the International Space Station. Working out the processes of epitaxy of semiconductor films in outer space will allow us to grow complex semiconductor structures with sharp boundaries, which serve as the basis for the creation of solar cells, as well as devices of modern microwave, optoand microelectronics. Cascade photovoltaic converters based on such multilayer heterostructures of A3B5 semiconductor compounds have high efficiency and radiation resistance and, therefore, are most widely used for the manufacture of space solar cells. The high efficiency of such batteries is due to the wide spectral range in which solar radiation is effectively absorbed and used in photovoltaic conversion.
{"title":"Equipment for growing semiconductor heterostructures in outer space","authors":"V. Blinov, V. M. Vladimirov, S. Kulinich, A. Nikiforov, D. N. Pridachin, D. Pchelyakov, O. Pchelyakov, L. Sokolov, D. V. Yarockiy","doi":"10.26732/j.st.2021.2.06","DOIUrl":"https://doi.org/10.26732/j.st.2021.2.06","url":null,"abstract":"This article describes the features of the equipment developed at the Rzhanov Institute of Semiconductor Physics for conducting experiments on growing semiconductor heterostructures from molecular beams in outer space under the conditions of an orbital flight of the International Space Station. Working out the processes of epitaxy of semiconductor films in outer space will allow us to grow complex semiconductor structures with sharp boundaries, which serve as the basis for the creation of solar cells, as well as devices of modern microwave, optoand microelectronics. Cascade photovoltaic converters based on such multilayer heterostructures of A3B5 semiconductor compounds have high efficiency and radiation resistance and, therefore, are most widely used for the manufacture of space solar cells. The high efficiency of such batteries is due to the wide spectral range in which solar radiation is effectively absorbed and used in photovoltaic conversion.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46464296","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}
The paper is devoted to the non-coplanar interplanetary Earth–Venus flight of a spacecraft equipped with a non-perfectly reflecting solar sail, the magnitude and direction of acceleration from which is calculated taking into account specular and diffuse reflections, absorption and transmission of photons by the surface of the solar sail. The goal of the heliocentric motion is to transfer the solar sail spacecraft into the Hill sphere of Venus with zero hyperbolic excess of speed. A feature of the paper is the study of the motion of a non-perfectly reflecting solar sail spacecraft taking into account the motion relative to the center of mass. The problem is divided into three stages. At the first stage, a nominal program for controlling the motion of the spacecraft center of mass is formed. At the second stage, sufficient angular velocities are determined to ensure the obtained nominal control program and the parameters of the spacecraft controls – thin-film controls located along the perimeter of the solar sail – are calculated. The operating principle of the thin-film controls is quite simple. When the voltage applied to the thin-film controls changes, they become transparent or opaque, there is a difference in the normal components of the light pressure forces, which provides a control torque for changing the orientation of the spacecraft in space. At the third stage, the joint motion of the center of mass and relative to the center of mass of the spacecraft is simulated to demonstrate the feasibility of the obtained control program. As a result, a comparison is made of non-coplanar interplanetary Earth–Venus flights with and without thin-film control elements.
{"title":"Non-coplanar interplanetary flight simulation considering motion relative to the center of mass peculiarities of solar sail spacecraft","authors":"R. Khabibullin, O. Starinova","doi":"10.26732/j.st.2020.3.02","DOIUrl":"https://doi.org/10.26732/j.st.2020.3.02","url":null,"abstract":"The paper is devoted to the non-coplanar interplanetary Earth–Venus flight of a spacecraft equipped with a non-perfectly reflecting solar sail, the magnitude and direction of acceleration from which is calculated taking into account specular and diffuse reflections, absorption and transmission of photons by the surface of the solar sail. The goal of the heliocentric motion is to transfer the solar sail spacecraft into the Hill sphere of Venus with zero hyperbolic excess of speed. A feature of the paper is the study of the motion of a non-perfectly reflecting solar sail spacecraft taking into account the motion relative to the center of mass. The problem is divided into three stages. At the first stage, a nominal program for controlling the motion of the spacecraft center of mass is formed. At the second stage, sufficient angular velocities are determined to ensure the obtained nominal control program and the parameters of the spacecraft controls – thin-film controls located along the perimeter of the solar sail – are calculated. The operating principle of the thin-film controls is quite simple. When the voltage applied to the thin-film controls changes, they become transparent or opaque, there is a difference in the normal components of the light pressure forces, which provides a control torque for changing the orientation of the spacecraft in space. At the third stage, the joint motion of the center of mass and relative to the center of mass of the spacecraft is simulated to demonstrate the feasibility of the obtained control program. As a result, a comparison is made of non-coplanar interplanetary Earth–Venus flights with and without thin-film control elements.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45580926","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 : 2019-06-21DOI: 10.26732/2618-7957-2019-2-94-100
M. N. Utkin, A. Saybel
Navigation spacecraft’s atomic clocks suffer from sudden small frequency jumps. These jumps lead to a decrease of user’s positioning accuracy and should be considered. Traditional method to detect these frequency jumps with the use of ground control segment does not ensure early user alert of increasing range error. A perspective way to improve global navigation satellite system’s signal integrity is the use of satellite on-board autonomous system for continuous control of board synchronization equipment time scale. This paper describes a novel diagram of frequency comparator – the main element of such system. The main difference of proposed solution is an application of time-to-digital converter for estimation of time error which allows to decrease mass, dimensions and power consumption. The paper deals with the particularities of direct frequency comparator implementation for on-board equipment of space vehicle and describes structure of implemented breadboard model.
{"title":"Modernization of time scale control unit for «Glonass-K» spacecrafts","authors":"M. N. Utkin, A. Saybel","doi":"10.26732/2618-7957-2019-2-94-100","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-94-100","url":null,"abstract":"Navigation spacecraft’s atomic clocks suffer from sudden small frequency jumps. These jumps lead to a decrease of user’s positioning accuracy and should be considered. Traditional method to detect these frequency jumps with the use of ground control segment does not ensure early user alert of increasing range error. A perspective way to improve global navigation satellite system’s signal integrity is the use of satellite on-board autonomous system for continuous control of board synchronization equipment time scale. This paper describes a novel diagram of frequency comparator – the main element of such system. The main difference of proposed solution is an application of time-to-digital converter for estimation of time error which allows to decrease mass, dimensions and power consumption. The paper deals with the particularities of direct frequency comparator implementation for on-board equipment of space vehicle and describes structure of implemented breadboard model.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47975573","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 : 2019-06-21DOI: 10.26732/2618-7957-2019-2-107-113
V. Chebotarev, I. Sidorova
The creation of rocket and space production has led to a powerful development of industrial potential in the field of high technologies. Space technology has a huge innovative potential for the development of high-tech and knowledge-intensive industries, which required appropriate staffing to solve these problems. As a result, elements of the space infrastructure were created in almost every region of the country, the newest space technologies were introduced in various sectors, into the practice of managing the socio-economic development of the regions. This had a positive effect on the development of the region and its individual cities. Using the cities of the Krasnoyarsk Region as an example, assessments of the level of budget financing of the city development program were made using the developed methodology. The role of special cities and city-forming enterprises of the space industry in ensuring the innovative development of the region, including ZATO Zheleznogorsk, is revealed. Research has been conducted on the development of the space technology direction of the cluster of innovative technologies implemented by the JSC «ISS» through the modernization of production and the expansion of cooperation between cluster enterprises and universities and enterprises of the Siberian region. The role of the personnel policy of JSC «ISS» is determined, ensuring the preservation and development of the professional competencies of its employees in the field of high-tech space industries, which contributes to the innovative development of the domestic space industry.
{"title":"Space technologies – one of the basic bases of innovative development of the siberian region","authors":"V. Chebotarev, I. Sidorova","doi":"10.26732/2618-7957-2019-2-107-113","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-107-113","url":null,"abstract":"The creation of rocket and space production has led to a powerful development of industrial potential in the field of high technologies. Space technology has a huge innovative potential for the development of high-tech and knowledge-intensive industries, which required appropriate staffing to solve these problems.\u0000As a result, elements of the space infrastructure were created in almost every region of the country, the newest space technologies were introduced in various sectors, into the practice of managing the socio-economic development of the regions. This had a positive effect on the development of the region and its individual cities.\u0000Using the cities of the Krasnoyarsk Region as an example, assessments of the level of budget financing of the city development program were made using the developed methodology. The role of special cities and city-forming enterprises of the space industry in ensuring the innovative development of the region, including ZATO Zheleznogorsk, is revealed. Research has been conducted on the development of the space technology direction of the cluster of innovative technologies implemented by the JSC «ISS» through the modernization of production and the expansion of cooperation between cluster enterprises and universities and enterprises of the Siberian region. The role of the personnel policy of JSC «ISS» is determined, ensuring the preservation and development of the professional competencies of its employees in the field of high-tech\u0000space industries, which contributes to the innovative development of the domestic space industry.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46833076","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 : 2019-06-21DOI: 10.26732/2618-7957-2019-2-101-106
R. B. Kovalyov, V. N. Ratushnyak, P. Y. Zverev
At present time the most of the work of specialists in the field of navigation is to improve the parameters of navigation systems such as noise immunity and accuracy. At all the world is more and more actual the interest of consumers of high-precision navigation information and equipment manufacturers to near navigation systems, which are an addition to the existing satellite radio navigation systems, allowing them to increase their accuracy and noise immunity. Assessment the parameters is made in the article and algorithm for calculating the radio line in the near-navigation system based on pseudosatellites is generalized. A model for calculating the energy of a radio line has been developed for various configurations of the location of pseudosatellites. The developed program for calculating the characteristics of radio lines of a near-navigation system based on pseudo-satellites allows to quickly evaluate not only its energy characteristics, but also realizes pictorial visualization of the resulting directional diagram of pseudo-satellite systems in accordance with the configured navigation zone of consumers and the required power of navigation signals in natural radio routes.
{"title":"Research of parameters and calculation of the budget of the radio line in the ground-based system of near navigation on the basis of pseudo-satellites","authors":"R. B. Kovalyov, V. N. Ratushnyak, P. Y. Zverev","doi":"10.26732/2618-7957-2019-2-101-106","DOIUrl":"https://doi.org/10.26732/2618-7957-2019-2-101-106","url":null,"abstract":"At present time the most of the work of specialists in the field of navigation is to improve the parameters of navigation systems such as noise immunity and accuracy. At all the world is more and more actual the interest of consumers of high-precision navigation information and equipment manufacturers to near navigation systems, which are an addition to the existing satellite radio navigation systems, allowing them to increase their accuracy and noise immunity. Assessment the parameters is made in the article and algorithm for calculating the radio line in the near-navigation system based on pseudosatellites is generalized. A model for calculating the energy of a radio line has been developed for various configurations of the location of pseudosatellites. The developed program for calculating the characteristics of radio lines of a near-navigation system based on pseudo-satellites allows to quickly evaluate not only its energy characteristics, but also realizes pictorial visualization of the resulting directional diagram of pseudo-satellite systems in accordance with the configured navigation zone of consumers and the\u0000required power of navigation signals in natural radio routes.","PeriodicalId":33896,"journal":{"name":"Kosmicheskie apparaty i tekhnologii","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2019-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44935984","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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