Journal of Space Safety Engineering最新文献

{"title":"Failure-oriented-accelerated-testing (FOAT) of spacecraft electronics at the design stage: Perspective, role, significance, attributes, challenges","authors":"E. Suhir","doi":"10.1016/j.jsse.2025.09.005","DOIUrl":"10.1016/j.jsse.2025.09.005","url":null,"abstract":"<div><div>An highly focused and highly cost effective failure-oriented-accelerated-testing (FOAT) suggested about a decade ago as an experimental basis for the novel probabilistic design for reliability (PDfR) concept is supposed to be carried out, when necessary, at the design stage of a spacecraft electronic or a photonic product, in addition to the FOAT at the initial, product development, stage (such as, e.g., shear-off or temperature cycling tests), and the final, manufacturing, burn-in testing (BIT) stage. Such an effort might be needed, when high operational reliability, like the one required for aerospace, military, medical or long-haul communication applications, is a must, when effective and trustworthy highly-accelerated-life testing (HALT) procedures have not been developed yet, nor acceptable “best practices” have been agreed upon for the product or the technology of importance. A need for that takes place particularly when a new product, new technology or a new design are considered and high and predictable operational reliability is a must. Burn-in-testing (BIT) that is routinely conducted at the manufacturing stage of almost any IC product is always of a FOAT type: it is aimed at eliminating the infant mortality portion (IMP) of the bathtub curve (BTC) by trying to get rid of the low reliability products (\"freaks\") prior to shipping the “healthy” ones, i.e., those that survived BIT, to the customer(s). When FOAT at the design stage and BIT at the manufacturing stage are considered and conducted, a suitable and physically meaningful constitutive Eq., such as the multi-parametric Boltzmann-Arrhenius-Zhurkov (BAZ) model, could be employed to predict, from the FOAT data, the probability of failure and the corresponding useful lifetime of the critical product in the field, and, from the BIT data, as has been recently demonstrated, - the adequate level and duration of the applied stressors, as well as the (relatively low, of course) activation energies of the \"freaks\". Both types of FOAT are addressed in our write-up using analytical (\"mathematical\") predictive modeling, and the general concepts are illustrated by numerical examples. It is concluded that predictive modeling should always be conducted prior to actual testing and that analytical modeling should always complement computer simulations. These two major modeling tools are based on different assumptions, use different calculation techniques, and if their computed data agrees, then there is a good reason to believe that the obtained results are sufficiently accurate and trustworthy. Future work should be focused on the experimental verification and implementation of the obtained findings and recommendations and should include also an assessment of the probability of the most likely consequences of the possible field failures. The agreed upon never-zero probability of such failures cannot be high, of course, but should not be lower than necessary either: it should be adequate fo","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 106-121"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553625","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":"Ionospheric Scintillation characteristics over high-latitude Svalbard archipelago, Norway using multi-constellation GNSS observations","authors":"Kutubuddin Ansari ,&nbsp;Janusz Walo ,&nbsp;Kinga Wezka ,&nbsp;Afsheen Ameer ,&nbsp;Sampad Kumar Panda","doi":"10.1016/j.jsse.2026.02.002","DOIUrl":"10.1016/j.jsse.2026.02.002","url":null,"abstract":"<div><div>The study investigates ionospheric scintillations over the high-latitude Svalbard archipelago, Norway region using multi-constellation GNSS (GPS, GLONASS, Galileo, and BeiDou) observations during the period from 2022 to 2024. To analyze the impact of ionospheric scintillation characteristics over high-latitudes, we investigated the GNSS observations at the WUTH station, which is located at the Svalbard Archipelago, Norway. Our results confirm the well-established dependency of high-latitude scintillation on solar and seasonal activity, but importantly extend this understanding through a multi-constellation comparison at the WUTH during the rising phase of Solar Cycle 25. The analysis highlights subtle but systematic differences among GPS, GLONASS, Galileo, and BeiDou responses, providing practical insight into the robustness of multi-constellation monitoring under polar ionospheric disturbances. The seasonal variability of amplitude scintillation occurrence probability was calculated by normalizing the number of scintillation events by the total number of observations for each year. The results show that the GPS intense scintillations are most prominent during the summer solstices of 2023 and 2024, with a smaller peak observed during the winter solstice of 2022. GLONASS has intense and moderate scintillations concentrated in the winter seasons of 2023 and 2024, whereas weak scintillations predominantly appear in the summer of 2024. A similar pattern is observed in the Galileo and BeiDou constellations. The amplitude scintillation index (S₄) correlation coefficient with solar and geomagnetic indices for each constellation is examined. Overall, the correlation coefficient between F10.7 and the S₄ occurrence rate is low to moderate for all selected constellations, manifesting a higher correlation with GLONASS and Galileo. These results provide new, site-specific insight into constellation-dependent amplitude scintillation behavior at high latitudes and its implications for multi-GNSS monitoring and positioning robustness in polar regions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 81-90"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553496","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":"Recycling space debris for lunar applications: A mission design and energy analysis perspective","authors":"Y. Heumassej ,&nbsp;A. Cervone ,&nbsp;S. Vincent-Bonnieu","doi":"10.1016/j.jsse.2025.11.007","DOIUrl":"10.1016/j.jsse.2025.11.007","url":null,"abstract":"<div><div>This study investigates the feasibility of using space debris as a supplemental resource for Lunar infrastructure, with a particular focus on the mission design and energy requirements of debris transfer operations. While recycling methods themselves remain at a conceptual stage, this work establishes a technical baseline for how orbital debris—specifically upper stages in GTO could be captured and transported for Lunar processing. The analysis highlights the central challenge of orbital transfer alignment under long-term perturbations and evaluates multiple capture and transfer scenarios, comparing them against direct material delivery missions. Both chemical and electric propulsion architectures are assessed, demonstrating potential energy savings of up to 30 % per kilogram of material, with further reductions when rideshare configurations are employed. By quantifying the mission energy expenditure, this study clarifies the role that efficient transfer design can play in making debris recycling a viable supplement to In-Situ Resource Utilization and reducing reliance on costly terrestrial launch. The results are intended to inform future research on processing methods by first establishing the transfer architectures under which recycling missions could realistically operate.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 202-211"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553501","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":"Assessment of autonomous flight levels for aviation safety: An AHP perspective","authors":"Jale Kahraman ,&nbsp;Didem Rodoplu Şahin","doi":"10.1016/j.jsse.2025.11.003","DOIUrl":"10.1016/j.jsse.2025.11.003","url":null,"abstract":"<div><div>This study aims to evaluate the safety effects of autonomous flight technologies, which are increasingly gaining importance in the aviation sector, using the Analytical Hierarchy Process (AHP), which is a multi-criteria decision-making (MCDM) method. While automation has the potential to reduce pilot workload and increase safety, its negative effects on human factors are emphasized in the literature. In this context, the study comparatively analyzes six different automation levels (from manual flight to autonomous systems) within the framework of five basic criteria (safety contribution, potential to reduce human error, technical maturity, implementation cost and compliance with regulations). In the study, the relative priorities of the alternatives were calculated using pairwise comparison matrices created by the evaluations of 22 different experts, in line with the criteria determined by a group of 5 experts, and the automation levels were ranked within the scope of this multi-criteria structure. With the applied AHP method, the most appropriate automation level was determined and which criteria were more effective in the decision process was revealed. As a result of the final evaluation, autonomous systems ranked first with a total priority value of 30,9%, especially due to their high contribution to safety and their potential to reduce human error. It was followed by full automation (20,7%) and high automation (15,5%). No automation alternative ranked fourth (11,6%) and partial automation ranked fifth (11,1%). The tastk assist (10%) were at the bottom of the ranking with lower score. The evaluation criteria were determined as contribution to safety (47,3%), potential to reduce human error (25,4%), technical maturity (12,8%), compliance with regulations (9,1%) and implementation cost (5,4%). The results provide a valuable roadmap for decision-makers, policy-makers and industry professionals in terms of strategic technology planning, investment prioritization and legislative adaptations. In this context, the successful management of safety-focused digital transformation processes in aviation requires not only technological competence but also a holistic approach to strategic, economic and regulatory compliance.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 122-131"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553562","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":"Same orbits, different rocket dreams? China, India, and the case for global space security studies","authors":"Dimitrios Stroikos","doi":"10.1016/j.jsse.2026.01.002","DOIUrl":"10.1016/j.jsse.2026.01.002","url":null,"abstract":"<div><div>This article puts forward the case for a global space security studies using China and India as an entry point. Recent trends, including the militarization and commercialization of outer space, growing concerns over orbital debris, and the expanding number of state and non-state actors engaged in space activities, have renewed scholarly and policy debates over the nature and scope of contemporary space security. However, although the participation of new actors, particularly from the Global South, has introduced greater diversity and plurality in understandings of what constitutes space security, prevailing analyses remain largely couched in Eurocentrism. This results in reifying a universal understanding of space security rooted in Western strategic cultures, experience, and production of knowledge, which often distorts or obscures the different meanings, referent objects, and drivers of security policy in non-Western contexts. Using the cases of China and India, this article shows the ways in which their understandings and practices of space security are hybrid, influenced by an amalgam of domestic and international factors. This requires going beyond looking at how China and India’s approaches to space security resemble the Eurocentric concept of space security, which offers an incomplete and distorting view. It also entails considering how their concept of space security is defined by differences that are glossed over by Eurocentric assumptions. In so doing, this article illustrates the need for a global space security studies: a potential research agenda that takes seriously the limitations of universal conceptions of space security, while recognizing the distinct logics through which space security is constructed and practiced in different parts of the world.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 222-233"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553568","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":"An MBSE approach for early validation of safety‐critical software: Lessons learned from the cross-organizational development of the HTV‐X automated docking system","authors":"Yuki Tomita ,&nbsp;Hiroki Umeda ,&nbsp;Ryo Mikoshiba ,&nbsp;Hiroshi Kozawa ,&nbsp;Ryosuke Fujimura ,&nbsp;Yuri Hachiya ,&nbsp;Tsutomu Kobayashi ,&nbsp;Takashi Uchiyama","doi":"10.1016/j.jsse.2026.01.003","DOIUrl":"10.1016/j.jsse.2026.01.003","url":null,"abstract":"<div><div>This paper presents a Model-Based Systems Engineering (MBSE) approach for the early validation of safety-critical software in cross-organizational development, with lessons learned from its application to Japan’s HTV-X automated docking system. The HTV-X, developed by JAXA as an uncrewed cargo spacecraft for ISS (International Space Station) resupply, will conduct a technology demonstration of automated docking compliant with the International Docking System Standard (IDSS). A central system-level challenge lies in coordinating interactions between the HTV-X host vehicle and the Japan Docking System (JDS), each equipped with independent computers and software developed by different organizations. To address this, we formulated a behavior-model-driven validation workflow for evaluating the interface software, utilizing SysML models—including state machines, transition trees, and activity diagrams—to analyze both nominal and off-nominal interactions, including two-fault tolerance scenarios required for ISS safety. This paper reports the application of the proposed SysML-based workflow during the engineering model (EM) development phase, where behavioral models representing interactions among software developed by different organizations were used in scenario-based software reviews to extract review comments. These comments, derived from discrepancies or ambiguities identified in interface logic, were analyzed to clarify potential software risks at an early development stage. From this application, lessons learned were derived on the practicality, strengths, and limitations of the proposed method in software evaluation. By integrating model-based analysis with verification and validation practices, the workflow helped reduce rework, improve interface clarity, and support efficient assurance across organizational boundaries in safety-critical missions.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 1-15"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553572","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":"Robotic arm with adaptive grasper for chaser satellites to remove space debris from lower earth orbit (LEO)","authors":"Nidhi Deepak Mandrekar","doi":"10.1016/j.jsse.2026.01.005","DOIUrl":"10.1016/j.jsse.2026.01.005","url":null,"abstract":"<div><div>The proliferation of anthropogenic space debris in Low Earth Orbit (LEO) has reached a critical threshold, with over 13,000 recorded debris objects larger than 10 cm posing significant threats to current and future space missions. The cascading collision risk, known as the Kessler Syndrome, underscores the urgency for active debris removal (ADR) systems that are both scalable and adaptable. This study presents the development and experimental evaluation of a novel Chaser Satellite Grasper (CSG) mechanism designed for robust debris capture using both Static Grasping Arms (SGA) and Adaptive Bearing Arms (ABA). The CSG was engineered with a modular architecture comprising servo-actuated joints, proprioceptive sensors, gecko-inspired adhesive interfaces, and omni-directional bearing plates embedded with polymeric strips. The mechanism was evaluated through 320 controlled trials across four configurations involving two target debris analogs i.e. one with uniform and the other with irregular surface topology.</div><div>Performance metrics focused on grasp reliability, contact stability, and adaptive surface conformity. The ABA system outperformed SGA by 64 % in successful grasping attempts for uniform targets, and demonstrated an 83 % increase in capture efficiency for irregular, rough-surfaced debris analogs. These results were attributed to the ABA’s ability to leverage Van der Waals forces via a gecko-inspired adhesive layer and to conform dynamically to non-planar surfaces via multi-axis bearing movement. The integration of sensor feedback enabled closed-loop control for fine-tuned grasping trajectories and surface interaction.</div><div>In conclusion, the ABA-based CSG architecture exhibits promising potential for next-generation on-orbit servicing and active debris removal missions. The demonstrated surface adaptability and grasping fidelity contribute critical advancements to autonomous ADR platforms, and the design is adaptable to further enhancements and integration into LEO chaser satellites under the RPO (Rendezvous and Proximity Operations) framework.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 73-80"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553497","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":"Experimental study of thermomechanical properties of PTFE-based nanocomposite for space application: Thermal expansion","authors":"Sayavur I. Bakhtiyarov ,&nbsp;Lia D. Gventsadze ,&nbsp;Elguja R. Kutelia ,&nbsp;David I. Gventsadze ,&nbsp;Ayten S. Bakhtiyarova ,&nbsp;Stephen M. White","doi":"10.1016/j.jsse.2025.11.006","DOIUrl":"10.1016/j.jsse.2025.11.006","url":null,"abstract":"<div><div>Polymer based composites are of interest for use on spacecraft surfaces as dielectrics and electrical insulators, and polytetrafluoroethylene (PTFE) is a most promising polymer with thermophysical and thermomechanical advantages, but low conductivity. Fe-doped carbon nanotubes (CNT) can be added to the polymer matrix and may improve their electrical properties. A comparison of the simulation results with the experimental data obtained by different researchers showed a qualitative agreement between the simulations and the experimental data. The thermal expansion of PTFE + Fe doped CNTs composites are lower as compared to the pristine PTFE, which can be contributed to the Fe-doped CNTs. The thermal expansion of the PTFE + Fe doped CNTs composite material decreases with the concentration of the Fe-doped CNTs.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 66-72"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553499","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":"Evaluating the impact of atomic oxygen and vacuum from the space environment on composite material reliability","authors":"A. Anwar","doi":"10.1016/j.jsse.2025.11.004","DOIUrl":"10.1016/j.jsse.2025.11.004","url":null,"abstract":"<div><div>This study investigates the degradation mechanisms of polymeric nano-composite materials exposed to simulated Low Earth Orbit (LEO) space environments, concentrating on atomic oxygen (AO) erosion and vacuum-induced outgassing effects. Composite samples, comprising a two-part epoxy matrix reinforced with multi-walled carbon nanotubes (MWCNTs) and graphene-based additives, were subjected to controlled LEO conditions. Key performance metrics, including surface erosion rates, total mass loss (TML), and collected volatile condensable materials (CVCM), were quantified using Fourier-transform infrared (FTIR) spectroscopy. Results demonstrate that polymer matrices experience significant degradation under AO and vacuum conditions, demonstrating surface erosion, mechanical property reduction, and altered thermal behavior. The incorporation of nano-additives enhanced material elasticity, enabling composites to meet standard acceptance criteria for structural integrity and outgassing (TML/CVCM thresholds). Experimental data informed the development of a predictive MATLAB model integrating AO erosion kinetics, outgassing dynamics, and mechanical stress factors to forecast long-term material failure in space.</div><div>The research provides insights into how to improve the effectiveness of spacecraft in the low-Earth orbit environment by enhancing reliability, durability, and sustainability through improved material selection and design strategies. The study results enhance our understanding of the interactions between spacecraft materials and the harsh conditions of space, thus providing the basis for further improvements in low-Earth orbit spacecraft.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 59-65"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553498","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":"Asteroid and space debris detection collision prediction, and orbit visualization using deep learning and NASA APIs","authors":"Pradip Paithane","doi":"10.1016/j.jsse.2026.01.001","DOIUrl":"10.1016/j.jsse.2026.01.001","url":null,"abstract":"<div><div>In recent years, the growing threat posed by asteroids and space debris has raised significant concerns about Earth’s safety and the future of space missions. Proposed method combines machine learning, deep learning, and real-time data from NASA’s API to detect, classify, and visualize hazardous space objects. It is designed to monitor asteroid data, predict possible collisions based on specific parameters like minimum approach length, and represent orbit paths visually around Earth for better analysis and awareness. Convolutional Neural Network (CNN) model for classifying asteroids and space debris based on their features. The data is fetched directly from NASA’s Near-Earth Object Web Service (NeoWs) API, ensuring authenticity and live updates. A key highlight of work is the creation of an interactive web platform where users can monitor incoming objects in a tabular format, view collision predictions, explore orbit visualizations, and even get in touch with team through integrated contact and about sections. The orbit visualization is dynamically generated by mapping the Earth and plotting asteroid trajectories depending on their threat levels. Additionally, the system generates PDF reports summarizing each event for documentation or further analysis. All components - including frontend UI, backend processing, and ML model - were designed and implemented through proposed model, ensuring a fully functional and collaborative project. CNN model achieved a validation accuracy of 92.4%, and the collision prediction logic successfully identified real-time risky objects based on minimum approach thresholds. The orbit plots provided clear spatial understanding, while the web-based dashboard ensured transparency and real-time monitoring for all users. This aims to contribute to the global efforts in planetary defense by making space threat detection more transparent, accessible, and intelligent. Proposed Method is unique in its real-time integration, visual representation, and automated prediction system setting the foundation for future innovations in space monitoring and risk management.</div></div>","PeriodicalId":37283,"journal":{"name":"Journal of Space Safety Engineering","volume":"13 1","pages":"Pages 212-221"},"PeriodicalIF":1.7,"publicationDate":"2026-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147553624","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}