Space Science and Technology-Kosmicna Nauka i Tehnologia最新文献

{"title":"IONOSPHERIC TOTAL ELECTRON CONTENT VARIATIONS CAUSED BY THE TONGA VOLCANO EXPLOSION ON JANUARY 15, 2022","authors":"L. Chernogor","doi":"10.15407/knit2023.03.067","DOIUrl":"https://doi.org/10.15407/knit2023.03.067","url":null,"abstract":"The capability of volcanoes to generate powerful explosive eruptions influencing the state of the ionosphere became known back in the 1980th. The Hunga-Tonga-Hunga-Ha’apai (Tonga for short) volcano explosion on January 15, 2022, has shown a surge of renewed interest in investigating effects in the Earth — atmosphere — ionosphere — magnetosphere system since this volcano can be rightfully classified as unique. A number of papers have already dealt with the ionospheric effects generated by the Tonga volcano. The temporal variations in the total electron content (TEC) were used to determine the number of volcano explosions to be five. The second and third explosions were the strongest, with the second being the most intense. The response of the ionosphere to the Tonga volcano explosion has been studied on local and global scales by making use of the Global Positioning System satellite constellation and measurements onboard the Swarm satellite network. In the vicinity of the volcano explosion, disturbances in TEC attained 5—10 TECU. In addition to the local effect, traveling ionospheric disturbances were observed to propagate, which were due to the generation and propagation of atmospheric gravity waves with speeds of 180 m/s to 1,050 m/s. Of particular importance to global-scale perturbations is the Lamb wave, which propagated with a speed of 315 m/s. At nighttime, plasma depletions of the equatorial ionosphere were revealed over the tropical Pacific Ocean when the electron density at 400—500 km altitude showed a decrease by 2-3 orders of magnitude. The length of these formations in longitude exceeded ~10 Mm, and they were observed for more than 4—5 h. The scientific objective of this study is further analysis of aperiodic and quasi-periodic perturbations in the ionosphere, which were caused by the Tonga volcano explosion, in a wide range of distances from the source of disturbance (from ~0.1 Mm to 5 Mm). To reveal the ionospheric response to the Tonga volcano explosion, the records of signals from Global Positioning System satellites have been analyzed. The intercomparison of temporal variations in TEC observed on the reference days and on the day when the volcano explosion occurred has resulted in the determination of basic principles of the generation of ionospheric perturbations and the estimation of numerical magnitudes of the parameters of the perturbations. Four groups of disturbances have been detected, each of which arrived at different time delays with respect to the moment of the volcano explosion. It is important to note that the time delay increases with increasing distance from the volcano to the observational instruments. The first group of speeds included the disturbances traveling with a speed close to 1,000 m/s and having an N-shaped profile. This perturbation was generated by a blast wave whose speed depended on the excess pressure and a priori exceeded the speed of sound. In the second group, the speed varied in the 336 m/s to 50","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":" ","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47196346","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ESTIMATION OF THE POSSIBILITY OF USING ELECTRIC PROPULSION SYSTEMS FOR LARGE-SIZED ORBITAL DEBRIS POST-MISSION DISPOSAL","authors":"A. Golubek, M. Dron’, O. M. Petrenko","doi":"10.15407/knit2023.03.034","DOIUrl":"https://doi.org/10.15407/knit2023.03.034","url":null,"abstract":"The steady increase in the amount of large-sized orbital debris represents a substantial threat to satellite missions. Currently, many methods of cleaning near-Earth space with the use of various means based on various physical principles are considered. Out of them all, the active method using a rocket propulsion system is the most commonly implemented. Considering the high specific impulse, small size, and mass of electric propulsion systems, they are a particularly attractive choice as means of post-mission disposal. Despite their advantages, such systems have certain peculiarities that need to be considered in the process of designing and implementing modern post-mission disposal means. These peculiarities include the maximum time of a single firing of the electric propulsion system, the maximum time of the battery charging, and the time of operation of the control system. The purpose of this work is the determination the capabilities of the modern Hall thrusters ST-25 and ST-40 developed by Space Electric Thruster Systems in solving the problem of post-mission disposal of large-sized orbital debris from low-Earth orbits taking into account the limitations on the power supply system. To achieve this goal, methods of analysis, synthesis, comparison, and computer simulation were used. In the course of the carried-out research, the following problems were solved. A scheme for post-mission disposal of large-sized orbital debris from low-Earth orbit was developed with consideration of the use of an electric propulsion system. The dependence was determined of the minimum delta-v increment required for post-mission disposal of an object within 25 years on the initial altitude of the orbit and the ballistic coefficient of the orbital debris. The upper boundary of the combinations of masses of orbital debris, the altitude of the initial orbit, and the ballistic coefficient were determined, for which post-mission disposal from near-Earth orbits is possible with the use of electric propulsion systems. The obtained results can be used in solving problems of the development of modern means of active post-mission disposal of orbital debris with the use of Hall thrusters developed by Space Electric Thruster Systems","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117888","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"TECHNICAL AND ECONOMIC SUBSTANTIATION OF THE AIR LAUNCH AEROSPACE SYSTEM PARAMETERS","authors":"D. Kalynychenko, T. Mańko, V. Pavlenko, T. Pavlenko","doi":"10.15407/knit2023.02.003","DOIUrl":"https://doi.org/10.15407/knit2023.02.003","url":null,"abstract":"The substantiation of the technical and economic parameters of the air launch aerospace system, which consists of a reusable unmanned aerial vehicle and integrated launch vehicle, is given. A combination of a turbofan engine and a ramjet engine is used as the unmanned aerial vehicle propulsion system. The considered vehicle is capable of delivering a payload into low-Earth orbits without the use of a spaceport. We have developed the methodology of the technical and economic substantiation of the parameters of the air launch aerospace system. The results were obtained by searching for the minimum of the objective function, which established the relationship between the technical and economic parameters of the aerospace system. For the objective function solution, the design parameters of the integrated launch vehicle and unmanned aerial vehicle were determined, as well as the limitation of the total acceleration velocity of the aerospace system. The methods used allowed us to determine the velocity constraints provided by the operation of the turbofan engine, ramjet engine, and the three solid propellant motors of integrated launch vehicle stages, as well as maximum dynamic pressure and maximum permissible temperature on the unmanned aerial vehicle surface. We determined the scheme for estimating the cost of launching the spacecraft into Earth orbit by the air launch aerospace system. The result of the substantiation is the determination of the technical and economic parameters of the integrated launch vehicle, unmanned aerial vehicle, and the aerospace system as a whole. The influence of the maximum temperature on the surface of the unmanned aerial vehicle and the specific impulse of the ramjet engine on the parameters of the aerospace system was also evaluated. The substantiation is the first step towards the creation of the Ukrainian aerospace air launch system.","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117828","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"SPECIFIC ACOUSTIC-GRAVITY WAVE MODES IN ISOTHERMAL ATMOSPHERE","authors":"A. Fedorenko, Yu. O. Klymenko, O. Cheremnykh, Y. Kryuchkov, I. Zhuk","doi":"10.15407/knit2023.02.045","DOIUrl":"https://doi.org/10.15407/knit2023.02.045","url":null,"abstract":"In the paper, we show that the spectrum of acoustic-gravity waves in an isothermal atmosphere includes four specific evanescent modes. These modes are the solutions of the system of hydrodynamic equations for small atmospheric disturbances under the assumption that one of the quantities (horizontal or vertical components of particle velocity, density fluctuations, or temperature) is equal to zero. Three of the four specific modes (the Lamb wave, the Brunt-Väisälä oscillation, and the f-mode) are well known, but they were previously obtained as independent solutions. The recent discovery by the authors of the evanescent γ-mode made it possible to show that all four specified modes form a certain family of special modes of the isothermal atmosphere. On the spectral diagram of the frequency and the wave vector, there are four dispersion curves of these special modes in which one of the perturbed quantities is equal to zero. These curves belong to the evanescent region of the acoustic-gravity wave spectrum. They intersect each other at five points. It is shown that the specific modes cannot interact at the intersection points. The polarization ratios between two perturbed quantities have a different sign on either side of a particular curve if one of the quantities on this curve is zero. These properties can be used as indicators of the specific modes in experimental studies of the evanescent spectrum of AGWs. By using polarization relations, the possibility of observing these modes in the Earth’s atmosphere and on the Sun is also analyzed.","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":" ","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49596808","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ELUCIDATION OF CELLULAR MECHANISMS OF AUTOPHAGY INVOLVEMENT IN PLANT ADAPTATION TO MICROGRAVITY CONDITIONS","authors":"A. Yemets, S. Plokhovska, R. Shadrina, O. Kravets, Y. Blume","doi":"10.15407/knit2023.02.022","DOIUrl":"https://doi.org/10.15407/knit2023.02.022","url":null,"abstract":"It was shown that clinostating conditions induce autophagy without increasing of programmed cell death (PCD) index in the epidermal cells of the root apex of A. thaliana seedlings. After the phase of activation of autophagy, its regulatory weakening occurs, which probably indicates adaptive changes to the conditions of clinostating. The induction of autophagy correlates with an increase in the expression levels of atg8 genes, some of which (atg8e and atg8i) may be involved in the implementation of autophagy under the simulated microgravity conditions. The transcriptional activity of cytoskeleton genes involved in the implementation of stress-induced autophagy, in particular α- and β-tubulin genes, was analyzed. Joint expression of α- and β-tubulin genes and atg8 under the simulated microgravity conditions was revealed. These results illustrate the role of the cytoskeleton in the development of microgravity-induced autophagy and make it possible to identify genes specific to this type of stress. The induction of autophagy and PСD was studied under the action of gamma irradiation as a concomitant factor of space flights, as well as under the combined action of acute irradiation and clinostating. Gamma irradiation in doses equivalent to those in the spacecraft cabin (1 - 6 Gy) induced dose-dependent changes in the topology and cytogenetic state of the root apical meristem, as well as slightly inhibited of the early plant development. In the meristem, heterogeneity increased, PCD indexes, mainly proliferative death and autophagy, increased. With the combined action of gamma irradiation (2 Gy) and clinostating, the density of autophagosomes in the epidermal cell root apices of 6-day-old seedlings increased (24 hours after irradiation), and after 4 days it decreased, compared to the non-irradiated control.","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117928","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"FROM THE HISTORY OF SPACE RESEARCH IN UKRAINE. 2. ІNTERNATIONAL COOPERATION IN PEACEFUL SPACE RESEARCH AND EXPLORATION (1957—1987)","authors":"Y. Yatskiv","doi":"10.15407/knit2023.02.097","DOIUrl":"https://doi.org/10.15407/knit2023.02.097","url":null,"abstract":"The article covers a special period of time, from the epochal event of 1957, the launch of the first artificial Earth satellite in the USSR, to the last most successful space project «Vega», carried out under the «Intercosmos» program in 1986. The problems of international cooperation in space exploration and development are highlighted. Information about other space projects of this period and the memories of eyewitnesses of these events are given","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"40 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117761","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ATOMIC OXYGEN IN LOW EARTH ORBITS, A RETROSPECTIVE REVIEW STUDY","authors":"W. M. Mahmoud, D. Elfiky, S. Robaa, M. Elnawawy, S. M. Yousef","doi":"10.15407/knit2023.02.032","DOIUrl":"https://doi.org/10.15407/knit2023.02.032","url":null,"abstract":"The article presents a retrospective review of atomic oxygen (AO) research in low Earth orbit (LEO).The space environment of LEO is a barrier to all satellites passing through it. Several of its constituent parts pose a great danger to satellite materials and subsystems. Such orbits are convenient for remote sensing and experimental satellites. In order to maintain the operational level of spacecraft, it is necessary to carry out thorough studies of the LEO environment and its components. AO, which is a hyperactive state of oxygen, is considered one of the most dangerous components of the LEO environment. It can react with many materials and thereby change the physical, optical and mechanical properties that affect the functionality of the satellite. To maintain the satellite in its orbit with a certain margin of reliability, it is necessary to reduce the aggressive influence on it of the environmental components of LEO. Predicting the impact of AO on materials that will be used in space ensures their correct selection. The work provides some recommendations for the creation of AO facilities for testing materials exposed to the aggressive influence of the space environment.","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117551","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"PHYSICAL EFFECTS OF THE POWERFUL TONGA VOLCANO EXPLOSION IN THE EARTH – ATMOSPHERE – IONOSPHERE – MAGNETOSPHERE SYSTEM ON JANUARY 15, 2022","authors":"L. Chernogor","doi":"10.15407/knit2023.02.054","DOIUrl":"https://doi.org/10.15407/knit2023.02.054","url":null,"abstract":"The Tonga volcano explosion has already been considered in many papers, which investigate the effects of tsunamis, explosiveatmospheric waves, traveling ionospheric disturbances, the perturbations of the equatorial anomaly, rearrangement of the ionospheric currents and of the atmospheric wind pattern, disturbances in the geomagnetic field, etc. It is reliably established that the explosion of the Tonga volcano caused a number of processes on a global scale. However, the mo deling of these processes is absent in the literature. The volcano is able to launch a whole complex of physical processes in all geophysical fields of the Earth (lithosphere, tectonosphere, ocean) – atmosphere – ionosphere – magnetosphere (EAIM) system. Analysis of the entire set of processes in the system caused by a unique explosion and volcanic eruption is a pressing scientific issue. The scientific objective of this study is to perform a comprehensive analysis and modeling of the main physical processes within the EAIM system, which accompanied the powerful explosion of the Tonga volcano on January 15, 2022. The article attempts to model or estimate the magnitude of the main effects caused by the explosion and eruption of the Tonga volcano. A comprehensive analysis and modeling of the main physical processes in the EAIM system, which accompanied the powerful explosi on and eruption of the Tonga volcano on January 15, 2022, has been performed. The energetics of the volcano and the explosive atmospheric wave has been estimated. The thermal energy of the volcano attained ~ 3.9×1018 J, while the mean thermal power has been estimated to be 9.1×1013 W. The energy of the explosive atmospheric wave was about 16–17 Mt TNT. The volcanic flow with an initial pressure of tens of atmospheres was determined to reach a few kilometers height, while the volcanic plume attained the peak altitude of 50–58 k m and moved 15 Mm we stward. The main parameters of the plume have been estimated. The plume’s mean power was 7.5 TW, and its heat flux was 15 MW/m2. With such a flux, one should have expected the appearance of a fire tornado with an ~0.17 s–1 angular frequency or a 37 s tornado rotation period. An analytical relation has been derived for estimating the maximum altitude of the plume rise. The main contribution to the magnitude of this altitude makes the volumetric discharge rate. The volcano explosion was accompanied by the generation of seismic and explosive atmospheric waves, tsunamis, Lamb waves, atmospheric gravity waves, infrasound, and sound, which propagated on a global scale. It is important to note that the powerful explosiveatmospheric wave could launch a secondary seismic wave and a secondary tsunami, which was one of the manifestations of subsystem couplings in the EAIM system. The propagation of powerful waves was accompanied by non-linear distortions of the wave profiles and non-linear attenuation as a result of the self-action of the waves. The electric processes in the tro","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117638","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"PRESENTATION OF THE GRAVITY FIELD OF CELESTIAL BODIES USING THE POTENTIALS OF FLAT ELLIPSOIDAL DISCS","authors":"M. Fys, A. Brydun, A. Sohor, V..A. Lozynskyy","doi":"10.15407/knit2023.02.078","DOIUrl":"https://doi.org/10.15407/knit2023.02.078","url":null,"abstract":"One of the possible ways for representing the external gravitational field of the planet by the potentials of flat discs, based on the classical potential theory, is proposed. At the same time, the potentials of a single- and double-layer are used for the description with the placement of the integration regions in the equatorial plane. The coefficients of the series expansion of these functions are linear combinations of the Stokes constants of the gravitational field and are uniquely expressed in terms of them. Series terms are single- or double-layer potentials. This makes it possible to calculate these terms using the results of the ellipsoid potential theory. The convergence of such a series, in contrast to the traditional one for spherical functions, is much wider and practically covers the effect of the external potential excluding the region of integration, including in the superficial parts of the surface. Since there is no problem with the convergence of the obtained expansions, we can interpret the obtained results more fully. The construction of flat density distributions for the potentials of a single and double layer is an additional tool in the study of the internal structure of the celestial body, as it is essentially a projection of the volume density of the planet’s interior onto the equatorial plane. Therefore, the extrema of these functions combine the features of the three-dimensional distribution function of the planet’s interior","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117701","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"ANALYSIS OF PHOTOMETRY OF THE SICH-2 SATELLITE ON A MULTI-YEAR OBSERVATION INTERVALS","authors":"V. Epishev, І.I. Motrunich, V. Perig, I. Neubauer, P. Guranich, A.I. Susla, M. Koshkin","doi":"10.15407/knit2023.02.086","DOIUrl":"https://doi.org/10.15407/knit2023.02.086","url":null,"abstract":"On August 17, 2011, a Dnipro vehicle launched the Sich-2 satellite into Earth’s orbit from the Yasny launch base. Ukrainian optical observation stations immediately began recording the satellite’s photometric light curves. In mid-2012, it was established that the Sich-2 spacecraft had a certain period of self-rotation and may have failed. This was confirmed later by official sources. Based on long-term observations of the Sich-2 artificial satellite of the Earth from Uzhgorod and Odesa, its behavior in orbit from the moment of launch until 2022 was investigated. The paper reveals the possibilities of the photometric method in combination with positional data from the research on the dynamics of the rotation of space vehicles with three degrees of freedom and complex design features of surfaces. In the article, the authors determined that the axis of self-rotation of the Sich-2 spacecraft coincides with its vertical axis, which precesses around the direction “the center of the satellite — the center of the Earth”. It was found that a pair of opposite PSBs are placed perpendicular to each other. The calculated value of the orbital period of the satellite was Porb = 99.5 min. and the average value of the precession period Ppr ~ 90.5 sec. The change in the period of selfrotation of the Sich-2 spacecraft was analyzed, which has changed at an interval of 9 years after destabilization in the range of Po = 11.95…3.63…5.06 sec. It was also established that the precession period during the same time varied within Рpr = 71.0…234.0 …226.0 sec. The angle of the precession of the axis of rotation relative to the direction from the center of the satellite to the center of the Earth is within 38°…28°.","PeriodicalId":42936,"journal":{"name":"Space Science and Technology-Kosmicna Nauka i Tehnologia","volume":"1 1","pages":""},"PeriodicalIF":0.4,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67117715","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}