Advances in Space Research最新文献

{"title":"GNSS satellite yaw attitude laws and impact on satellite clock, phase OSB and PPP-AR","authors":"Lingyue Cheng ,&nbsp;Tao Geng ,&nbsp;Jingnan Liu ,&nbsp;Xin Xie ,&nbsp;Pu Zhao ,&nbsp;Wenjian Liu","doi":"10.1016/j.asr.2024.10.064","DOIUrl":"10.1016/j.asr.2024.10.064","url":null,"abstract":"<div><div>Satellite yaw attitudes have significant impact on Global Navigation Satellite System (GNSS) data processing in two ways: the satellite horizontal phase center offset (PCO) corrections and phase wind-up corrections. When the Sun elevation angle is small, GNSS satellites are unable to maintain the nominal attitude and take place the yaw maneuvers. Generally, different types of satellites adopt different yaw attitudes during the yaw maneuver periods. In this research, the yaw attitude laws of different types of GPS, Galileo and BDS-3 satellites are comprehensively investigated, and the impact of yaw attitudes on satellite clock, phase observable-specific signal bias (OSB) and precise point positioning with ambiguity resolution (PPP-AR) are deeply evaluated. The main results show that for GPS Block IIF satellites, the maximum differences between the nominal yaw angles and the modeled yaw angles can reach to 360°. With the nominal attitude, the estimated phase OSB changes approximately 1 cycle and a 10 cm bias is observed in the U component positioning solutions of kinematic PPP-AR. After applying the modeled attitude, these obvious errors disappear. In addition, for BDS-3 SECM satellites, the mismodeling of the nominal attitude and CSNO modeled attitude results in 4–6 cm jumps in the detrended satellite clock residuals, and a 40 cm bias is observed in the U component positioning solutions of BDS-3 kinematic PPP-AR. After applying the modified CSNO modeled attitude to BDS-3 SECM satellites, the stability of satellite clocks and the positioning accuracy of PPP-AR are significantly improved.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2535-2549"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143171690","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":"Enhancing GNSS tropospheric delay corrections through an innovative lapse rate grid and adiabatic modelling","authors":"Jian Mao ,&nbsp;Di Hu ,&nbsp;RuiGuang Li ,&nbsp;ChangChen Wu ,&nbsp;TieJun Cui","doi":"10.1016/j.asr.2024.11.039","DOIUrl":"10.1016/j.asr.2024.11.039","url":null,"abstract":"<div><div>Since measurements of meteorological parameters like air pressure, water vapor pressure, and temperature are typically not conducted at the receiving antenna’s height, accurate vertical adjustments are indispensable for the tropospheric delay calculation in GNSS applications. We developed an enhanced GPT3 model named as GPT3a, incorporating a new temperature lapse rate grid model and the adiabatic method. The capabilities of GPT3a in predicting atmospheric parameter profiles are assessed by comparison with radiosonde data, NCEP reanalysis data, and GNSS data. Compared with GPT3, IGPT, UNB3, and the constant model with a value of 6.5 K/km, the accuracy of the GPT3a is improved by 50 %, 26 %, 21 %, and 31 % respectively in predicting lapse rate. The RMSEs of GPT3a, GPT3 and IGPT, across temperature profiles (4.2 K, 10.7 K and 6.6 K, respectively), pressure profiles (5.7 hPa, 18.7 hPa and 6.8 hPa, respectively), and ZHD profiles (16.4 mm, 36.4 mm and 17.5 mm, respectively), demonstrate that GPT3a performs superiorly to the GPT3 and IGPT models. Moreover, in the GNSS-based water vapor retrieval, when there is a large height difference between GNSS sites and the model, the GPT3a obviously outperforms GPT3. In short, GPT3a can be used as an enhancement of GPT3 to support GNSS positioning, GNSS meteorology and atmospheric research, which extends the applicability of GPT3 beyond the Earth’s surface to airspace.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2696-2710"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143171700","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 non-Lyapunov approach to control design with application to spacecraft docking","authors":"Xun Liu,&nbsp;Hashem Ashrafiuon,&nbsp;Sergey G. Nersesov","doi":"10.1016/j.asr.2024.11.026","DOIUrl":"10.1016/j.asr.2024.11.026","url":null,"abstract":"<div><div>In this paper, we present a novel control design framework for nonlinear dynamical systems that is not based on traditional Lyapunov approach. Specifically, the Iterative Control Framework (ICF) is designed to guarantee the convergence of the closed-loop system state to zero <em>without</em> a priori verification of Lyapunov-like conditions. The approach is based on a numerical routine that reconfigures the control input vector at each iteration in such a way that when the control input is applied to the system, the system trajectory reaches closer to the desired state. This allows the control of real-world systems regardless of complexity in model nonlinearities or system dimensionality. Here we apply this framework to spacecraft control during the final stage of its rendezvous with another space vehicle, that is, docking. Since spacecrafts are controlled by impulsive thrusters with very short activation time, this application presents an ideal case study for ICF. We show that all states of the dynamical model are driven to the desired equilibrium and run Monte Carlo simulations to demonstrate the robustness of the approach.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2954-2969"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172001","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 strategy for addressing large-scale hinge issues in large two-dimensional planar phased array antennas","authors":"Li Pei ,&nbsp;Liu Xiang ,&nbsp;Cai Guoping ,&nbsp;Liu Fucheng ,&nbsp;Sun Jun ,&nbsp;Zhu Dongfang","doi":"10.1016/j.asr.2024.11.031","DOIUrl":"10.1016/j.asr.2024.11.031","url":null,"abstract":"<div><div>In large space structures, the numerous connecting hinges exhibit significant nonlinear characteristics that profoundly impact the structural dynamic properties. The accuracy of hinge parameters is crucial for ensuring the precision of structural dynamic models. This paper addresses the issue of large-scale hinge parameter optimization for a two-dimensional planar phased array antenna structure in space. Firstly, the structure of the antenna is introduced, and dynamic modeling is conducted using the finite element method. Then, a hinge parameter optimization method based on a clustering strategy is proposed, determining the optimal number of clusters and hinge parameters using a genetic algorithm. Subsequently, a piecewise approximation method is employed to handle the nonlinear vibration caused by hinge clearance. Finally, a genetic algorithm optimizes actuator positions, and a combination of LQR and Bang-Bang control algorithms is used for segmented linear vibration active control of the structure. Simulation results demonstrate that the proposed method effectively addresses large-scale hinge uncertainty and nonlinear vibration and control issues arising from hinge clearance.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2994-3009"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172017","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":"Orbit determination analysis of IGSO satellite onboard GPS/BDS pseudorange data corrected by different code hardware delays products","authors":"Zhenghao Zhang ,&nbsp;Yong Huang ,&nbsp;Peng Yang ,&nbsp;Yanling Chen ,&nbsp;Xiaolin Jia","doi":"10.1016/j.asr.2024.11.047","DOIUrl":"10.1016/j.asr.2024.11.047","url":null,"abstract":"<div><div>The navigation signal received by the Inclined Geo-Synchronous Orbit (IGSO) satellite is often blocked by the Earth, and the signal strength is weak due to the long propagation distance, which makes the carrier phase data processing complicated. Using pseudorange data is a convenient and efficient method for determining the orbit of IGSO satellites. Code hardware delays are non-negligible errors in pseudorange data processing. This study investigates the precise orbit determination (POD) result using only pseudorange data corrected by four types of Differential Code Bias (DCB) products and Observable-specific Signal Biases (OSB) products, with the LT4A satellite as a case study. The results show that the correction of code hardware delay can effectively improve the orbit quality. After correcting the code hardware delay, using only GPS pseudorange observations, using only BDS pseudorange observations, and using GPS + BDS combined pseudorange observations to determine the orbit, the pseudorange residuals RMS are about 1.82 m, 1.09 m, and 1.53 m, respectively. Compared with the uncorrected code hardware delays results, the residuals RMS is better by 21.8 %, 79.5 %, and 53.0 %, respectively. As the length of the POD arc increases from 24 h to 72 h, both the quality and stability of the orbit are observed to improve. For the 72 h arc, the orbit overlap RMS with the three data types is 3.4 m, 3.0 m, and 2.8 m, respectively, with the improvement of about 10.5 %, 77.6 %, and 59.4 %, respectively, compared with no code hardware delays correction. Compared with the precise reference orbit, the comparison RMS are 6.3 m, 4.8 m, and 4.4 m, increased by 24.0 %, 78.9 %, and 51.6 %, respectively. The results demonstrate that the comparison RMS of the IGSO satellite with only pseudorange data can be better than 5 m in position, and correcting the code hardware delays can improve orbit quality obviously, especially for BDS pseudorange data.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 3050-3062"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172019","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":"Deep learning classification of winter wheat from Sentinel optical-radar image time series in smallholder farming areas","authors":"Xiaofang Sun ,&nbsp;Meng Wang ,&nbsp;Junbang Wang ,&nbsp;Guicai Li ,&nbsp;Xuehui Hou","doi":"10.1016/j.asr.2024.11.038","DOIUrl":"10.1016/j.asr.2024.11.038","url":null,"abstract":"<div><div>As crop yield stagnation, climate change, and the rising demand for agricultural products pose increasing challenges, mapping crop systems is becoming more and more important. Winter wheat is one of the major cereal crops cultivated in China, ranking as the third largest crop in terms of production and harvested area. Accurately mapping winter wheat is necessary for implementing effective farm management practices. While many studies have successfully produced high spatiotemporal resolution land cover maps, relatively few map products of crop types are available in China. The growing archive of satellite image time series provides enormous opportunities to map crops more closely. This research presents a two-step method to map winter wheat based on Sentinel-1 and Sentinel-2 time-series data from Shandong Province using the deep learning approaches. The winter crops were firstly mapped using time-series optical vegetation indices employing the deep learning methods. Then winter wheat was extracted from the winter crops mask by coupling optical and synthetic aperture radar time-series images. The results indicated that the precision of mapping winter wheat using Temporal Convolution Neural Networks (TempCNN) achieved the highest precision in mapping winter wheat, with an overall accuracy of 93.7 %, a kappa coefficient of 0.907, and an F1-score of 0.989. This was followed sequentially by the Residual 1D convolutional neural networks (ResNet), the Multi-Layer Perceptron (MLP), and the Lightweight Temporal Self-Attention Encoder (L-TAE). The Temporal Attention Encoder (TAE) model demonstrated the lowest precision among the compared models. The results agree well with independent county-level official census winter wheat area data (<em>R²</em> = 0.936). The proposed framework can also be applied in other regions to generate maps of different crops, so future work can extend the proposed model to other agricultural regions, where an increased number of crop types and natural vegetation types can be included and tested.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2683-2695"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172099","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":"Modelling and prediction of atmospheric drag coefficients in LEO satellite orbit determination and prediction with Bi-LSTM approach","authors":"Xiang Chen ,&nbsp;Chengpan Tang ,&nbsp;Wujiao Dai ,&nbsp;Xiaogong Hu ,&nbsp;Liucheng Chen ,&nbsp;Zhongying Zhang ,&nbsp;Xinhui Zhu ,&nbsp;Mingzhe Li","doi":"10.1016/j.asr.2024.10.063","DOIUrl":"10.1016/j.asr.2024.10.063","url":null,"abstract":"<div><div>In the precise orbit determination (POD) of Low Earth Orbit (LEO) satellites with onboard Global Navigation Satellite System (GNSS) observations, atmospheric drag coefficients (Cd) are estimated piece-wise to absorb atmosphere density modeling errors, attitude modeling errors and windward area errors when the satellite physical metadata is not available. This study focuses on modeling and prediction of atmospheric drag coefficient in LEO satellite orbit determination and prediction. Orbit determination was conducted to determine atmospheric drag coefficients for eight LEO satellites with the orbital altitudes from 500 km to 1300 km. The Bidirectional Long Short-Term Memory (Bi-LSTM) neural network was used to model and predict the atmospheric drag coefficient estimations. The average Mean Absolute Percentage Error (MAPE) and average relative error between the predicted and estimated values of Cd for the eight satellites, were 0.09 and 0.11, respectively, indicating a satisfactory prediction performance of Cd. Prediction of the Cd is applied in orbit prediction and 30-minute short arc orbit determination (SOD). The results of the orbit prediction show that the modeling of Cd plays a key role in improving the accuracy of orbit prediction. The accuracy of the orbit prediction method based on the Cd prediction is better than that of the method without Cd prediction, and the average accuracy improves by 67.5 % and 73.7 % for the eight satellites in 2019 and 2023, respectively. The highest accuracy improvement rate is 94.5 % for GRACE-C satellite in 2019 and 86.6 % for Swarm-B satellite in 2023. Among them, the RMS of the average 3D error of the 3-day orbit prediction of the Swarm-B satellite is the lowest in both 2019 and 2023, at 2.11 m and 8.79 m, respectively. The results show that the SOD method with constrained Cd for eight satellites has different degrees of accuracy improvement in most arcs relative to the method without constrained Cd. The average orbital accuracy with constrained Cd improves by 14.8 % and 17.1 % for the eight satellites in 2019 and 2023, respectively, with the highest accuracy improvement of 24.7 % for GRACE-C satellite in 2019 and 24.2 % for GRACE-D satellite in 2023. The average orbit error of GRACE-C satellite is reduced from 9.23 cm to 5.95 cm, and the average orbit error of GRACE-D satellite is reduced from 13.45 cm to 8.22 cm.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 2874-2888"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172103","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":"On the identification of the spatiotemporal locations of solar wind structures during an intense geomagnetic storm","authors":"Victor U. Chukwuma ,&nbsp;Bolarinwa J. Adekoya ,&nbsp;Eugene O. Onori ,&nbsp;Oluwafunmilayo O. Ometan ,&nbsp;Aghogho Ogwala","doi":"10.1016/j.asr.2024.11.034","DOIUrl":"10.1016/j.asr.2024.11.034","url":null,"abstract":"<div><div>Available literature indicates that various studies do not adequately provide information on the temporal locations of solar wind structures, which leaves a gap that needs to be filled. In response, a study of the geomagnetic storm of Oct 13, 2016, is carried out to fill this gap by identifying the spatiotemporal locations of solar wind structures responsible for the geomagnetic storm to effectively elucidate ionospheric responses during a geomagnetic storm, as well as enable the determination by further studies of the global relative geo-effectiveness of these structures as it were. Primarily, the investigation aimed to confirm if the typical simplified structure of all CMEs consists of a forward shock followed by the sheath and the magnetic cloud. Now, this study has brought forth some distinct/previously unseen results: A typical simplified structure of a CME consists of a forward shock followed by the sheath and the magnetic cloud. Our findings revealed a sandwich structure of sheath-magnetic cloud-sheath following the forward shock with the following spatiotemporal arrangement for the solar wind structures: (a) Sheath I, observed from 2 Oct 13 to 3 Oct 14, spanning: (i) the initial phase: 2–7 UT, Oct 13 (ii) the main phase:7–23 UT, Oct 13 (iii) the early parts of the recovery phase: 0–3 UT, Oct 14 (b) The Magnetic Cloud, observed through 03–09 UT, Oct 14, during the recovery phase. (c) Sheath II, observed during the recovery phase from 9 to 23 Oct 14.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 3197-3209"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143171081","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":"Comparative case study of delayed ionospheric response to a superposed 27-day solar rotation signal","authors":"Hanna Dühnen ,&nbsp;Rajesh Vaishnav ,&nbsp;Christoph Jacobi ,&nbsp;Erik Schmölter ,&nbsp;Jens Berdermann","doi":"10.1016/j.asr.2024.12.004","DOIUrl":"10.1016/j.asr.2024.12.004","url":null,"abstract":"<div><div>Major ionization processes in the upper atmosphere are driven by the solar extreme ultraviolet (EUV) radiation causing corresponding responses in ionospheric observables. The response to the 27-day solar rotation period is of particular interest, as this variation occurs with a delay, which depends on the level of solar and geomagnetic activity as well as atmospheric processes. The 27-day signature is also frequently superimposed with long-term variations, which further impact the length of the delay. For a better understanding of these interactions, the present study investigates the delayed response of ionospheric total electron content (TEC) and the concentrations of major neutral and ionized species. Using high-resolution simulations from the Thermosphere-Ionosphere-Electrodynamics General Circulation Model (TIE-GCM) and the Coupled Thermosphere Ionosphere Plasmasphere Electrodynamics (CTIPe) model, two distinct 27-day solar rotation periods from the high solar activity year of 2014 are analyzed. This comparison allows us to examine the effects of an ideal 27-day solar activity cycle alongside one characterized by increasing solar activity, while also comparing model results with observed IGS data. Our detailed analysis, based on TIE-GCM simulations, presents the ionospheric response for various ionized and neutral species across different altitudes and latitudes. Notably, we find that the accumulation of ionized species, such as <span><math><mrow><msup><mrow><mi>O</mi></mrow><mrow><mo>+</mo></mrow></msup></mrow></math></span> and <span><math><mrow><msubsup><mrow><mi>O</mi></mrow><mrow><mn>2</mn></mrow><mrow><mo>+</mo></mrow></msubsup></mrow></math></span>, in the lower ionosphere, particularly at approximately 230 km, where ionized oxygen density peaks—is significantly influenced by the long-term increase in solar activity. However, the 27-day solar rotation period predominantly governs ionization processes at altitudes above 230 km in both, ideal and complex model runs. Thus, our results are in good agreement with previous studies and extend the understanding of the delayed ionospheric response to more complex cases.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 3115-3132"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143172014","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"地球科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Attitude synchronization of chaotic satellites with unknown dynamics using a neural network based fixed time sliding mode controller","authors":"Özhan Bingöl","doi":"10.1016/j.asr.2024.11.009","DOIUrl":"10.1016/j.asr.2024.11.009","url":null,"abstract":"<div><div>This study investigates the synchronization and anti-synchronization of both identical and non-identical chaotic satellite systems. A fixed-time sliding mode control framework, based on a radial basis function (RBF) neural network, has been developed to synchronize the chaotic dynamics of master–slave satellite configurations. The proposed control scheme operates under the assumption that the dynamics of the satellites are not entirely known. The proposed control method guarantees that system errors will converge to negligible levels within a fixed time. Furthermore, the controller exhibits robustness in the presence of parametric uncertainties and external disturbances. The stability of the controlled systems is rigorously validated through Lyapunov analysis, and the controller’s effectiveness is confirmed through extensive simulation studies. These simulations are conducted on both identical and non-identical satellite models, with performance comparisons made against recent findings reported in the literature.</div></div>","PeriodicalId":50850,"journal":{"name":"Advances in Space Research","volume":"75 3","pages":"Pages 3242-3267"},"PeriodicalIF":2.8,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143171230","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}