Advances in Space Research最新文献

{"title":"An investigation into the development of equatorial plasma bubbles (EPBs) through satellite traces (STs) using ionosonde observations","authors":"B. Gayathri,&nbsp;S. Sripathi","doi":"10.1016/j.asr.2025.06.017","DOIUrl":"10.1016/j.asr.2025.06.017","url":null,"abstract":"<div><div>This study examines the role of Satellite Traces (STs) in ionograms as a precursory signature of Equatorial Plasma Bubbles (EPBs) and Equatorial Spread F (ESF) irregularities. Using digital ionosonde observations from Tirunelveli (8.7°N; 77.8°E; 1.7°N Dip Lat), an equatorial station, we analyzed the occurrence of STs and their association with EPB development during the descending phase of the solar cycle (2014–2020). STs appear as oblique echoes in ionograms, originating from the upwelling walls of Large Scale Wave Structures (LSWS). We examined the role of STs in ESF occurrence, considering solar flux, seasonal, and temporal variations. Our analysis shows that STs frequently occur between 19:00 and 20:00 IST across all solar activity levels and are strongly correlated with post-sunset EPBs. The average time delay between ST appearance and ESF onset is around 30 min, suggesting that STs provide an early indication of EPB development. Additionally, we examined the role of bottomside h’F variations in ESF occurrence across different seasons and solar activity conditions. STs are also linked to post-midnight EPBs, particularly during low solar activity, even when Pre-reversal enhancement (PRE) is weak. These results demonstrate that STs serve as a reliable precursory signature of EPB, improving our ability to anticipate ESF occurrence. The findings enhance our understanding of STs and ESF occurrence during post-sunset and post-midnight hours, contributing to better ionospheric monitoring.</div><div>*Corresponding author.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2339-2353"},"PeriodicalIF":2.8,"publicationDate":"2025-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670643","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Mission analysis for the first-ever Saturn Trojan 2019 UO14","authors":"Yuki Takao","doi":"10.1016/j.asr.2025.06.016","DOIUrl":"10.1016/j.asr.2025.06.016","url":null,"abstract":"<div><div>In mid-2024, asteroid 2019 UO₁₄ was identified as the first-ever Saturn Trojan through ground-based archival observations and numerical simulations. Exploring this Trojan object with spacecraft may provide definitive information to elucidate the formation processes of our solar system. However, due to 2019 UO₁₄’s significant orbital inclination relative to the ecliptic plane and its long orbital period of over 30 years, opportunities to visit this object may be limited to approximately every 15 years. This paper thoroughly investigates potential mission scenarios to the first Saturn Trojan, 2019 UO₁₄, to determine the necessary launch window and spacecraft specifications. Initially, assuming a ballistic flight using chemical engines, a meta-heuristic global trajectory optimization algorithm has been developed that incorporates (powered) gravity-assist maneuvers and deep-space maneuvers. Analysis of all potential flyby sequences becomes possible through parallelized iterative search space pruning and evolutionary algorithms. The result indicates that flyby exploration is feasible with a launch window around 2034 and a <span><math><mrow><mi>Δ</mi><mi>V</mi></mrow></math></span> ranging from 92 m/s to 1041 m/s within an 11-year mission duration, while a rendezvous can be achieved with a departure around 2035 and a <span><math><mrow><mi>Δ</mi><mi>V</mi></mrow></math></span> of 2–3 km/s. Specifically, the itinerary via Saturn requires a <span><math><mrow><mi>Δ</mi><mi>V</mi></mrow></math></span> of 2 km/s and a flight time of 24.6 years, while the route via Jupiter results in a <span><math><mrow><mi>Δ</mi><mi>V</mi></mrow></math></span> of 3 km/s and a flight time of 13.4 years. Given that the orbital motion of outer solar system objects is relatively slow, low-thrust propulsion, which gradually accelerates the spacecraft, proves to be effective. Consequently, low-thrust trajectories to 2019 UO₁₄ were examined. The results demonstrate that a rendezvous can be accomplished with nearly the same departure epoch, time of flight, and <span><math><mrow><mi>Δ</mi><mi>V</mi></mrow></math></span> as in the ballistic flight, suggesting that low-thrust propulsion is highly compatible with the rendezvous scenario, as it significantly reduces the propellant mass fraction.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2488-2506"},"PeriodicalIF":2.8,"publicationDate":"2025-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670957","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Enhanced PPP based on optimization of GNSS broadcast ionospheric model using robust and adaptive constraint","authors":"Xianggao Yan ,&nbsp;Yanjun Du","doi":"10.1016/j.asr.2025.06.015","DOIUrl":"10.1016/j.asr.2025.06.015","url":null,"abstract":"<div><div>Current uncombined (UC) precise point positioning (PPP) with ionospheric constraints mainly relies on Global Ionosphere Maps (GIM), facing two key issues: (1) irrational weighting of virtual ionospheric observations degrades PPP performance; (2) insufficient real-time capability. This study proposes a new method using the GNSS broadcast ionospheric model with robust adaptive constraints to improve UC PPP, preventing unreasonable weighting of virtual ionospheric observations and enhancing positioning performance. To validate the method, GNSS data from 27 global stations during ionospheric calm/disturbed periods are utilized. The UC PPP is conducted with three ionospheric models: Global Ionosphere Maps (GIM), BeiDou global broadcast ionospheric delay correction model (BDGIM), and GPS Klobuchar model (GKlob). For single-frequency UC PPP, the effects of stepwise relaxation constraints and robust adaptive stepwise relaxation constraints on positioning accuracy and convergence time are analyzed. Results indicate that traditional stepwise relaxation constraints prolong convergence and cause solution failures under active ionospheric conditions, whereas the robust adaptive constraint method alleviates performance degradation from irrational weighting. Global-scale analysis demonstrates significant convergence acceleration: UC-BDGIM reduces average convergence time by 5.84 min, and UC-GKlob by 2.31 min.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2221-2231"},"PeriodicalIF":2.8,"publicationDate":"2025-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670961","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Optimized YOLOv8 with multi-level attention for satellite image-based landslide detection","authors":"Naveen Chandra ,&nbsp;Himadri Vaidya ,&nbsp;Magaly Koch ,&nbsp;Rajeshwari Bhookya ,&nbsp;Saurabh Singh ,&nbsp;Sansar Raj Meena","doi":"10.1016/j.asr.2025.06.010","DOIUrl":"10.1016/j.asr.2025.06.010","url":null,"abstract":"<div><div>Detecting landslide events presents a significant challenge in remote sensing, especially as computer vision technologies continue to advance. Landslide detection from remotely sensed images has traditionally relied on manual or semi-automated processes. However, with the rapid development of computational resources, there has been a shift towards automatic methods leveraging deep learning algorithms. Moreover, attention models, inspired by the human visual system, have emerged substantially providing improved solutions for object detection-related problems especially, landslide mapping. Therefore, this research work introduces an enhanced YOLOv8 (nano (n), small (s), and medium (m)) network incorporating popular attention modules, specifically convolutional block attention module (CBAM), efficient channel attention (ECA), and shuffle attention (SA), for enhancing landslide detection accuracy using satellite images. The original YOLOv8 is improved by adding the attention layer discretely after the C2F module within the neck. The addition of an attention layer enables the model to concentrate on the most informative parts of the feature maps combining the capabilities of both channel and spatial attention mechanisms for detecting subtle landslide features. The experiments are conducted using the publicly available Bijie landslide detection database. Standard evaluation metrics, including precision, recall, F-score, and mean average precision (mAP), are used for quantitative analysis. Among the variants tested, YOLOv8n + ResCBAM demonstrates the most promising performance. This study underscores the model’s efficacy in facilitating inventory preparation and precise landslide mapping for disaster recovery and response efforts, thereby supporting early prediction models.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2072-2085"},"PeriodicalIF":2.8,"publicationDate":"2025-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670433","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Rapid identification of time-varying aerodynamic parameters for aeroassisted vehicle via asynchronous iterative filtering","authors":"Qian Pan,&nbsp;Hongwei Han,&nbsp;Dong Qiao","doi":"10.1016/j.asr.2025.06.012","DOIUrl":"10.1016/j.asr.2025.06.012","url":null,"abstract":"<div><div>Aeroassisted maneuver represents a promising low-energy and high-efficiency maneuvering mode for orbital operations. Nonetheless, this maneuver necessitates that the vehicle traverse through unstable atmospheric conditions within a short timeframe to achieve orbital energy modulation. Such conditions imply that precise and time-varying aerodynamic parameters are critical to the accuracy of the dynamic model, and consequently, the safety of the flight. This paper proposes a methodology for identifying time-varying aerodynamic parameters through asynchronous iterative filtering. The effectiveness of this approach is demonstrated under various initial states and aerodynamic parameters, validating both its speed and robustness. Initially, to swiftly and accurately ascertain the initial values of aerodynamic parameters and state quantities in situations where these parameters are unknown and the vehicle state has an initial error, a time-synchronized initial value determination strategy is designed for the flight’s beginning phase. Following this, an asynchronous iterative filter is developed by incorporating time delay characteristics from dynamic system theory, enabling rapid and accurate tracking of the time-varying aerodynamic parameters throughout the subsequent flight process. Finally, Monte Carlo simulation analyses are conducted across multiple typical aeroassisted maneuver scenarios. These simulations illustrate the identification effectiveness of the proposed method under various initial states and aerodynamic parameters, thereby confirming its speed and robustness.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2207-2220"},"PeriodicalIF":2.8,"publicationDate":"2025-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670960","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Spacecraft maneuver detection based on nonlinear uncertainty propagation along decussated orbital arc","authors":"Zhen Yang ,&nbsp;Hexiang Huang ,&nbsp;Jiasheng Li ,&nbsp;Yazhong Luo","doi":"10.1016/j.asr.2025.06.013","DOIUrl":"10.1016/j.asr.2025.06.013","url":null,"abstract":"<div><div>This paper presents a method for detecting on-orbit spacecraft maneuvers using nonlinear orbital uncertainty propagation. The combined Gaussian mixture model and unscented transform method are used to propagate the orbital uncertainty associated with state estimation errors. This method accounts for potential non-Gaussian effects of the mapping uncertainty through nonlinear orbital dynamics and is applicable to arbitrary dynamical models. Forward orbital uncertainty propagation is used to determine whether an orbital anomaly exists between two observed states, and backward uncertainty propagation is then used to confirm whether the latter observed state was produced by a maneuver between the two observations. The proposed method can detect whether an orbital anomaly has occurred between two sequential orbital states, and uses data association to identify whether the two observations are of the same space object separated by an orbital maneuver. Numerical results show that the proposed method can successfully solve the problem of orbit association after impulsive maneuvers.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2472-2487"},"PeriodicalIF":2.8,"publicationDate":"2025-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670956","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Unified approach to far-range space rendezvous","authors":"Pini Gurfil","doi":"10.1016/j.asr.2025.06.011","DOIUrl":"10.1016/j.asr.2025.06.011","url":null,"abstract":"<div><div>Far-range space rendezvous is a complex process, designed to achieve terminal conditions required for the subsequent close-range rendezvous phase. In far-range rendezvous, the relative dynamics between the chaser spacecraft and the target are nonlinear, thus challenging the simple orbit control methods used in close-range rendezvous. In this paper, a new nonlinear closed-loop low-thrust far-range rendezvous law applicable to both spacecraft rendezvous and minor celestial body rendezvous is developed by means of angular momentum and eccentricity vector matching, which steers the chaser into the target’s orbital plane. This matching is realized by a nonlinear Lyapunov-based feedback control, in which the chaser and target angular momentum and eccentricity vectors are expressed in target-fixed local-vertical local-horizontal coordinates. In order to reduce the resulting along-track offset, the targeted semimajor axis is appended with an along-track-dependent bias, such that the along-track relative distance and speed are ultimately nullified. It is proven that the newly-developed rendezvous law remains invariant under the gravitational acceleration exerted by a minor celestial body, and is, therefore, applicable to minor celestial body rendezvous. Simulation results for both low Earth orbit spacecraft rendezvous and minor celestial body rendezvous indicate that the proposed far-range rendezvous algorithm is effective, steering the chaser spacecraft to close proximity of the target, thus enabling to initiate the close-range rendezvous phase.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 3","pages":"Pages 1662-1673"},"PeriodicalIF":2.8,"publicationDate":"2025-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144579318","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A weighted mean temperature model by integrating FY-4B GIIRS and ERA5 reanalysis data","authors":"Xiwang Cui ,&nbsp;Xinzhi Wang ,&nbsp;Yi Zhou ,&nbsp;Fayuan Chen ,&nbsp;Jianhang Zhang ,&nbsp;Jie Li","doi":"10.1016/j.asr.2025.06.007","DOIUrl":"10.1016/j.asr.2025.06.007","url":null,"abstract":"<div><div>Weighted mean temperature (<em>T</em>_m) is a significant parameter of high-precision and high-resolution Global Navigation Satellite System Precipitable Water Vapor (GNSS PWV) inversion. We constructed an empirical <em>T</em>_m model (called the FY-4BTm) by integrating the Fengyun-4B (FY-4B) Geostationary Interferometric Infrared Sounder (GIIRS) and the ERA5 reanalysis data provided by European Centre for Medium Range Weather Forecasts (ECMWF). Like other studies, the FY-4BTm empirical model takes into account multiple factors such as the longitude, latitude, and elevation, and at high spatial resolutions of 0.5° × 0.5°. When compared to the 102 radiosonde data in 2022, the annual mean bias and root mean square error (RMSE) of the FY-4BTm model are 0.53 K and 4.92 K, respectively. The FY-4BTm model performs better than the legacy Bevis and GPT3 models with an improvement of 2.09 K and 1.78 K in T_m respectively, especially in the high-latitude regions of the western and northern parts of the study area (73°E ∼ 140°E, 3°N ∼ 55°N). Compared with the ERA5 reanalysis data in 2022, the FY-4BTm’s annual mean bias and RMSE are 0.43 K and 4.16 K, respectively. Its precision is generally the best among the three models, but with a slightly lower stability than that of the Bevis model. With the PWV obtained from GNSS station as the reference, the FY-4BTm model also demonstrates well performance in PWV inversion, with annual mean bias ranging from 0 to 0.2 mm. Therefore, the FY-4BTm model will benefit a lot for GNSS PWV inversion without requiring the users to obtain additional meteorological data.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2039-2052"},"PeriodicalIF":2.8,"publicationDate":"2025-06-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670475","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Spatiotemporal dynamics of refugees and displaced persons during the Russia-Ukraine conflict: a nighttime light remote sensing perspective","authors":"Bin Guo ,&nbsp;Shixin Zhang ,&nbsp;Tingting Xie ,&nbsp;Wencai Zhang ,&nbsp;Zheng Wang ,&nbsp;Dingming Zhang ,&nbsp;Puhao Chen ,&nbsp;Tengyue Guo","doi":"10.1016/j.asr.2025.06.009","DOIUrl":"10.1016/j.asr.2025.06.009","url":null,"abstract":"<div><div>The Russian-Ukrainian conflict, which commenced on 24 February 2022, has precipitated a significant substantial refugee and displaced person (R&amp;DP) crisis. This study presents a novel methodological framework for analyzing the spatiotemporal dynamics of R&amp;DP at a raster scale based on nighttime light (NTL) images and statistical data via data-driven models. We employed comprehensive trend analysis and spatial statistical methods to examine R&amp;DP distribution patterns and their quantitative relationships with NTL radiance values. Data-driven models were developed to quantify the relations between NTL pixel values and the numbers of R&amp;DP and map R&amp;DP distribution at a 500 m resolution. Spatial statistical methods were adopted to identify the spatiotemporal dynamics of R&amp;DP. This study yielded several key findings. The total daily DN values of NTL images in Ukraine decreased by approximately 81.2 % since the onset of the war and as of April 4, 2023. A significant negative correlation between NTL pixel values and the numbers of R&amp;DP with correlation coefficients of −0.93 and −0.74 was detected. The number of refugees in Kyiv, Kyiv Oblast, Cherkasy Oblast, Volyn Oblast, Kharkiv Oblast, Donetsk Oblast, Luhansk Oblast, and Zaporizhzhia Oblast, as well as the number of displaced persons in Vinnytsia Oblast and Cherkasy Oblast, has shown a continuously increasing trend with the progression of the war. Conversely, refugees in Poltava, Sumy, Kirovohrad, Rivne, Khmelnytskyi, and Chernivtsi Oblasts, as well as displaced persons in Poltava, Volyn, Lviv, Rivne, Khmelnytskyi, Ternopil, Ivano-Frankivsk, Transcarpathian, and Chernivtsi Oblasts, exhibited a decreasing trend. This study provides a reference to evaluate the impact of emergencies and can serve as a basis for decision-making in humanitarian assistance.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 4","pages":"Pages 2053-2071"},"PeriodicalIF":2.8,"publicationDate":"2025-06-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144670968","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Assessment of middle atmosphere climatology using lidar for aerospace applications","authors":"Nicolas Gilbert Tufel ,&nbsp;Philippe Keckhut ,&nbsp;Laurent Dumas ,&nbsp;Alexis Mariaccia ,&nbsp;Mustapha Meftah ,&nbsp;Yann Courcoux ,&nbsp;Marie Vicomte ,&nbsp;Alain Hauchecorne","doi":"10.1016/j.asr.2025.06.004","DOIUrl":"10.1016/j.asr.2025.06.004","url":null,"abstract":"<div><div>This study evaluates temperature and density variations in the upper stratosphere and in the mesosphere using ERA-5 and NRLMSISE-2.0 models, by comparing them with our forty-years long temperature lidar observations. NRLMSISE-2.0, while reliable in terms of seasonal trends, is less accurate daily: it shows high biases with the lidar at high altitudes (globally less than 4 K below 50 km, up to 14 K at 80 km). The European Climate and Weather Forecast reanalysis model ERA-5 shows a bias to the lidar of −5 K the upper stratosphere but shows a larger difference reaching +20 K in the mesosphere. Lidar observations can reveal non-Gaussian distributions because of extreme events, such as Mesospheric Inversion Layers (MILs), minor and Major Sudden Stratospheric Warmings (m- and M-SSWs) or Double Stratopauses (DSs). These events are atmospheric particularities which should not be mixed with steady-state profiles to compute a mean climatology if the aim is to create a reference. To address this issue, a new methodology was developed to remove those events, resulting in what we called ”Steady-State” climatology. Our method based on lidar observation in four sites (Observatory of Haute-Provence, Reunion Island, Table Mountain and Mauna Loa) allowed us to give statistical information about these extreme phenomena. Furthermore, our findings show that when m-SSWs and MILs occur, the density profile deviates strongly from the NRLMISE-2.0 density, which highlights the need for refined atmospheric models for aerospace applications. Corresponding density differences between NRLMSISE and lidar can reach −15% and +25% at most for MILs and m-SSWs, respectively.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"76 3","pages":"Pages 1871-1889"},"PeriodicalIF":2.8,"publicationDate":"2025-06-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144579438","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}