Pub Date : 2021-03-31DOI: 10.33950/SPACETECH-2308-7625-2020-4-65-77
F. Pelevin, A. Ponomarev
The paper discusses a new method for regenerative cooling of the chamber of liquid-propellant rocket engines using the concept of interchannel coolant flow through a porous metal mesh made by vacuum diffusion welding of woven metal netting. It provides a theoretical rationale for switching from unidimensional (longitudinally channeled) flow to two-dimensional (interchannel) inter-mesh flow coolant through a porous mesh. It provides experimental data for hydraulic resistance and heat exchange in porous metal meshes. Based on the experimental data, a generalized criterial equation was obtained for surface heat release in the paths with interchannel two-dimensional intermesh coolant flow through metal mesh. The paper examines the efficiency of heat exchange in the paths with interchannel coolant flow. Key words: regenerative cooling, interchannel flow; vacuum diffusion technology, metal mesh; hydraulic resistance; heat exchange, heat exchange efficiency.
{"title":"A regenerative cooling system for the chamber of a liquid-propellant rocket engine with interchannel coolant flow through a metal mesh","authors":"F. Pelevin, A. Ponomarev","doi":"10.33950/SPACETECH-2308-7625-2020-4-65-77","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-65-77","url":null,"abstract":"The paper discusses a new method for regenerative cooling of the chamber of liquid-propellant rocket engines using the concept of interchannel coolant flow through a porous metal mesh made by vacuum diffusion welding of woven metal netting. It provides a theoretical rationale for switching from unidimensional (longitudinally channeled) flow to two-dimensional (interchannel) inter-mesh flow coolant through a porous mesh. It provides experimental data for hydraulic resistance and heat exchange in porous metal meshes. Based on the experimental data, a generalized criterial equation was obtained for surface heat release in the paths with interchannel two-dimensional intermesh coolant flow through metal mesh. The paper examines the efficiency of heat exchange in the paths with interchannel coolant flow.\u0000Key words: regenerative cooling, interchannel flow; vacuum diffusion technology, metal mesh; hydraulic resistance; heat exchange, heat exchange efficiency.","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":"126883605","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 : 2021-03-15DOI: 10.33950/SPACETECH-2308-7625-2020-4-20-41
S. Klimov, V. Grushin, Kalman Balajthy, D. Bachvarov, S. Belyaev, J. Bergman, C. Ferencz, K. Georgieva, M. Gough, Alla B. Belikova, Lyudmila D. Belyakova, T. V. Grechko, V. Konoshenko, V. Korepanov, B. Kirov, O. Lapshinova, J. Lichtenberger, A. Marusenkov, M. Morawski, Nagygál János, R. Nedkov, D. Novikov, V. Rodin, H. Rothkaehl, G. Stanev, S. Szalai, P. Szegedi
The program and results of physical research in the international (5 countries) space experiment «The situation (1 stage)», conducted onboard the Russian segment of the International Space Station (ISS) in the period 27.02.2013 to 09.05.2015, is presented. The methods and scientific tasks of the experiment and the composition of the Plasma-wave complex based on the combined wave diagnostics method are described in detail, and designed to conduct geophysical studies through long-term monitoring measurements of the electromagnetic parameters of the ionosphere plasma and plasma-wave processes associated with the manifestation in the ionosphere of the solar-magnetosphere-ionosphere and ionosphere-atmosphere relationships, i. e., parameters of space weather. Studies in the near-surface zone of plasma-wave processes of interaction of an extra-large spacecraft, like ISS, with the ionosphere are necessary for both applied and fundamental geophysical studies. The electric and magnetic fields and currents measured at the surface of the ISS are determined by the parameters of the surrounding ionosphere plasma and the nature of the interaction of the materials on the surface with this medium. Key words: orbital space station, fundamental space research, ionosphere plasma, plasma-wave processes, electromagnetic fields and radiation, scientific instrument, space weather.
{"title":"Studying of space weather electromagnetic parameters of ionosphere in «Obstanovka 1-step» experiment on the Russian segment of the ISS","authors":"S. Klimov, V. Grushin, Kalman Balajthy, D. Bachvarov, S. Belyaev, J. Bergman, C. Ferencz, K. Georgieva, M. Gough, Alla B. Belikova, Lyudmila D. Belyakova, T. V. Grechko, V. Konoshenko, V. Korepanov, B. Kirov, O. Lapshinova, J. Lichtenberger, A. Marusenkov, M. Morawski, Nagygál János, R. Nedkov, D. Novikov, V. Rodin, H. Rothkaehl, G. Stanev, S. Szalai, P. Szegedi","doi":"10.33950/SPACETECH-2308-7625-2020-4-20-41","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2020-4-20-41","url":null,"abstract":"The program and results of physical research in the international (5 countries) space experiment «The situation (1 stage)», conducted onboard the Russian segment of the International Space Station (ISS) in the period 27.02.2013 to 09.05.2015, is presented. The methods and scientific tasks of the experiment and the composition of the Plasma-wave complex based on the combined wave diagnostics method are described in detail, and designed to conduct geophysical studies through long-term monitoring measurements of the electromagnetic parameters of the ionosphere plasma and plasma-wave processes associated with the manifestation in the ionosphere of the solar-magnetosphere-ionosphere and ionosphere-atmosphere relationships, i. e., parameters of space weather. Studies in the near-surface zone of plasma-wave processes of interaction of an extra-large spacecraft, like ISS, with the ionosphere are necessary for both applied and fundamental geophysical studies. The electric and magnetic fields and currents measured at the surface of the ISS are determined by the parameters of the surrounding ionosphere plasma and the nature of the interaction of the materials on the surface with this medium. \u0000Key words: orbital space station, fundamental space research, ionosphere plasma, plasma-wave processes, electromagnetic fields and radiation, scientific instrument, space weather.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"88 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115662373","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 : 2020-12-15DOI: 10.33950/spacetech-2308-7625-2020-4-5-20
A. Kirilin, R. Akhmetov, A. I. Baklanov, N. Stratilatov, V. Abrashkin, E. V. Kosmodemyansky, V. Salmin, I. Tkachenko, S. Safronov
The description of the unified platform of small spacecraft AIST-2 is presented. The platform is intended to accommodate various types of science equipment, Earth remote sensing equipment and onboard support systems. The description of the unified platform design, main onboard systems, ground control facilities, data acquisition and processing is given. The results of design studies, construction and operation of small spacecraft built on the basis of the AIST-2 unified platform are presented. The design, onboard composition, technical characteristics and results of operation of the first small spacecraft in the line – AIST-2D which it was launched on April 28, 2016 in the scope of the first launch campaign from the Vostochny Cosmodrome by the Soyuz-2.1a launch vehicle with the Volga ascent unit are described in detail. The results of design studies on the development of advanced small spacecraft based on the AIST-2 platform capable of functioning as part of the space monitoring system are described. Key words: small spacecraft, unified platform, design configuration, remote sensing of the Earth, stereoscopic image equipment, electro-rocket propulsion system.
{"title":"Main design characteristics of small scientific and applied-purpose spacecraft based on the Aist-2 unified platform","authors":"A. Kirilin, R. Akhmetov, A. I. Baklanov, N. Stratilatov, V. Abrashkin, E. V. Kosmodemyansky, V. Salmin, I. Tkachenko, S. Safronov","doi":"10.33950/spacetech-2308-7625-2020-4-5-20","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2020-4-5-20","url":null,"abstract":"The description of the unified platform of small spacecraft AIST-2 is presented. The platform is intended to accommodate various types of science equipment, Earth remote sensing equipment and onboard support systems. The description of the unified platform design, main onboard systems, ground control facilities, data acquisition and processing is given. The results of design studies, construction and operation of small spacecraft built on the basis of the AIST-2 unified platform are presented. The design, onboard composition, technical characteristics and results of operation of the first small spacecraft in the line – AIST-2D which it was launched on April 28, 2016 in the scope of the first launch campaign from the Vostochny Cosmodrome by the Soyuz-2.1a launch vehicle with the Volga ascent unit are described in detail. The results of design studies on the development of advanced small spacecraft based on the AIST-2 platform capable of functioning as part of the space monitoring system are described.\u0000Key words: small spacecraft, unified platform, design configuration, remote sensing of the Earth, stereoscopic image equipment, electro-rocket propulsion system.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-12-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127309349","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-48-56
M. A. Filina, Nadezhda Yu. Kostikova, V. Petrov, Gleb B. Buzik, Yuriy V. Zuev, A. V. Yusov, S. Kozlov, E. A. Ustinova
The paper discusses issues involved in fine adjustment of the linear and angular position of antenna system reflectors on a spacecraft (SC) during its assembly using an alignment-and-metrology facility that has been developed, which consists of a 6-DOF pointing device and a laser coordinate measurement tracker. Achieving the specified linear and angular positions of antenna system elements in the SC datum reference frame, reducing human effort and time needed to perform this processing operation is an important task when building a spacecraft. To address this problem, a procedure was developed and tried out during an actual SC assembly consisting in the joint use of the 6-DOF pointing device Hexapod PM-mkm-P and the high-precision laser tracker Leica AT 403 for measuring the coordinates. An algorithm was developed for hardware/software interfacing between elements of the alignment-and-metrology facility, which provides iterative linear and angular positioning of the antenna reflectors in a closed loop with a feedback. The paper discusses sources of errors and the way to minimize their effect on the operation of various types of pointing using continuous monitoring by means of an external measuring system. The developed alignment-and-metrology facility provided high-precision spatial positioning of antenna elements in the SC coordinate system, which made it possible to rule out any errors by operator/installation worker during alignment and significantly reduce the time needed to perform the said operation. Key words: spacecraft, antenna alignment, 6-DOF hexapod-type platform with parallel kinematics, Gough-Stewart platform, laser coordinate measuring system.
{"title":"Alignment-and-metrological facility for fine adjustment of antenna linear and angular position during spacecraft assembly","authors":"M. A. Filina, Nadezhda Yu. Kostikova, V. Petrov, Gleb B. Buzik, Yuriy V. Zuev, A. V. Yusov, S. Kozlov, E. A. Ustinova","doi":"10.33950/SPACETECH-2308-7625-2019-3-48-56","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-48-56","url":null,"abstract":"The paper discusses issues involved in fine adjustment of the linear and angular position of antenna system reflectors on a spacecraft (SC) during its assembly using an alignment-and-metrology facility that has been developed, which consists of a 6-DOF pointing device and a laser coordinate measurement tracker. Achieving the specified linear and angular positions of antenna system elements in the SC datum reference frame, reducing human effort and time needed to perform this processing operation is an important task when building a spacecraft. To address this problem, a procedure was developed and tried out during an actual SC assembly consisting in the joint use of the 6-DOF pointing device Hexapod PM-mkm-P and the high-precision laser tracker Leica AT 403 for measuring the coordinates. An algorithm was developed for hardware/software interfacing between elements of the alignment-and-metrology facility, which provides iterative linear and angular positioning of the antenna reflectors in a closed loop with a feedback. \u0000The paper discusses sources of errors and the way to minimize their effect on the operation of various types of pointing using continuous monitoring by means of an external measuring system. The developed alignment-and-metrology facility provided high-precision spatial positioning of antenna elements in the SC coordinate system, which made it possible to rule out any errors by operator/installation worker during alignment and significantly reduce the time needed to perform the said operation.\u0000Key words: spacecraft, antenna alignment, 6-DOF hexapod-type platform with parallel kinematics, Gough-Stewart platform, laser coordinate measuring system.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125695790","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-20-29
L. D’yachkov, M. Vasilyev, O. Petrov, S. Savin, I. Churilo
We discuss the possibility of using static magnetic traps as an alternative to electrostatic traps for forming and confining structures of charged dust particles in a gas discharge plasma in the context of our study of strongly interacting Coulomb systems. Some advantages of confining structures in magnetic traps over electrostatic ones are shown. Also we provide a review of the related researches carried out first in laboratory conditions, and then under microgravity conditions including the motivation of performing the experiments aboard the International Space Station (ISS). The preparations of a new space experiment «Coulomb-magnet» as well as the differences of a new equipment from previously used are described. We proposed the main tasks of the new experiment as a study of the dynamics and structure of active monodisperse and polydisperse macroparticles in an inhomogeneous magnetic field under microgravity conditions, including phase transitions and the evolution of such systems in the kinetic heating of dust particles by laser radiation. Key words: Coulomb structures, magnetic trap, antiprobotron, diamagnetic particles, dust particles, microgravity.
{"title":"Antiprobcotron magnetic trap for charged dust particles in space experiments","authors":"L. D’yachkov, M. Vasilyev, O. Petrov, S. Savin, I. Churilo","doi":"10.33950/SPACETECH-2308-7625-2019-3-20-29","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-20-29","url":null,"abstract":"We discuss the possibility of using static magnetic traps as an alternative to electrostatic traps for forming and confining structures of charged dust particles in a gas discharge plasma in the context of our study of strongly interacting Coulomb systems. Some advantages of confining structures in magnetic traps over electrostatic ones are shown. Also we provide a review of the related researches carried out first in laboratory conditions, and then under microgravity conditions including the motivation of performing the experiments aboard the International Space Station (ISS). The preparations of a new space experiment «Coulomb-magnet» as well as the differences of a new equipment from previously used are described. We proposed the main tasks of the new experiment as a study of the dynamics and structure of active monodisperse and polydisperse macroparticles in an inhomogeneous magnetic field under microgravity conditions, including phase transitions and the evolution of such systems in the kinetic heating of dust particles by laser radiation.\u0000Key words: Coulomb structures, magnetic trap, antiprobotron, diamagnetic particles, dust particles, microgravity.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122165305","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-30-38
A. Aksenov, A. A. Dyadkin, Valeria V. Zharkova, A. Pavlov, T. V. Simakova, Aleksandr Evgenyevich Shсhelyaev
The re-entry vehicle included into the manned spacecraft Federatsiya that is being developed by RSC Energia, nominally lands on specially prepared solid ground landing sites using a parachute-jet system. In off-nominal situations the re-entry vehicle is capable of performing a splashdown. In that case, in order to properly take into account the loads and do strength analysis, one needs to know the levels of hydrodynamic loads on the spacecraft body and its dynamic behavior in water, factoring in all the possible weather conditions at the landing site and all possible operational modes of parachute-jet system in off-nominal situations. This paper presents the results of numerical simulation of a splashdown on rough water of the re-entry vehicle included in the crew transportation spacecraft Federatsiya. It discusses both the cases where the propulsion system is firing and where it is not. It provides data on changes in kinematic properties of the re-entry vehicle, in forces and torques it is subjected to, as well as g-loads it experiences. The obtained data are required for further loading and strength analyses of the spacecraft structure. Key words: numerical simulation, splashdown, re-entry vehicle, aerodynamic properties, rough seas
{"title":"Simulating splashdown of a re-entry vehicle with operating propulsion system on rough water","authors":"A. Aksenov, A. A. Dyadkin, Valeria V. Zharkova, A. Pavlov, T. V. Simakova, Aleksandr Evgenyevich Shсhelyaev","doi":"10.33950/SPACETECH-2308-7625-2019-3-30-38","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-30-38","url":null,"abstract":"The re-entry vehicle included into the manned spacecraft Federatsiya that is being developed by RSC Energia, nominally lands on specially prepared solid ground landing sites using a parachute-jet system. In off-nominal situations the re-entry vehicle is capable of performing a splashdown. In that case, in order to properly take into account the loads and do strength analysis, one needs to know the levels of hydrodynamic loads on the spacecraft body and its dynamic behavior in water, factoring in all the possible weather conditions at the landing site and all possible operational modes of parachute-jet system in off-nominal situations.\u0000This paper presents the results of numerical simulation of a splashdown on rough water of the re-entry vehicle included in the crew transportation spacecraft Federatsiya. It discusses both the cases where the propulsion system is firing and where it is not. It provides data on changes in kinematic properties of the re-entry vehicle, in forces and torques it is subjected to, as well as g-loads it experiences. The obtained data are required for further loading and strength analyses of the spacecraft structure.\u0000Key words: numerical simulation, splashdown, re-entry vehicle, aerodynamic properties, rough seas","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"117 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126783682","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-5-19
Yevgeny A. Mikrin
This paper, which is, to a large extent, a review, presents results of an analysis of the current status and future prospects for the development of our country’s manned spaceflight from the standpoint of RSC Energia as the prime organization in Russia in this field of science and engineering. It addresses the issues involved in the ISS Russian Segment deployment completion, which is to be achieved by the addition of three new modules currently being developed at RSC Energia: the Multipurpose Laboratory Module in 2020; the Node Module in 2021; Science and Power Module in 2022, and the development of an improved version of cargo spacecraft Progress-MS. It describes quick ISS rendezvous profiles for crew and cargo transportation spacecraft. It discusses the issues involved in improving the efficiency of the ISS Russian Segment utilization, commercialization problems and plans to expand scientific applied research. The paper explores the desirability of establishing a Russian orbital station after the ISS program completion. As a strategic outlook for the development of our country’s manned space flight the paper formulates proposals on the national program of lunar research and exploration. It summarizes RSC Energia’s proposals on the development of a multifunctional system for crew search and rescue during launches of manned spacecraft from Vostochny launch site. It discusses the results and problems involved in laying the scientific, engineering and manufacturing groundwork for the development of advanced manned space systems, including introduction of digital technologies, development of new instrumentation, use of composite materials, additive and robotic technologies. Key words: Manned spaceflight, ISS Russian Segment, commercialization of scientific research, Russian orbital station, lunar research and exploration program, crew search and rescue system, problems of laying the scientific and engineering groundwork.
{"title":"Scientific and engineering problems involved in the implementation of the project «Manned space systems and complexes»","authors":"Yevgeny A. Mikrin","doi":"10.33950/SPACETECH-2308-7625-2019-3-5-19","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-5-19","url":null,"abstract":"This paper, which is, to a large extent, a review, presents results of an analysis of the current status and future prospects for the development of our country’s manned spaceflight from the standpoint of RSC Energia as the prime organization in Russia in this field of science and engineering. It addresses the issues involved in the ISS Russian Segment deployment completion, which is to be achieved by the addition of three new modules currently being developed at RSC Energia: the Multipurpose Laboratory Module in 2020; the Node Module in 2021; Science and Power Module in 2022, and the development of an improved version of cargo spacecraft Progress-MS. It describes quick ISS rendezvous profiles for crew and cargo transportation spacecraft. It discusses the issues involved in improving the efficiency of the ISS Russian Segment utilization, commercialization problems and plans to expand scientific applied research. The paper explores the desirability of establishing a Russian orbital station after the ISS program completion.\u0000As a strategic outlook for the development of our country’s manned space flight the paper formulates proposals on the national program of lunar research and exploration. It summarizes RSC Energia’s proposals on the development of a multifunctional system for crew search and rescue during launches of manned spacecraft from Vostochny launch site.\u0000It discusses the results and problems involved in laying the scientific, engineering and manufacturing groundwork for the development of advanced manned space systems, including introduction of digital technologies, development of new instrumentation, use of composite materials, additive and robotic technologies. \u0000Key words: Manned spaceflight, ISS Russian Segment, commercialization of scientific research, Russian orbital station, lunar research and exploration program, crew search and rescue system, problems of laying the scientific and engineering groundwork.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129592921","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-77-88
V. Gorshkov, Alexey S. Savelyev, A. S. Nevrov, A. V. Smirnova
The paper reviews advanced process for manufacturing high-precision optical components used in space-based electrooptic systems for scientific research and Earth remote sensing. It presents an integrated process for automatic shaping (TESAF) of aspheric surfaces, including off-axis surfaces, of optical elements for electrooptic systems. This paper discusses various methods for shaping optical parts with virtually any degree of asphericity and various values of the off-axis parameter (off-axis aspherics) achieving surface shape precision to within λ/60…λ/80 (λ = 0.6328 micron) by the standard deviation criteria. The paper also presents the newly developed off-axis collimators, designed to shape a reference wavefront within a broad spectral range from ultraviolet to infrared radiation. In particular, a mirror collimator with an adaptive off-axis mirror that is capable of changing the wavefront that is being formed in order to obtain the response function of the electrooptical system under study. Optical systems built using the TESAF process are already successfully used. Key words: surface shaping, aspheric surface, surface interferogram, standard deviation.
{"title":"A process for shaping high-precision optical components for ground- and space-based electrooptic systems","authors":"V. Gorshkov, Alexey S. Savelyev, A. S. Nevrov, A. V. Smirnova","doi":"10.33950/SPACETECH-2308-7625-2019-3-77-88","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-77-88","url":null,"abstract":"The paper reviews advanced process for manufacturing high-precision optical components used in space-based electrooptic systems for scientific research and Earth remote sensing. It presents an integrated process for automatic shaping (TESAF) of aspheric surfaces, including off-axis surfaces, of optical elements for electrooptic systems. This paper discusses various methods for shaping optical parts with virtually any degree of asphericity and various values of the off-axis parameter (off-axis aspherics) achieving surface shape precision to within λ/60…λ/80 (λ = 0.6328 micron) by the standard deviation criteria.\u0000The paper also presents the newly developed off-axis collimators, designed to shape a reference wavefront within a broad spectral range from ultraviolet to infrared radiation. In particular, a mirror collimator with an adaptive off-axis mirror that is capable of changing the wavefront that is being formed in order to obtain the response function of the electrooptical system under study. Optical systems built using the TESAF process are already successfully used.\u0000Key words: surface shaping, aspheric surface, surface interferogram, standard deviation.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"213 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114971454","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-39-47
Yaroslav V. Rasskazov
The new peripheral docking mechanism is intended for docking with the International Standard-compliant docking ports. The distinct feature of this docking mechanism is accumulation, rather than damping of the kinetic energy of the approaching spacecraft. Selected as the basis for the kinematic system of the docking mechanism was Gough-Stewart. Design implementation of each of its translational links is hereafter called a rod. It consists of a ball screw converter, a gearbox and an energy accumulator. The new energy accumulating device includes a spiral spring mechanism and a controllable overrunning clutch, which can be commanded to disable or enable spinning of the spring mechanism shaft. The spring mechanism implements a predetermined non-linear load-deformation curve through the use of a variable-width ribbon in its design. The controllable overrunning clutch consists of a ratchet mechanism, friction (safety) brake and a two-position electromagnetic actuator, which makes it possible to control the switching of the clutch modes with short pulses, ensuring low power consumption and the ability to implement the specified sequence. Key words: spacecraft, peripheral docking mechanism, accumulation of mechanical energy.
{"title":"Energy accumulator device for a new peripheral docking mechanism","authors":"Yaroslav V. Rasskazov","doi":"10.33950/SPACETECH-2308-7625-2019-3-39-47","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-39-47","url":null,"abstract":"The new peripheral docking mechanism is intended for docking with the International Standard-compliant docking ports. The distinct feature of this docking mechanism is accumulation, rather than damping of the kinetic energy of the approaching spacecraft. Selected as the basis for the kinematic system of the docking mechanism was Gough-Stewart. Design implementation of each of its translational links is hereafter called a rod. It consists of a ball screw converter, a gearbox and an energy accumulator. The new energy accumulating device includes a spiral spring mechanism and a controllable overrunning clutch, which can be commanded to disable or enable spinning of the spring mechanism shaft. The spring mechanism implements a predetermined non-linear load-deformation curve through the use of a variable-width ribbon in its design. The controllable overrunning clutch consists of a ratchet mechanism, friction (safety) brake and a two-position electromagnetic actuator, which makes it possible to control the switching of the clutch modes with short pulses, ensuring low power consumption and the ability to implement the specified sequence.\u0000Key words: spacecraft, peripheral docking mechanism, accumulation of mechanical energy.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116427236","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-57-65
A. V. Tolok, S. Bronnikov, Dmitry Pavlov, S. Kuzin, A. Razumovskiy, V. Romakin, M. Loktev, Alexander M. Plaksin
The paper discusses problem statement for and software implementation of a Graphic Package Adaptation System (GPAS) intended for reading and processing graphic design data, produced by the CAD system PTC Creo. The idea is to introduce into the process of building a 3-D model of a spacecraft for training facilities an additional operation of ‘automated adaptation of the graphic package’. The proposed process does not exclude manual refinement of the model, however, including additional automated components into the process makes it possible to significantly reduce human effort required to build a model for training facilities. The exchange of models between PTC Creo, GPAS and Autodesk 3ds Max is conducted at the level of the open format Virtual Reality Modeling Language (VRML). The paper describes GPAS architecture, provides views of work windows of the program, and methods of running its main functions. Key words: Digital design model, polygonal model, simplification, graphic design data.
{"title":"Developing 3D–models for training facilities of a space complex","authors":"A. V. Tolok, S. Bronnikov, Dmitry Pavlov, S. Kuzin, A. Razumovskiy, V. Romakin, M. Loktev, Alexander M. Plaksin","doi":"10.33950/SPACETECH-2308-7625-2019-3-57-65","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-57-65","url":null,"abstract":"The paper discusses problem statement for and software implementation of a Graphic Package Adaptation System (GPAS) intended for reading and processing graphic design data, produced by the CAD system PTC Creo. The idea is to introduce into the process of building a 3-D model of a spacecraft for training facilities an additional operation of ‘automated adaptation of the graphic package’. The proposed process does not exclude manual refinement of the model, however, including additional automated components into the process makes it possible to significantly reduce human effort required to build a model for training facilities. The exchange of models between PTC Creo, GPAS and Autodesk 3ds Max is conducted at the level of the open format Virtual Reality Modeling Language (VRML). The paper describes GPAS architecture, provides views of work windows of the program, and methods of running its main functions.\u0000Key words: Digital design model, polygonal model, simplification, graphic design data.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"106 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133852283","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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