Pub Date : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-28-36
L. Bobe, N. Salnikov
Analysis and calculation have been conducted of the process of low-pressure reverse osmosis in the membrane apparatus of the system for recycling hygiene water for the space station. The paper describes the physics of the reverse osmosis treatment and determines the motive force of the process, which is the difference of effective pressures (operating pressure minus osmotic pressure) in the solution near the surface of the membrane and in the purified water. It is demonstrated that the membrane scrubbing action is accompanied by diffusion outflow of the cleaning agent components away from the membrane. The mass transfer coefficient and the difference of concentrations (and, accordingly, the difference of osmotic pressures) in the boundary layer of the pressure channel can be determined using an extended analogy between mass transfer and heat transfer. A procedure has been proposed and proven in an experiment for calculating the throughput of a reverse osmosis apparatus purifying the hygiene water obtained through the use of a cleaning agent used in sanitation and housekeeping procedures on Earth. Key words: life support system, hygiene water, water processing, low-pressure reverse osmosis, space station.
{"title":"Analysis and calculation of the process of low-pressure reverse osmosis during recycling of hygienic water","authors":"L. Bobe, N. Salnikov","doi":"10.33950/SPACETECH-2308-7625-2019-2-28-36","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-28-36","url":null,"abstract":"Analysis and calculation have been conducted of the process of low-pressure reverse osmosis in the membrane apparatus of the system for recycling hygiene water for the space station. The paper describes the physics of the reverse osmosis treatment and determines the motive force of the process, which is the difference of effective pressures (operating pressure minus osmotic pressure) in the solution near the surface of the membrane and in the purified water. It is demonstrated that the membrane scrubbing action is accompanied by diffusion outflow of the cleaning agent components away from the membrane. The mass transfer coefficient and the difference of concentrations (and, accordingly, the difference of osmotic pressures) in the boundary layer of the pressure channel can be determined using an extended analogy between mass transfer and heat transfer. A procedure has been proposed and proven in an experiment for calculating the throughput of a reverse osmosis apparatus purifying the hygiene water obtained through the use of a cleaning agent used in sanitation and housekeeping procedures on Earth.\u0000 Key words: life support system, hygiene water, water processing, low-pressure reverse osmosis, space station.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133989587","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-14-27
V. Maevskiy, V. V. Aseev, A. S. Ivlev, N. A. Nizhelskiy, M. Sysoev, V. Sinyavskiy
The article presents possible options to solve problems characteristic of the lunar program using devices with elements of high-temperature superconductivity technology (HTSC). Both the general state of work on high-temperature superconductivity technologies and types of HTSC products and their main characteristics are considered preliminarily. According to foreign information materials, the possible options are described to use HTSC assemblies for solving tasks on the lunar surface. It is shown that conditions on the lunar surface are more attractive for operation of HTSC devices than on the surface of the Earth. Combining HTSC and lunar technologies is related to the purpose of reducing the mass and dimensions and increasing the service life of the equipment for operation on the Moon. The main attention in the article is paid to devices with bulk HTSC and, above all, taking into account the possible wide use on the lunar surface – to magnetic HTSC bearings, including for the kinetic energy storage, a telescope. The list of devices with HTSC assemblies that can be efficiently used for the optimal solution of many urgent tasks is given and their features are described. Key words: high-temperature superconductivity, bulk HTSC, magnetic HTSC bearing, lunar surface, kinetic energy storage, telescope.
{"title":"Some possible fields of utilization of high-temperature superconductivity in lunar exploration program","authors":"V. Maevskiy, V. V. Aseev, A. S. Ivlev, N. A. Nizhelskiy, M. Sysoev, V. Sinyavskiy","doi":"10.33950/SPACETECH-2308-7625-2019-2-14-27","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-14-27","url":null,"abstract":"The article presents possible options to solve problems characteristic of the lunar program using devices with elements of high-temperature superconductivity technology (HTSC). Both the general state of work on high-temperature superconductivity technologies and types of HTSC products and their main characteristics are considered preliminarily. According to foreign information materials, the possible options are described to use HTSC assemblies for solving tasks on the lunar surface.\u0000It is shown that conditions on the lunar surface are more attractive for operation of HTSC devices than on the surface of the Earth. \u0000Combining HTSC and lunar technologies is related to the purpose of reducing the mass and dimensions and increasing the service life of the equipment for operation on the Moon. The main attention in the article is paid to devices with bulk HTSC and, above all, taking into account the possible wide use on the lunar surface – to magnetic HTSC bearings, including for the kinetic energy storage, a telescope. The list of devices with HTSC assemblies that can be efficiently used for the optimal solution of many urgent tasks is given and their features are described.\u0000Key words: high-temperature superconductivity, bulk HTSC, magnetic HTSC bearing, lunar surface, kinetic energy storage, telescope.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115833522","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-37-54
Y. Berkovich, S. O. Smolyanina, A. Zheleznyakov, A. S. Guzenberg
It is planned to include greenhouses in the suite of regenerative life support systems for crews of manned long-duration space vehicles to improve their habitability. Space greenhouses will provide crew members with green vegetables containing digestible vitamins and dietary fibers, as well as psychophysiological support during long space missions. The paper presents an analytical review of designs of a number of greenhouses in our country and abroad, both existing and under construction that are capable of operating in spaceflight environment. It describes their key design and operational properties, analyses problems standing in the way of developing more productive space greenhouses. It explains the advantages of our country’s conveyor-type space greenhouse with cylindrical planting surface for continuous production of vitamin-rich greens and other vegetables onboard a manned spacecraft. It points out the need to construct our country’s ground prototype for a full-scale space greenhouse to develop the process for growing plants in orbital station, transportation vehicles, in lunar and Martian outposts. Key words: regenerative life support systems, habitat, space greenhouse, cylindrical planting surface.
{"title":"Prospects for using space greenhouses as a part of a suite of crew life support systems of a lunar orbital station, a lunar base and interplanetary transfer vehicles","authors":"Y. Berkovich, S. O. Smolyanina, A. Zheleznyakov, A. S. Guzenberg","doi":"10.33950/SPACETECH-2308-7625-2019-2-37-54","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-37-54","url":null,"abstract":"It is planned to include greenhouses in the suite of regenerative life support systems for crews of manned long-duration space vehicles to improve their habitability. Space greenhouses will provide crew members with green vegetables containing digestible vitamins and dietary fibers, as well as psychophysiological support during long space missions. The paper presents an analytical review of designs of a number of greenhouses in our country and abroad, both existing and under construction that are capable of operating in spaceflight environment. It describes their key design and operational properties, analyses problems standing in the way of developing more productive space greenhouses. \u0000 It explains the advantages of our country’s conveyor-type space greenhouse with cylindrical planting surface for continuous production of vitamin-rich greens and other vegetables onboard a manned spacecraft. It points out the need to construct our country’s ground prototype for a full-scale space greenhouse to develop the process for growing plants in orbital station, transportation vehicles, in lunar and Martian outposts.\u0000Key words: regenerative life support systems, habitat, space greenhouse, cylindrical planting surface.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114884645","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 : 2019-06-15DOI: 10.33950/SPACETECH-2308-7625-2019-2-107-114
V. Babishin, Dmitriy Yu. Dementyev, M. Mikhailov, Vladimir V. Nekrasov, D. Sobolev, K. A. Sosedko
The development of radiation-resistant microcontroller technology opened new possibilities for controlling the flywheel engine and, consequently, the whole spacecraft. The lack of import-independent flywheel engine having the advanced capabilities as compared with domestic and foreign analogs made it necessary to develop a new generation of flywheel engines with digital microcontroller-based control at JSC Corporation VNIIEM. Such a flywheel engine is being developed as a fast-acting actuator of the orientation and stabilization system of a high-dynamic spacecraft (the maximum control moment of the new flywheel engine is 1 N·m). Such features of creating digital microcontroller-based control of a new flywheel engine as organizing the flywheel engine rotor rate feedback, consideration of the basic control modes of the flywheel engine and options for reaching the required rotor rate of the flywheel engine, as well as self-diagnostics not only controlling but automatically updating the diagnosed parameters of the flywheel engine are given in this article. Key words: flywheel engine, digital control, microcontroller-based control, JSC Corporation VNIIEM.
{"title":"Features of digital control of flywheel engine, jsc corporation vniiem for high-dynamic spacecraft","authors":"V. Babishin, Dmitriy Yu. Dementyev, M. Mikhailov, Vladimir V. Nekrasov, D. Sobolev, K. A. Sosedko","doi":"10.33950/SPACETECH-2308-7625-2019-2-107-114","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-107-114","url":null,"abstract":"The development of radiation-resistant microcontroller technology opened new possibilities for controlling the flywheel engine and, consequently, the whole spacecraft. The lack of import-independent flywheel engine having the advanced capabilities as compared with domestic and foreign analogs made it necessary to develop a new generation of flywheel engines with digital microcontroller-based control at JSC Corporation VNIIEM. Such a flywheel engine is being developed as a fast-acting actuator of the orientation and stabilization system of a high-dynamic spacecraft (the maximum control moment of the new flywheel engine is 1 N·m).\u0000Such features of creating digital microcontroller-based control of a new flywheel engine as organizing the flywheel engine rotor rate feedback, consideration of the basic control modes of the flywheel engine and options for reaching the required rotor rate of the flywheel engine, as well as self-diagnostics not only controlling but automatically updating the diagnosed parameters of the flywheel engine are given in this article. \u0000Key words: flywheel engine, digital control, microcontroller-based control, JSC Corporation VNIIEM.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"153 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132524729","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 : 1900-01-01DOI: 10.33950/spacetech-2308-7625-2021-1-108-118
M. Y. Gunchenko
The paper provides results of estimated accuracy comparisons for applied satellite constellations (ASC) in Molniya-type high elliptical orbits based on a previously presented criterion for analysis of accuracy parameters of ASC that observe targets on the Earth surface and/or in the layer above the surface, which is not dependent on specific features of the onboard equipment, but rather on the structure and dynamics of the ASC. The paper provides an algorithm for numerical simulations of ASC. The paper discusses accuracy parameters for ASC in high elliptical orbits in various orbital configurations, as well as a combined option involving spacecraft in geostationary orbit. It defines key trajectory design parameters driving the ASC accuracy. The results can be used for selecting the initial ASC configuration in high elliptical orbits during preliminary design phase. Key words: observation satellite systems, high elliptical orbits, accuracy criterion, satellite constellation analysis.
{"title":"Сomparative study of the accuracy of Earth observation by satellite constellations in high elliptical orbits","authors":"M. Y. Gunchenko","doi":"10.33950/spacetech-2308-7625-2021-1-108-118","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2021-1-108-118","url":null,"abstract":"The paper provides results of estimated accuracy comparisons for applied satellite constellations (ASC) in Molniya-type high elliptical orbits based on a previously presented criterion for analysis of accuracy parameters of ASC that observe targets on the Earth surface and/or in the layer above the surface, which is not dependent on specific features of the onboard equipment, but rather on the structure and dynamics of the ASC. The paper provides an algorithm for numerical simulations of ASC. The paper discusses accuracy parameters for ASC in high elliptical orbits in various orbital configurations, as well as a combined option involving spacecraft in geostationary orbit. It defines key trajectory design parameters driving the ASC accuracy. The results can be used for selecting the initial ASC configuration in high elliptical orbits during preliminary design phase.\u0000Key words: observation satellite systems, high elliptical orbits, accuracy criterion, satellite constellation analysis.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128142447","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 : 1900-01-01DOI: 10.33950/spacetech-2308-7625-2021-1-78-87
N. Tupitsyn
The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author. It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines. Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.
{"title":"Feasibility analysis of liquid propellant settling in the tanks of a space propulsion system after flying in zero gravity using a separating turn maneuver of the orbital unit","authors":"N. Tupitsyn","doi":"10.33950/spacetech-2308-7625-2021-1-78-87","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2021-1-78-87","url":null,"abstract":"The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author.\u0000It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines.\u0000Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130973588","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 : 1900-01-01DOI: 10.33950/spacetech-2308-7625-2021-1-98-107
A. P. Elchin, A. Guzenberg, S. Romanov, A. Zheleznyakov, A. M. Ryabkin
The paper presents partial analytical solutions for equations describing variation in trace amounts of carbon dioxide in the atmosphere of habitable spaces within pressurized modules (PM) of a space station. The solutions may find practical application in calculations of concentrations for any contaminants, or for air flow through the purification system. It is shown that in a case where low-toxic contaminants are released into the PM atmosphere, it would be enough to cycle 3 volumes of the PM air through the purification system when the system operates without the breakthrough concentration (without the residual concentration of the contaminant at the outlet from the purification system), in order to achieve the 95% purification of the atmosphere. For highly toxic contaminants this value should be significantly increased depending on the maximum allowable concentration of the substance (47 volumes and more — up to 99.9% purification). The paper also considers variation in the concentration of the contaminant in the atmosphere during intermixing of atmospheres between PMs using intermodular ventilation. As a result, new analytical solutions were obtained for practical calculations which make it possible to determine gaseous contaminant concentration at any point in time and the time of the final equalization of the contaminant concentration in the space station atmosphere. It was determined that the time needed for complete mixing of gaseous contaminants through intermodular ventilation between two PMs does not depend on the initial concentrations of the contaminants (and only depends on the PM volumes and the intermodular ventilation flow rate). Key words: space station, pressurized module atmosphere, carbon dioxide, atmosphere purification, variation in concentration, air flow, atmosphere mixing.
{"title":"Results of studies of processes of clearing of gaseous contaminants and ventilating the atmosphere of habitable pressurized modules in a space station","authors":"A. P. Elchin, A. Guzenberg, S. Romanov, A. Zheleznyakov, A. M. Ryabkin","doi":"10.33950/spacetech-2308-7625-2021-1-98-107","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2021-1-98-107","url":null,"abstract":"The paper presents partial analytical solutions for equations describing variation in trace amounts of carbon dioxide in the atmosphere of habitable spaces within pressurized modules (PM) of a space station. The solutions may find practical application in calculations of concentrations for any contaminants, or for air flow through the purification system. It is shown that in a case where low-toxic contaminants are released into the PM atmosphere, it would be enough to cycle 3 volumes of the PM air through the purification system when the system operates without the breakthrough concentration (without the residual concentration of the contaminant at the outlet from the purification system), in order to achieve the 95% purification of the atmosphere. For highly toxic contaminants this value should be significantly increased depending on the maximum allowable concentration of the substance (47 volumes and more — up to 99.9% purification). \u0000The paper also considers variation in the concentration of the contaminant in the atmosphere during intermixing of atmospheres between PMs using intermodular ventilation. As a result, new analytical solutions were obtained for practical calculations which make it possible to determine gaseous contaminant concentration at any point in time and the time of the final equalization of the contaminant concentration in the space station atmosphere. It was determined that the time needed for complete mixing of gaseous contaminants through intermodular ventilation between two PMs does not depend on the initial concentrations of the contaminants (and only depends on the PM volumes and the intermodular ventilation flow rate).\u0000Key words: space station, pressurized module atmosphere, carbon dioxide, atmosphere purification, variation in concentration, air flow, atmosphere mixing.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132420037","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 : 1900-01-01DOI: 10.33950/spacetech-2308-7625-2021-1-88-97
Nikolay P. Sizyakov, I. A. Yuriev, A. G. Galeev
The paper provides a review of materials on the development of testing facilities in the Scientific Testing Center of the Rocket and Space Industry and the issues involved in raising the efficiency and safety of experimental development of advanced cryogenic propulsion systems for launch vehicles intended for exploration of the near and deep space. It shows that the most dangerous tests are those that are conducted on engines and propulsion systems that use oxygen, methane and hydrogen as propellant components. They may involve containment failure in the propellant system in off-nominal situations — emergency releases of propellant components, explosions and fires. It provides calculation results for overpressure in the shock-wave front depending on the mass of the released hydrogen and the factor of its contribution to the explosion. It formulates special and additional safety measures for engine and propulsion system tests in a test facility. Key words: test facility (test stand), propulsion system, safety, off-nominal situation, cryogenic propellant components.
{"title":"On the development of testing facilities for the scientific testing center of the rocket and space industry for developmental testing of advanced cryogenic propulsion systems","authors":"Nikolay P. Sizyakov, I. A. Yuriev, A. G. Galeev","doi":"10.33950/spacetech-2308-7625-2021-1-88-97","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2021-1-88-97","url":null,"abstract":"The paper provides a review of materials on the development of testing facilities in the Scientific Testing Center of the Rocket and Space Industry and the issues involved in raising the efficiency and safety of experimental development of advanced cryogenic propulsion systems for launch vehicles intended for exploration of the near and deep space.\u0000It shows that the most dangerous tests are those that are conducted on engines and propulsion systems that use oxygen, methane and hydrogen as propellant components. They may involve containment failure in the propellant system in off-nominal situations — emergency releases of propellant components, explosions and fires. It provides calculation results for overpressure in the shock-wave front depending on the mass of the released hydrogen and the factor of its contribution to the explosion. It formulates special and additional safety measures for engine and propulsion system tests in a test facility.\u0000Key words: test facility (test stand), propulsion system, safety, off-nominal situation, cryogenic propellant components.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"57 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114400460","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：