Pub Date : 2021-06-01DOI: 10.33950/SPACETECH-2308-7625-2021-2-130-140
T. Kombaev, M. Artemov, V. Sysoev, D. Dezhin, Mai
It is proposed to develop a small spacecraft for an experiment using high-temperature superconductors (HTS) and shape memory materials. The purpose of the experiment is to test a technological capability of creating a strong magnetic field on the small spacecraft using HTS and shape memory materials for deployed large-area structures, and study the magnetic field interaction with the solar wind plasma and the resulting force impact on the small spacecraft. This article is of a polemical character and makes it possible to take a fresh look at the applicability of new technologies in space-system engineering. Key words: high-temperature superconductors, shape memory materials, solar wind, spacecraft.
{"title":"The small spacecraft with a magnetic sail on high-temperature superconductors","authors":"T. Kombaev, M. Artemov, V. Sysoev, D. Dezhin, Mai","doi":"10.33950/SPACETECH-2308-7625-2021-2-130-140","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2021-2-130-140","url":null,"abstract":"It is proposed to develop a small spacecraft for an experiment using high-temperature superconductors (HTS) and shape memory materials. The purpose of the experiment is to test a technological capability of creating a strong magnetic field on the small spacecraft using HTS and shape memory materials for deployed large-area structures, and study the magnetic field interaction with the solar wind plasma and the resulting force impact on the small spacecraft. This article is of a polemical character and makes it possible to take a fresh look at the applicability of new technologies in space-system engineering.\u0000Key words: high-temperature superconductors, shape memory materials, solar wind, spacecraft.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132856279","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 : 2021-06-01DOI: 10.33950/SPACETECH-2308-7625-2021-2-107-118
V. Soloviev, Rsc Energia, R. Murtazin, E. Melnikov
35 years ago, in March 1986, a unique flight of the Soyuz T-15 transport manned vehicle was performed, including in its program the flight of the crew from one orbital station to another (from the Mir station to the Salyut-7 station) and back. In the 60-year history of manned space exploration, such a double flight continues to be the only one of its kind. The article considers the circumstances that developed at the time of the Mir station launch into orbit — the first station of the 3rd generation. The approaches adopted during the development of the ballistics profile and the operational changes required during its implementation are described in detail. In conclusion, the actual fuel consumption of all spacecraft involved in this scheme is presented. It is assumed that the experience gained during the implementation of flights can be used in future promising manned missions, both in near-Earth orbit and in the implementation of the future Lunar program. Key words: orbital station Salyut, orbital station Mir, manned vehicle, orbital flights, prospective human missions.
{"title":"Chronicle of an extraordinary space journey (ballistic analysis of Soyuz T-15 flight)","authors":"V. Soloviev, Rsc Energia, R. Murtazin, E. Melnikov","doi":"10.33950/SPACETECH-2308-7625-2021-2-107-118","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2021-2-107-118","url":null,"abstract":"35 years ago, in March 1986, a unique flight of the Soyuz T-15 transport manned vehicle was performed, including in its program the flight of the crew from one orbital station to another (from the Mir station to the Salyut-7 station) and back. In the 60-year history of manned space exploration, such a double flight continues to be the only one of its kind. The article considers the circumstances that developed at the time of the Mir station launch into orbit — the first station of the 3rd generation. The approaches adopted during the development of the ballistics profile and the operational changes required during its implementation are described in detail. In conclusion, the actual fuel consumption of all spacecraft involved in this scheme is presented. It is assumed that the experience gained during the implementation of flights can be used in future promising manned missions, both in near-Earth orbit and in the implementation of the future Lunar program. \u0000Key words: orbital station Salyut, orbital station Mir, manned vehicle, orbital flights, prospective human missions.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"128 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128126717","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 : 2021-06-01DOI: 10.33950/SPACETECH-2308-7625-2021-2-97-108
A. Levandovich, Msa named after A.F. Mozhaisky, D. Mosin, A. Tyutyukin, I. Urtmintsev, V. Sinyavskiy, Rsc Energia
The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper stage (EPUS) – a space transportation stage (a space tug) with main engines based on electric propulsion powered by solar arrays. It addresses the problem of deploying a multi-plane orbital constellation of small spacecraft (SSC) using an electrically propelled upper stage. It proposes to change the SSC operational orbital planes based on the effect of the difference in precession rates between the parking and the working orbits owing to the effect of eccentricity in the Earth gravitational field. Requirements have been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type. Key words: Electrically propelled upper stage, electric propulsion, small spacecraft, orbital constellation.
{"title":"Conceptual design studies of an electrically propelled upper stage for deployment of a multi-plane orbital constellation of small spacecraft","authors":"A. Levandovich, Msa named after A.F. Mozhaisky, D. Mosin, A. Tyutyukin, I. Urtmintsev, V. Sinyavskiy, Rsc Energia","doi":"10.33950/SPACETECH-2308-7625-2021-2-97-108","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2021-2-97-108","url":null,"abstract":"The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper stage (EPUS) – a space transportation stage (a space tug) with main engines based on electric propulsion powered by solar arrays. It addresses the problem of deploying a multi-plane orbital constellation of small spacecraft (SSC) using an electrically propelled upper stage. It proposes to change the SSC operational orbital planes based on the effect of the difference in precession rates between the parking and the working orbits owing to the effect of eccentricity in the Earth gravitational field. Requirements have been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. \u0000It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type.\u0000Key words: Electrically propelled upper stage, electric propulsion, small spacecraft, orbital constellation.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114394249","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 : 2021-06-01DOI: 10.33950/SPACETECH-2308-7625-2021-2-109-118
Igor V. Orlovskiy, Rsc Energia, M. Mikhailov, S. Rozhkov, G. Avanesov, B. Zhukov, Sri Ras
The paper discusses an integrated system for spacecraft rendezvous and docking using measurements from satellite navigation equipment combined with the optical final approach subsystem (OFAS) which generates high-precision relative position vector during final approach It addresses issues involved in designing an OFAS which has to operate in an environment exposed to sunlight and provides an estimate for the accuracy of the relative position measurements depending on the current range and OFAS configuration. Simulations have been run of the final approach involving simultaneous control for m the satellite navigation equipment and OFAS. It was shown that at the moment of initial contact the approach accuracy of 2–5 cm for relative position, and of 1 cm/s for velocity is achieved. Key words: spacecraft, navigation, rendezvous, docking, final approach, satellite navigation, optical sensor, TV camera, control, precision.
{"title":"Spacecraft rendezvous and docking using measurements from satellite navigation equipment combined with the optical subsystem for final approach","authors":"Igor V. Orlovskiy, Rsc Energia, M. Mikhailov, S. Rozhkov, G. Avanesov, B. Zhukov, Sri Ras","doi":"10.33950/SPACETECH-2308-7625-2021-2-109-118","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2021-2-109-118","url":null,"abstract":"The paper discusses an integrated system for spacecraft rendezvous and docking using measurements from satellite navigation equipment combined with the optical final approach subsystem (OFAS) which generates high-precision relative position vector during final approach It addresses issues involved in designing an OFAS which has to operate in an environment exposed to sunlight and provides an estimate for the accuracy of the relative position measurements depending on the current range and OFAS configuration. Simulations have been run of the final approach involving simultaneous control for m the satellite navigation equipment and OFAS. It was shown that at the moment of initial contact the approach accuracy of 2–5 cm for relative position, and of 1 cm/s for velocity is achieved.\u0000Key words: spacecraft, navigation, rendezvous, docking, final approach, satellite navigation, optical sensor, TV camera, control, precision.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133177822","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 : 2021-06-01DOI: 10.33950/SPACETECH-2308-7625-2021-2-119-127
V. Dushin, Rsc Energia, A. Krylov, A. Skorovarov
In view of the increasing number of science experiments being carried out in the Russian Segment of the International Space Station, there is a growing interest in the state of the environment where they are conducted, especially, in the contaminating effects of the external induced atmosphere. Sources of the induced atmosphere contamination are the off-gassing of non-metallic materials of the outer coatings, firings of control system thrusters and exhausts of various venting systems, as well as dust particles remaining on the external surfaces after launch from Earth, atmospheric aerosols and space dust. The paper presents results of measurements of molecular depositions on the sensors of quartz crystal microbalances that were used for evaluating contamination in the induced atmosphere of the first Soviet orbital stations Salyut-7 and Mir, as well as modules Pirs and Poisk of the Russian Segment of the International Space Station. The results of the experiments show a significant effect of lighting and thermal conditions of the contamination source and the quartz microbalance sensor on the measurement results. Key words: contamination, quartz crystal microbalance, orbital, external induced atmosphere.
{"title":"Measuring contamination levels in external induced atmosphere of Russian orbital stations and the Russian Segment of the International Space Station","authors":"V. Dushin, Rsc Energia, A. Krylov, A. Skorovarov","doi":"10.33950/SPACETECH-2308-7625-2021-2-119-127","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2021-2-119-127","url":null,"abstract":"In view of the increasing number of science experiments being carried out in the Russian Segment of the International Space Station, there is a growing interest in the state of the environment where they are conducted, especially, in the contaminating effects of the external induced atmosphere. Sources of the induced atmosphere contamination are the off-gassing of non-metallic materials of the outer coatings, firings of control system thrusters and exhausts of various venting systems, as well as dust particles remaining on the external surfaces after launch from Earth, atmospheric aerosols and space dust. The paper presents results of measurements of molecular depositions on the sensors of quartz crystal microbalances that were used for evaluating contamination in the induced atmosphere of the first Soviet orbital stations Salyut-7 and Mir, as well as modules Pirs and Poisk of the Russian Segment of the International Space Station. The results of the experiments show a significant effect of lighting and thermal conditions of the contamination source and the quartz microbalance sensor on the measurement results.\u0000Key words: contamination, quartz crystal microbalance, orbital, external induced atmosphere.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130377700","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 : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-5-19
Gennady V. Lebedev, O. Evseenko
The paper analyzes engineering and operational solutions implemented in rocket and space system Vostok to assure crew safety during ascent in view of the need to complete the work on an extremely short notice. It reviews the results of flight tests of launch vehicles belonging to the R7 family and the status of during prelaunch processing and ascent phase. The paper draws comparisons between work to develop a crew escape system by the time when the first manned mission of Vostok spacecraft took place. It provides an analysis of emergencies and measures to assure safety our country’s project Vostok and US project Mercury. Key words: rocket and space system, spacecraft, descent vehicle, crew safety.
{"title":"KEY ENGINEERING SOLUTIONS IMPLEMENTED IN ROCKET AND SPACE SYSTEM VOSTOK TO ASSURE CREW SAFETY DURING ASCENT (towards 60th anniversary of the first man in space)","authors":"Gennady V. Lebedev, O. Evseenko","doi":"10.33950/SPACETECH-2308-7625-2020-4-5-19","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-5-19","url":null,"abstract":"The paper analyzes engineering and operational solutions implemented in rocket and space system Vostok to assure crew safety during ascent in view of the need to complete the work on an extremely short notice. It reviews the results of flight tests of launch vehicles belonging to the R7 family and the status of during prelaunch processing and ascent phase. The paper draws comparisons between work to develop a crew escape system by the time when the first manned mission of Vostok spacecraft took place. It provides an analysis of emergencies and measures to assure safety our country’s project Vostok and US project Mercury.\u0000Key words: rocket and space system, spacecraft, descent vehicle, crew safety.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"64 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122692352","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 : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-127-141
V. Kovtun, A. N. Pavlov, B. Sokolov, D. Pavlov, V. N. Vorotyagin
A key condition for accomplishing a mission of an unmanned spacecraft consists in providing it with resources. Resources can be replenished through synergetic observations of processes in cases where measured data are partially or fully missing or lacking for some of the controlled objects by means of measuring parameters of the processes characterizing the operation of other controlled objects. As an example, the paper discusses provisioning of resources for the process of controlling the motion about the center of mass by means of synergetic observations in cases where no inertial instrument was available for measuring the angular rate vector in the system controlling the motion of the geostationary communications satellite Yamal-200. Specifically, the observation is based on the operation of transitive closure of the binary relation defined on the base set of processes in the onboard systems and ground assets for radio interactions with the onboard systems of the unmanned spacecraft. Key words: unmanned spacecraft, control process, measuring data, binary relations, transitive closure, provision of resources.
{"title":"LEVERAGING SYNERGETIC INFORMATION RESOURCES FOR ANGULAR MOTION CONTROL OF UNMANNED SPACECRAFT","authors":"V. Kovtun, A. N. Pavlov, B. Sokolov, D. Pavlov, V. N. Vorotyagin","doi":"10.33950/SPACETECH-2308-7625-2020-4-127-141","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-127-141","url":null,"abstract":"A key condition for accomplishing a mission of an unmanned spacecraft consists in providing it with resources. Resources can be replenished through synergetic observations of processes in cases where measured data are partially or fully missing or lacking for some of the controlled objects by means of measuring parameters of the processes characterizing the operation of other controlled objects. As an example, the paper discusses provisioning of resources for the process of controlling the motion about the center of mass by means of synergetic observations in cases where no inertial instrument was available for measuring the angular rate vector in the system controlling the motion of the geostationary communications satellite Yamal-200. Specifically, the observation is based on the operation of transitive closure of the binary relation defined on the base set of processes in the onboard systems and ground assets for radio interactions with the onboard systems of the unmanned spacecraft.\u0000Key words: unmanned spacecraft, control process, measuring data, binary relations, transitive closure, provision of resources.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128776059","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 : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-56-64
V. A. Buzhinskiy
The paper discusses small oscillations of a panel in an incompressible medium. Air can be considered an incompressible medium during modal tests of solar array panels for spacecraft deployed on the ground in a lab environment. A panel is represented as a two-sided boundary surface. Conditions are determined for applicability of the potential motion of the medium. Calculation of the attached mass is reduced to the solution of the Neumann boundary value problem. To solve the boundary value problem, the method of boundary elements is used in the piecewise constant approximation variant, which provides a solution of the hypersingular boundary integral equation. Numerical solutions are obtained for the three fundamental modes of rectangular panels. The obtained numerical values are refined using non-linear Shanks transformation. Dependence of attached mass on panel elongation and the amount of the gap between its fragments is studied. For any in-plane oscillation mode of a panel fragment, the attached mass is determined using the principle of linear superposition. An estimate is given of the effect of the distance from the panel to the wall on the attached mass value. Key words: oscillations, incompressible medium, air, attached mass, rectangular panels, boundary elements method.
{"title":"On attached masses of panels oscillating in incompressible medium","authors":"V. A. Buzhinskiy","doi":"10.33950/SPACETECH-2308-7625-2020-4-56-64","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-56-64","url":null,"abstract":"The paper discusses small oscillations of a panel in an incompressible medium. Air can be considered an incompressible medium during modal tests of solar array panels for spacecraft deployed on the ground in a lab environment. A panel is represented as a two-sided boundary surface. Conditions are determined for applicability of the potential motion of the medium. Calculation of the attached mass is reduced to the solution of the Neumann boundary value problem. To solve the boundary value problem, the method of boundary elements is used in the piecewise constant approximation variant, which provides a solution of the hypersingular boundary integral equation. Numerical solutions are obtained for the three fundamental modes of rectangular panels. The obtained numerical values are refined using non-linear Shanks transformation. Dependence of attached mass on panel elongation and the amount of the gap between its fragments is studied. For any in-plane oscillation mode of a panel fragment, the attached mass is determined using the principle of linear superposition. An estimate is given of the effect of the distance from the panel to the wall on the attached mass value.\u0000Key words: oscillations, incompressible medium, air, attached mass, rectangular panels, boundary elements method.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131382754","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 : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-42-55
Aleksandr P. Danylkin, V. Voronkov, Oleg Yu. Kazantsev, Vyacheslav A. Ketov, Y. Koptev, Yu. A. Plastinin, I. L. Strulya, A. V. Tatarnikov
The paper presents basic results of exploratory design studies into a space system for real-time monitoring of the Earth surface based on small spacecraft* for Earth remote sensing, which provides acquisition in real time of highly detailed Earth surface images with resolution of 0.7–1.0 m, a swath of 20 km and 15m in-plane georeferencing accuracy from a ~300 km orbit with a mass of spacecraft ~200 kgf repeating with high frequency (at least every 1.0–1.5h). The said parameters are in line with the current state of the art and are quite feasible for our country’s industry. _________________________________________ * — for the purposes of this paper ‘small spacecraft’ is a 150-220 kg spacecraft. Key words: small spacecraft, space system, Earth remote sensing, satellite bus, payload module, electro-optical equipment, multipurpose ground facility, combined ground station, services of space monitoring of the Earth surface.
{"title":"Small spacecraft-based space system for real-time Earth surface monitoring","authors":"Aleksandr P. Danylkin, V. Voronkov, Oleg Yu. Kazantsev, Vyacheslav A. Ketov, Y. Koptev, Yu. A. Plastinin, I. L. Strulya, A. V. Tatarnikov","doi":"10.33950/SPACETECH-2308-7625-2020-4-42-55","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-42-55","url":null,"abstract":"The paper presents basic results of exploratory design studies into a space system for real-time monitoring of the Earth surface based on small spacecraft* for Earth remote sensing, which provides acquisition in real time of highly detailed Earth surface images with resolution of 0.7–1.0 m, a swath of 20 km and 15m in-plane georeferencing accuracy from a ~300 km orbit with a mass of spacecraft ~200 kgf repeating with high frequency (at least every 1.0–1.5h). The said parameters are in line with the current state of the art and are quite feasible for our country’s industry.\u0000_________________________________________\u0000* — for the purposes of this paper ‘small spacecraft’ is a 150-220 kg spacecraft.\u0000\u0000Key words: small spacecraft, space system, Earth remote sensing, satellite bus, payload module, electro-optical equipment, multipurpose ground facility, combined ground station, services of space monitoring of the Earth surface.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125808533","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 : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-119-126
S. Solovyev
The paper discusses objectives and structure of smart monitoring of spacecraft status in the course of mission control. It defines the place of the monitoring and the notion of analysis used in the context of solving mission control problems. It summarizes the current state of monitoring techniques used in the course of controlling the missions of modern spacecraft and orbital complexes. It provides data on the results of the use of computerized data analysis techniques for our country’s space assets that are currently in operation. It articulates major drawbacks in the monitoring process, which are getting more exacerbated with the current trends in space programs development. It proposes a remedy for the drawbacks by means of development and introduction of procedures that will make telemetry data analysis smarter. The paper introduces the notion of smart analysis and its key advantages in technical applications. It identifies the key prerequisites for expanding the computerization of the monitoring process involved in the spacecraft mission control. It outlines basic operational principles of a smart monitoring system taking into account its operational peculiarities. Key words: spacecraft, mission control, introduction of smart technologies, status analysis, monitoring system.
{"title":"OBJECTIVES AND STRUCTURE OF SMART MONITORING OF SPACECRAFT STATUS IN THE COURSE OF MISSION CONTROL","authors":"S. Solovyev","doi":"10.33950/SPACETECH-2308-7625-2020-4-119-126","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-119-126","url":null,"abstract":"The paper discusses objectives and structure of smart monitoring of spacecraft status in the course of mission control. It defines the place of the monitoring and the notion of analysis used in the context of solving mission control problems. It summarizes the current state of monitoring techniques used in the course of controlling the missions of modern spacecraft and orbital complexes. It provides data on the results of the use of computerized data analysis techniques for our country’s space assets that are currently in operation. It articulates major drawbacks in the monitoring process, which are getting more exacerbated with the current trends in space programs development. It proposes a remedy for the drawbacks by means of development and introduction of procedures that will make telemetry data analysis smarter. The paper introduces the notion of smart analysis and its key advantages in technical applications. It identifies the key prerequisites for expanding the computerization of the monitoring process involved in the spacecraft mission control. It outlines basic operational principles of a smart monitoring system taking into account its operational peculiarities.\u0000Key words: spacecraft, mission control, introduction of smart technologies, status analysis, monitoring system.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"785 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116413504","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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