Pub Date : 2024-06-04DOI: 10.1134/s0010952524600306
M. M. Mikhailov, S. A. Artishchev, A. N. Lapin, S. A. Yuryev, V. A. Goronchko, N. S. Trufanova, O. A. Mikhailova, D. S. Fedosov
Abstract
The results of studies of changes in the diffuse reflection spectra and integral solar radiation absorption coefficient as of a thermal control coating (TCC) of the Optical Solar Reflectors (OSR) class for spacecraft (SCs) under electron irradiation are presented. A dielectric ceramic paste (DCP) consisting of a filler, crushed polycor (Al2O3) and a solvent with a thickener (terpineol with ethyl cellulose), was applied by a 3D printer onto a substrate. Then, heating at 150°C and annealing at 850°C were carried out; a “white” coating was obtained with a high reflection coefficient and a low absorption coefficient, meeting the requirements and standards of the OSR class TCC. The radiation resistance of the resulting DCP-based coating is comparable to the resistance of a highly stable coating based on ZnO pigment with liquid lithium glass and is much higher than the resistance of a plasma-sprayed coating—MgAl2O4 spinel.
{"title":"Radiation Resistance of a Spacecraft Coating Obtained by 3D Printing","authors":"M. M. Mikhailov, S. A. Artishchev, A. N. Lapin, S. A. Yuryev, V. A. Goronchko, N. S. Trufanova, O. A. Mikhailova, D. S. Fedosov","doi":"10.1134/s0010952524600306","DOIUrl":"https://doi.org/10.1134/s0010952524600306","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The results of studies of changes in the diffuse reflection spectra and integral solar radiation absorption coefficient <i>a</i><sub><i>s</i></sub> of a thermal control coating (TCC) of the Optical Solar Reflectors (OSR) class for spacecraft (SCs) under electron irradiation are presented. A dielectric ceramic paste (DCP) consisting of a filler, crushed polycor (Al<sub>2</sub>O<sub>3</sub>) and a solvent with a thickener (terpineol with ethyl cellulose), was applied by a 3D printer onto a substrate. Then, heating at 150°C and annealing at 850°C were carried out; a “white” coating was obtained with a high reflection coefficient and a low absorption coefficient, meeting the requirements and standards of the OSR class TCC. The radiation resistance of the resulting DCP-based coating is comparable to the resistance of a highly stable coating based on ZnO pigment with liquid lithium glass and is much higher than the resistance of a plasma-sprayed coating—MgAl<sub>2</sub>O<sub>4</sub> spinel.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"25 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256256","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s0010952524600227
P. I. Shustov, A. A. Petrukovich, A. V. Artemyev
Abstract
Modeling the dynamics of energetic electron flows in the Earth’s inner magnetosphere is an important problem in the study of “space weather,” due to the role that energetic electrons play in spacecraft equipment failures. This paper examines the possibility of constructing an empirical model of electron flows in a medium-altitude circular orbit of GLONASS satellites. Measurements from the Radiation Belt Storm Probes satellite mission for 2012–2019 were used as the main source of flux data. Near-equatorial Radiation Belt Storm Probes measurements are projected onto the orbital altitudes of GLONASS satellites using an empirical magnetic field model. The main feature of the presented model of energetic electron fluxes is that, instead of providing just the average flux, this model reconstructs the probability distribution function of flux amplitudes depending on the electron energy and geomagnetic conditions.
{"title":"A Model of High-Energy Electron Flows in GLONASS Orbits","authors":"P. I. Shustov, A. A. Petrukovich, A. V. Artemyev","doi":"10.1134/s0010952524600227","DOIUrl":"https://doi.org/10.1134/s0010952524600227","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>Modeling the dynamics of energetic electron flows in the Earth’s inner magnetosphere is an important problem in the study of “space weather,” due to the role that energetic electrons play in spacecraft equipment failures. This paper examines the possibility of constructing an empirical model of electron flows in a medium-altitude circular orbit of GLONASS satellites. Measurements from the <i>Radiation Belt Storm Probes</i> satellite mission for 2012–2019 were used as the main source of flux data. Near-equatorial <i>Radiation Belt Storm Probes</i> measurements are projected onto the orbital altitudes of GLONASS satellites using an empirical magnetic field model. The main feature of the presented model of energetic electron fluxes is that, instead of providing just the average flux, this model reconstructs the probability distribution function of flux amplitudes depending on the electron energy and geomagnetic conditions.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"66 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256287","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s001095252460029x
E. K. Kolesnikov, S. V. Chernov
Abstract
A mathematical model has been developed describing the motion in near–Earth space (NES) and aerodynamic heating upon entry into the atmosphere of spherical microparticles of carbon (graphite) with radii from 0.5 to 3 μm, modeling spores of terrestrial bacteria, as well as spores of hypothetical bacteria of extraterrestrial origin. The model is based on a joint numerical solution of the equations of motion in the NES of the specified model microbiological object (MBO) and the heat balance equation describing the change in the internal energy of the MBO. The calculated data obtained show that the maximum temperatures of aerodynamic heating of spores of terrestrial bacteria separating from the surfaces of large low-orbit objects of artificial origin are significantly lower than the maximum temperature of survival of spores of terrestrial bacteria during pulsed heating. In addition, the results of numerical experiments give grounds for the assumption that the spores of hypothetical extraterrestrial bacteria with a size of no more than 1 μm are able to withstand aerodynamic heating when entering the Earth’s atmosphere at speeds greater than both the second and third cosmic speeds.
{"title":"On the Temperatures of Aerodynamic Heating of Spherical Microparticles Modeling Microbiological Objects Entering the Earth’s Atmosphere at Cosmic Velocities","authors":"E. K. Kolesnikov, S. V. Chernov","doi":"10.1134/s001095252460029x","DOIUrl":"https://doi.org/10.1134/s001095252460029x","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>A mathematical model has been developed describing the motion in near–Earth space (NES) and aerodynamic heating upon entry into the atmosphere of spherical microparticles of carbon (graphite) with radii from 0.5 to 3 μm, modeling spores of terrestrial bacteria, as well as spores of hypothetical bacteria of extraterrestrial origin. The model is based on a joint numerical solution of the equations of motion in the NES of the specified model microbiological object (MBO) and the heat balance equation describing the change in the internal energy of the MBO. The calculated data obtained show that the maximum temperatures of aerodynamic heating of spores of terrestrial bacteria separating from the surfaces of large low-orbit objects of artificial origin are significantly lower than the maximum temperature of survival of spores of terrestrial bacteria during pulsed heating. In addition, the results of numerical experiments give grounds for the assumption that the spores of hypothetical extraterrestrial bacteria with a size of no more than 1 μm are able to withstand aerodynamic heating when entering the Earth’s atmosphere at speeds greater than both the second and third cosmic speeds.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"26 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256983","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s0010952524600239
Yu. M. Zabolotnov, Changqing Wang, Zheng Min
Abstract
The article deals with the control of the process of rapprochement of a tether system with a passive space object (cargo, space debris, etc.) in an almost circular near-Earth orbit. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. The position of the dummy point is chosen based on the fact that, after the deployment of the tether system, the capture device appears in the vicinity of the cargo immediately or after some small portion of passive movement in orbit. The control of the process of approaching the spacecraft with a fictitious point in the spatial case is constructed using the Bellman dynamic programming principle using a linearized system. Continuous control is used with the help of jet engines with finite thrust. The components of the reactive forces for which the control is being constructed are directed along the transversal and binormal in the orbital coordinate system. It is assumed that the unavoidable guidance errors can be corrected by changing the length of the tether or in some other way. A numerical example of modeling the processes under consideration using nonlinear equations of motion is given illustrating the proposed control scheme.
{"title":"Control of the Process of Rapprochement of a Tether System with a Passive Space Object in a Near-Circular Orbit","authors":"Yu. M. Zabolotnov, Changqing Wang, Zheng Min","doi":"10.1134/s0010952524600239","DOIUrl":"https://doi.org/10.1134/s0010952524600239","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The article deals with the control of the process of rapprochement of a tether system with a passive space object (cargo, space debris, etc.) in an almost circular near-Earth orbit. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. The position of the dummy point is chosen based on the fact that, after the deployment of the tether system, the capture device appears in the vicinity of the cargo immediately or after some small portion of passive movement in orbit. The control of the process of approaching the spacecraft with a fictitious point in the spatial case is constructed using the Bellman dynamic programming principle using a linearized system. Continuous control is used with the help of jet engines with finite thrust. The components of the reactive forces for which the control is being constructed are directed along the transversal and binormal in the orbital coordinate system. It is assumed that the unavoidable guidance errors can be corrected by changing the length of the tether or in some other way. A numerical example of modeling the processes under consideration using nonlinear equations of motion is given illustrating the proposed control scheme.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"70 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256367","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s0010952524600288
K. R. Korneev, S. P. Trofimov
Abstract
The regularization of spacecraft motion equations by the Kustaanheimo–Stiefel transformation for coordinates and Sundman’s transformation for time is considered in the problem of low-thrust optimal transfer. From Pontryagin’s maximum principle, the thrust vector optimal control is derived under the limited power condition. The Earth–Mars transfer problem is solved in regular variables. The comparison of calculated trajectories with the ones obtained by the parameter continuation method is performed, and the stability properties of the two-point boundary value problem in the Cartesian and regular variables are studied.
{"title":"Low-Thrust Trajectory Optimization in Kustaanheimo–Stiefel Variables","authors":"K. R. Korneev, S. P. Trofimov","doi":"10.1134/s0010952524600288","DOIUrl":"https://doi.org/10.1134/s0010952524600288","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The regularization of spacecraft motion equations by the Kustaanheimo–Stiefel transformation for coordinates and Sundman’s transformation for time is considered in the problem of low-thrust optimal transfer. From Pontryagin’s maximum principle, the thrust vector optimal control is derived under the limited power condition. The Earth–Mars transfer problem is solved in regular variables. The comparison of calculated trajectories with the ones obtained by the parameter continuation method is performed, and the stability properties of the two-point boundary value problem in the Cartesian and regular variables are studied.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"93 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256466","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s0010952524600252
P. S. Krasilnikov, A. V. Dobroslavskiy
Abstract
The asymptotic behavior of the secular perturbation function expanded in a power series in μ, the ratio of the semimajor axes of the massless point (asteroid) and Jupiter, is studied in the restricted spatial circular three-body problem. It is assumed that (mu < 1) (internal case). A new derivation of the expansion of a secular perturbation function into a power series with coefficients expressed through Gauss and Clausen functions is described based on Parseval’s formula. For different values of μ at fixed values of the Lidov-Kozai constant, the radius of convergence of the reduced series, the areas of convergence and divergence are described in the plane of osculating elements e, ω. It is shown that power series is asymptotic in the sense of Poincaré in divergence regions, and that truncating the series after a 70 number of terms provides an high value approximation to a secular perturbation function. It is shown that the asymptotic properties of the series deteriorate on the nonanalyticity curves of secular perturbation function and completely disappear in a small neighborhood of (mu = 1). The asymptotic nature of the series allows, using ordinary methods of perturbation theory, to study the evolution of Keplerian orbital elements for all values of (mu ) from the interval [0, 1), excluding the case (mu approx 1).
{"title":"On the Asymptotic Behavior of the Secular Perturbation Function in the Circular Restricted Three-Body Problem","authors":"P. S. Krasilnikov, A. V. Dobroslavskiy","doi":"10.1134/s0010952524600252","DOIUrl":"https://doi.org/10.1134/s0010952524600252","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The asymptotic behavior of the secular perturbation function expanded in a power series in μ, the ratio of the semimajor axes of the massless point (asteroid) and Jupiter, is studied in the restricted spatial circular three-body problem. It is assumed that <span>(mu < 1)</span> (internal case). A new derivation of the expansion of a secular perturbation function into a power series with coefficients expressed through Gauss and Clausen functions is described based on Parseval’s formula. For different values of μ at fixed values of the Lidov-Kozai constant, the radius of convergence of the reduced series, the areas of convergence and divergence are described in the plane of osculating elements <i>e</i>, ω. It is shown that power series is asymptotic in the sense of Poincaré in divergence regions, and that truncating the series after a 70 number of terms provides an high value approximation to a secular perturbation function. It is shown that the asymptotic properties of the series deteriorate on the nonanalyticity curves of secular perturbation function and completely disappear in a small neighborhood of <span>(mu = 1)</span>. The asymptotic nature of the series allows, using ordinary methods of perturbation theory, to study the evolution of Keplerian orbital elements for all values of <span>(mu )</span> from the interval [0, 1), excluding the case <span>(mu approx 1)</span>.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"2 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256550","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-06-04DOI: 10.1134/s0010952524600264
P. S. Krasilnikov, A. E. Baikov
Abstract
The translational–rotational motions of a symmetrical dumbbell are considered in a circular restricted three-body problem where two primaries of equal mass move in circular orbits about common barycenter. A new type of motion is described for the dumbbell whereby its barycenter moves along the normal to the plane of rotation of the two primaries, whilst the dumbbell itself rotates continuously around the normal, forming a constant angle of π/2 with it (the invariant manifold “gravitational propeller”). It is shown that this manifold includes several two-dimensional invariant submanifolds. The dynamics of a dumbbell on these submanifolds is described. Relative equilibria were found on a “gravitational propeller” when the dumbbell mass center rests at the barycenter of the system, while the dumbbell is oriented parallel to the axis connecting the primaries or perpendicular to it. The stability of these equilibria is investigated. Small spatial nonlinear oscillations on a “gravitational propeller” manifold in the vicinity of a stable relative equilibrium were studied for the dumbbell of infinitesimal length. It is shown that these oscillations have the nature of a nonlinear parametric resonance, which sets a “slow” amplitude modulation of “fast” harmonic oscillations along the angle of rotation of the dumbbell.
{"title":"On Dumbbell Motions in the Generalized Circular Sitnikov Problem","authors":"P. S. Krasilnikov, A. E. Baikov","doi":"10.1134/s0010952524600264","DOIUrl":"https://doi.org/10.1134/s0010952524600264","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The translational–rotational motions of a symmetrical dumbbell are considered in a circular restricted three-body problem where two primaries of equal mass move in circular orbits about common barycenter. A new type of motion is described for the dumbbell whereby its barycenter moves along the normal to the plane of rotation of the two primaries, whilst the dumbbell itself rotates continuously around the normal, forming a constant angle of π/2 with it (the invariant manifold “gravitational propeller”). It is shown that this manifold includes several two-dimensional invariant submanifolds. The dynamics of a dumbbell on these submanifolds is described. Relative equilibria were found on a “gravitational propeller” when the dumbbell mass center rests at the barycenter of the system, while the dumbbell is oriented parallel to the axis connecting the primaries or perpendicular to it. The stability of these equilibria is investigated. Small spatial nonlinear oscillations on a “gravitational propeller” manifold in the vicinity of a stable relative equilibrium were studied for the dumbbell of infinitesimal length. It is shown that these oscillations have the nature of a nonlinear parametric resonance, which sets a “slow” amplitude modulation of “fast” harmonic oscillations along the angle of rotation of the dumbbell.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"310 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141256251","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-04-15DOI: 10.1134/s0010952523600282
N. A. Vlasova, G. A. Bazilevskaya, E. A. Ginzburg, E. I. Daibog, V. V. Kalegaev, K. B. Kaportseva, Yu. I. Logachev, I. N. Myagkova
Abstract
The results of studying the fluxes of solar protons with energies greater than 5 MeV in near-Earth space on March 13–23, 2023, are presented. The features of the period under study are no visible solar flare with which the beginning of the event could be associated and an untypical time profile of proton fluxes, as well as a long duration of the existence of solar proton fluxes in near-Earth space. An attempt was made to explain the sources of the observed different variations in particle fluxes and to understand what happened on the Sun and in the near-Earth space. The source of solar protons on March 13, 2023, was an explosive process on the back side of the Sun from the Earth, registered as a coronal mass ejection of very high power. The reason for the long and complex time profile of solar protons was the contribution of particle acceleration processes on the Sun and in the interplanetary medium, as well as the modulation of particle fluxes by the structures of the interplanetary magnetic field. A possible scenario has been proposed to explain the existence of increased fluxes of solar particles on March 15–23, 2023: the formation of a heliospheric structure, this being a closed trap region formed by two interplanetary coronal mass ejections and regions of interaction of high-speed and slow solar wind streams. The study uses experimental data obtained from the Solar Orbiter spacecraft and from spacecraft located near the L1 point of the Earth–Sun system (ACE and DSCOVR) and in geostationary orbit (GOES-16).
{"title":"Solar Energetic Proton Fluxes in Near-Earth Space on March 13–23, 2023","authors":"N. A. Vlasova, G. A. Bazilevskaya, E. A. Ginzburg, E. I. Daibog, V. V. Kalegaev, K. B. Kaportseva, Yu. I. Logachev, I. N. Myagkova","doi":"10.1134/s0010952523600282","DOIUrl":"https://doi.org/10.1134/s0010952523600282","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The results of studying the fluxes of solar protons with energies greater than 5 MeV in near-Earth space on March 13–23, 2023, are presented. The features of the period under study are no visible solar flare with which the beginning of the event could be associated and an untypical time profile of proton fluxes, as well as a long duration of the existence of solar proton fluxes in near-Earth space. An attempt was made to explain the sources of the observed different variations in particle fluxes and to understand what happened on the Sun and in the near-Earth space. The source of solar protons on March 13, 2023, was an explosive process on the back side of the Sun from the Earth, registered as a coronal mass ejection of very high power. The reason for the long and complex time profile of solar protons was the contribution of particle acceleration processes on the Sun and in the interplanetary medium, as well as the modulation of particle fluxes by the structures of the interplanetary magnetic field. A possible scenario has been proposed to explain the existence of increased fluxes of solar particles on March 15–23, 2023: the formation of a heliospheric structure, this being a closed trap region formed by two interplanetary coronal mass ejections and regions of interaction of high-speed and slow solar wind streams. The study uses experimental data obtained from the <i>Solar Orbiter</i> spacecraft and from spacecraft located near the <i>L</i>1 point of the Earth–Sun system (<i>ACE</i> and <i>DSCOVR</i>) and in geostationary orbit (<i>GOES-16</i>).</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"26 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140613144","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-04-15DOI: 10.1134/s0010952523600348
O. A. Sheiner, V. M. Fridman
Abstract
Based on an analysis of data for February–March 2023, the report considers the results of studies of the relationship between the occurrence of sporadic microwave radiation preceding the phenomena of coronal mass ejections and these phenomena. The aim is to develop methods for short-term prediction of coronal mass ejections from radio data.
{"title":"CME Radio Precursors Recorded in February–March 2023","authors":"O. A. Sheiner, V. M. Fridman","doi":"10.1134/s0010952523600348","DOIUrl":"https://doi.org/10.1134/s0010952523600348","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>Based on an analysis of data for February–March 2023, the report considers the results of studies of the relationship between the occurrence of sporadic microwave radiation preceding the phenomena of coronal mass ejections and these phenomena. The aim is to develop methods for short-term prediction of coronal mass ejections from radio data.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"109 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140613449","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-04-15DOI: 10.1134/s0010952523600294
F. I. Vybornov, O. A. Sheiner
Abstract
As a result of the analysis of data from vertical and oblique sounding of the ionosphere in February–March 2023 using the new ionospheric index, it was found that solar coronal mass ejections (CMEs) of the loop type lead to a long-term decrease in the critical frequencies F-layer of the ionosphere, while other types of CMEs may not lead to significant changes in the state ionosphere. The possible role of high-speed streams of solar wind and energetic protons in the occurrence of ionospheric disturbances is noted. Distance–frequency characteristics of the Cyprus–Nizhny Novgorod route during geomagnetic disturbances are given, which indicate both a strong deformation of the F-layer of the ionosphere and the appearance of z-shaped wave disturbances propagating to a region of lower altitudes.
摘要 利用新的电离层指数对 2023 年 2 月至 3 月电离层垂直和倾斜探测数据进行分 析后发现，环型太阳日冕物质抛射导致电离层临界频率 F 层长期下降，而其他类 型的日冕物质抛射可能不会导致状态电离层发生重大变化。注意到太阳风和高能质子高速流在发生电离层扰动中可能发挥的作用。给出了塞浦路斯-下诺夫哥罗德航线在地磁扰动期间的距离-频率特性，这表明电离层 F 层发生了强烈变形，并出现了向低空区域传播的 Z 形波扰动。
{"title":"Earth’s Ionospheric Response to Solar Activity Phenomena in February–March 2023","authors":"F. I. Vybornov, O. A. Sheiner","doi":"10.1134/s0010952523600294","DOIUrl":"https://doi.org/10.1134/s0010952523600294","url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>As a result of the analysis of data from vertical and oblique sounding of the ionosphere in February–March 2023 using the new ionospheric index, it was found that solar coronal mass ejections (CMEs) of the loop type lead to a long-term decrease in the critical frequencies <i>F</i>-layer of the ionosphere, while other types of CMEs may not lead to significant changes in the state ionosphere. The possible role of high-speed streams of solar wind and energetic protons in the occurrence of ionospheric disturbances is noted. Distance–frequency characteristics of the Cyprus–Nizhny Novgorod route during geomagnetic disturbances are given, which indicate both a strong deformation of the <i>F</i>-layer of the ionosphere and the appearance of <i>z</i>-shaped wave disturbances propagating to a region of lower altitudes.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":"33 1","pages":""},"PeriodicalIF":0.6,"publicationDate":"2024-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140613215","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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