Acta Astronautica最新文献

{"title":"Sun sensor calibration algorithms: A systematic mapping and survey","authors":"Michael Herman,&nbsp;Olivia J. Pinon Fischer,&nbsp;Dimitri N. Mavris","doi":"10.1016/j.actaastro.2025.12.053","DOIUrl":"10.1016/j.actaastro.2025.12.053","url":null,"abstract":"<div><div>Attitude sensors determine the spacecraft attitude through the sensing of an astronomical object, field or other phenomena. The Sun and fixed stars are the two primary astronomical sensing objects. Attitude sensors are critical components for the survival and knowledge improvement of spacecraft. Of these, sun sensors are one of the most common and important sensors for small satellite attitude determination. The sun sensor measures the Sun vector in spacecraft coordinates. The sun sensor calibration process is particularly difficult due to the complex nature of the uncertainties involved. The uncertainties are small, difficult to observe, and vary spatio-temporally over the lifecycle of the sensor. In addition, the sensors are affected by numerous sources of uncertainties, including manufacturing, electrical, environmental, and interference sources. This motivates the development of advanced calibration algorithms to minimize uncertainty over the sensor lifecycle and improve accuracy. Although modeling and calibration techniques for sun sensors have been explored extensively in the literature over the past two decades, there is currently no resource that consolidates and systematically reviews this body of work. The present review proposes a systematic mapping of sun sensor modeling and calibration algorithms across a breadth of sensor configurations. It specifically provides a comprehensive survey of each methodology, along with an analysis of research gaps and recommendations for future directions in sun sensor modeling and calibration techniques.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"243 ","pages":"Pages 112-148"},"PeriodicalIF":3.4,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146033458","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Covariance estimation and fusion for ephemeris-only catalogues applied to the Special Perturbations Catalogue","authors":"Pietro Canal ,&nbsp;Alejandro Cano ,&nbsp;Santiago Martínez ,&nbsp;Adrián Hernández ,&nbsp;Pierluigi Di Lizia ,&nbsp;Diego Escobar","doi":"10.1016/j.actaastro.2026.01.063","DOIUrl":"10.1016/j.actaastro.2026.01.063","url":null,"abstract":"<div><div>The availability of realistic covariance information for the orbit of every Resident Space Object (RSO) contained in a catalogue is crucial for Space Situational Awareness activities, e.g., collision avoidance services. The most comprehensive of these catalogues is the Special Perturbations Catalogue (SPCAT), maintained by the U.S. 18th Space Defense Squadron. The SPCAT is the high-precision ephemeris version of the Two Line Elements RSOs catalogue, publicly available on databases such as Space Track and Celestrak. However, covariance information is not provided with the mean state of the SPCAT ephemerides. So-called observed covariance values can be obtained via a comparison procedure between consecutive orbit information updates referring to the same SPCAT RSO. This paper proposes new methodologies for calculating covariance values for catalogues deprived of such information, including the application and adaptation of existing data-fusion methods from literature. The main final goal is to compute covariance matrices that are more realistic and reliable than those obtained with the currently available methods. Another key objective is the integration of the new methodology in an operational environment. Computational efficiency is then a relevant factor, and the baseline method to be developed is selected and improved taking into account such efficiency criterion. A new routine that considers the Orbit Determination epoch of each RSO ephemeris arc to coherently combine covariances based on their propagation time is developed and implemented. Two fusion methods are deployed, Covariance Intersection and Covariance Union, and the realism of the results is tested with a well-established metric, the Mahalanobis distance and its fitting of the Chi-square distribution according to appropriate Empirical Distribution Function tests such as Cramer-von Mises. The realism of the combined covariances is validated against precise ephemeris of LEO Sentinel satellites. While Covariance Intersection is proved inadequate as a stand-alone fusion method due to the characteristics of the SPCAT observed covariances, Covariance Union provides covariance values that are consistently more realistic than the ones obtained with the baseline method.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"243 ","pages":"Pages 207-219"},"PeriodicalIF":3.4,"publicationDate":"2026-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146072606","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Airborne re-entry observation campaign of the Cluster-II salsa re-entry","authors":"Stefan Loehle ,&nbsp;Fabian Zander ,&nbsp;Patrik Kaerraeng ,&nbsp;Tobias Lips ,&nbsp;Gerard Armstrong ,&nbsp;Byrenn Birch ,&nbsp;Ranjith Ravichandran ,&nbsp;Clemens Mueller ,&nbsp;Juraj Toth ,&nbsp;Tomasz Paulech ,&nbsp;Jiri Silha ,&nbsp;Matej Zigo ,&nbsp;Beatriz Jilete ,&nbsp;Stijn Lemmens","doi":"10.1016/j.actaastro.2026.01.030","DOIUrl":"10.1016/j.actaastro.2026.01.030","url":null,"abstract":"<div><div>After their end of operation, the four Cluster-II satellites are re-entering the Earth’s atmosphere. The first Cluster-II satellite, named <em>Salsa</em>, re-entered on the 8th of September at 18:46<!--> <!-->UTC (2024-09-08T18:46 UTC) over the South Pacific, approximately 2000<!--> <!-->km west of Easter Island. An airborne observation team was on station aiming to observe the satellite’s break-up. This paper reports the design and execution of the airborne observation under the challenging situation of an entry under plain daylight conditions. The mission planning and preparation in coordination with the observation prediction leads to the flight mission details. Due to the highly eccentric orbit, the entry predictions were particularly challenging and resulted in a wider spread of potential entry corridors. Therefore, based on the very last perigee, only 52 h before the actual entry, and spacecraft data after the maneuver, the team received the last orbit information at 20:30<!--> <!-->UTC on the 7th of September (2024-09-07T20:30UTC). Based on this data an appropriate flight path for the aircraft was designed. On board a Falcon 900 business jet, the team deployed six different stations with a total of 26 cameras. All cameras were time-synchronized to the GPS time using a centralized time server. The mission was successful. The infrared cameras detected the entry for approximately 23<!--> <!-->s beginning at around 18:47:08<!--> <!-->UTC.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 74-84"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145961921","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Fly me to the moon: Family conferencing with communication delays on lunar missions","authors":"Sheena I. Dev ,&nbsp;Nikole D. Moody ,&nbsp;Diana P. Arias ,&nbsp;Suzanne T. Bell","doi":"10.1016/j.actaastro.2026.01.022","DOIUrl":"10.1016/j.actaastro.2026.01.022","url":null,"abstract":"<div><h3>Background</h3><div>Current astronauts on the International Space Station have scheduled time to connect with their families via virtual audio and video private family conferences (PFCs). However, one-way communication delays expected to range from 4 to 12 s during lunar missions represent a significant paradigm shift for PFCs which have thus far operated with real-time communication. The objective of this study was to determine the effect of lunar communication delays on the expected benefits of PFCs in astronaut-like participants and their families.</div></div><div><h3>Methods</h3><div>Thirty-five primary participants were recruited to approximate astronaut demographics at NASA Johnson Space Center in Houston, Texas. They were asked to identify a family member living outside of Houston to join as their study partner. Each study pair participated in six weekly virtual audiovisual PFC sessions conducted under 0, 4, 6, 8, 10, or 12 s one-way delays. Relationship and individual well-being outcomes were assessed before and after each PFC. Communication quality was assessed after each PFC in reference to the delay implemented. Linear mixed models with planned contrasts examined the impact of each PFC on relationship, individual well-being, and communication quality.</div></div><div><h3>Results</h3><div>PFCs improved relationship outcomes relative to baseline regardless of the delay. Compared to PFCs with no delays, greater decrements to relationships and individual well-being were observed after PFCs with 8 s one-way delays or longer. Participants also indicated all delay latencies significantly reduced their communication quality and would impact their relationships if they were required to continue communicating under those conditions for six months.</div></div><div><h3>Conclusion</h3><div>PFCs benefit long distance relationships among astronaut-like families. While participants generally tolerated shorter communication delays in this time limited laboratory setting, our results suggest that PFCs with communication delays, especially 8 s or longer, may not be sufficient to maintain family bonds in future long duration lunar missions. These findings underscore the importance of maintaining access to family and friends during spaceflight and provide a foundation from which innovative solutions can be crafted to preserve connections despite obstacles to communication.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 48-57"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146039452","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Propellantless space exploration","authors":"Roman Ya. Kezerashvili","doi":"10.1016/j.actaastro.2026.01.024","DOIUrl":"10.1016/j.actaastro.2026.01.024","url":null,"abstract":"<div><div>Propellantless propulsion refers to methods of space travel that do not require onboard propellant, instead relying on natural forces or external energy sources. In this paper, I review different approaches that have been explored and discuss Pros and Cons for each approach for interstellar space exploration.</div><div><em>Gravitational assist</em> uses planetary gravity to change a spacecraft’s speed and direction without fuel. It is effective but limited to specific alignments.</div><div><em>Solar sails</em> harness radiation pressure from sunlight for continuous, fuel-free acceleration. While effective over time, they require large, reflective materials that degrade in space. Speed can be enhanced by thermal desorption triggered by solar radiation.</div><div><em>Magnetic sails</em> generate thrust by interacting with the solar wind through superconducting loops that produce a magnetic field. They provide lower acceleration compared to solar sails, and their performance depends on the available power and the variability of solar wind conditions.</div><div><em>Electric sails</em> utilize charged tethers to repel solar wind protons, producing gradual acceleration. Their effectiveness depends on the successful deployment of very long, lightweight conductive wires. They can achieve higher acceleration than solar sails, and their performance is influenced by available power and solar wind conditions.</div><div>Lastly, <em>quantum effects</em>, such as the Casimir force, offer a speculative but intriguing route to propellantless propulsion based on the vacuum energy of space.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 17-31"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145969385","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Overall results of the SMPAG work package on mission scenarios definition in response to the 2025 Planetary Defense Conference Hypothetical Asteroid Impact Threat Scenario","authors":"Juan L. Cano ,&nbsp;Michael Khan ,&nbsp;Camilla Colombo ,&nbsp;Massimiliano Vasile ,&nbsp;Richard Moissl ,&nbsp;Detlef Koschny","doi":"10.1016/j.actaastro.2026.01.023","DOIUrl":"10.1016/j.actaastro.2026.01.023","url":null,"abstract":"<div><div>The members of the Space Mission Planning Advisory Group (SMPAG) performed an asteroid impact simulation exercise over a medium size asteroid with impact chances on 24 April 2041, in preparation for the 2025 Planetary Defense Conference. The exercise was articulated on two different simulation periods lasting, respectively, two months and a half and four months. In the first period, Epoch 1, the asteroid impact probability grew from 1.6% to 10% and was played in real time. A preliminary assessment of the required actions that would need to be implemented and a set of recommendations were provided at a plenary SMPAG session held on 10 October 2024. Epoch 2 was simulated after the fast flyby of a reconnaissance mission by the asteroid in April 2028 that allowed refining the asteroid size, and impact location. An assessment of the decisions that were required and the feasible mission options was performed in order to facilitate a recommendation by the SMPAG plenary. Based on a trade-off of several deflection mission strategies, mission options included kinetic impactors, ion-beam deflection and nuclear explosive devices.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 158-165"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146039836","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"A polynomial-based Monte Carlo approach for estimating long-term collision probabilities","authors":"Andrea Zollo ,&nbsp;Cristina Parigini ,&nbsp;Roberto Armellin ,&nbsp;Juan Félix San Juan Díaz ,&nbsp;Annarita Trombetta ,&nbsp;Ralph Kahle","doi":"10.1016/j.actaastro.2026.01.039","DOIUrl":"10.1016/j.actaastro.2026.01.039","url":null,"abstract":"<div><div>This paper introduces a versatile approach for computing the risk of collision specifically tailored for scenarios featuring low relative encounter velocities, but with potential applicability across a wide range of situations. The technique employs Differential Algebra (DA) to express the non-linear dynamical flow of the initial distribution in the primary-secondary objects relative motion through high-order Taylor polynomials. The entire initial uncertainty set is subdivided into subsets through Automatic Domain Splitting (ADS) techniques to control the accuracy of the Taylor expansions. The methodology samples the initial conditions of the relative state and evaluates the polynomial expansions for each sample while retaining their temporal dependency. The classical numerical integration of the initial statistics over the set of conditions for which a collision occurs is thus reduced to an evaluation of mono-dimensional time polynomials. Specifically, samples reaching a relative distance below a critical value are identified along with the time at which this occurs. The approach is tested against a Monte Carlo (MC) simulation for various literature test cases, yielding accurate results and a consistent gain in computational time. Specifically, the time reduction can reach up to 99.9 %, depending on the dynamics and the number of samples employed in the analysis, while the estimated final Probability of Collision (<em>Pc</em>), for long-term scenarios, deviates from the reference by no more than 0.018 %.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 178-192"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146001048","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Energy-optimized attitude planning for spacecraft with movable parts using auxiliary rotation","authors":"Yuqi Fan ,&nbsp;Zhe Zhu ,&nbsp;Rui Xu ,&nbsp;Zhaoyu Li ,&nbsp;Shengying Zhu ,&nbsp;Shengyu Zhang ,&nbsp;Xiuwei Li","doi":"10.1016/j.actaastro.2025.12.049","DOIUrl":"10.1016/j.actaastro.2025.12.049","url":null,"abstract":"<div><div>Attitude planning is required for spacecraft with movable parts to allow the pointing of the movable sensor to avoid strong light celestial bodies. For the orbiter in the shadow region or deep space probe, it is important to consider the optimization of energy consumption in attitude planning because of energy limitations. Nevertheless, prior approaches to attitude planning for spacecraft with movable parts rely on deterministic decoupled strategies, which minimize body rotations solely from a geometric standpoint. We provide an energy-optimized decoupled strategy based on Differential Evolution (DE) to deal with this problem. This strategy introduces a new auxiliary rotation vector as the individual vector for optimization, transforming attitude maneuver sequences with minimal geometric rotation into sequences optimized for energy consumption. Furthermore, the fitness function is tailored to the Polynomial Attitude Trajectory Planning (PATP) and Decoupled Attitude Trajectory Planning (DATP) approaches in order to estimate energy consumption, which is refined throughout the evolutionary process. Simulation results indicate the suggested method’s energy optimization effect and ability to handle complex constraints.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 166-177"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145823359","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Probabilistic Risk Assessment (PRA) for Artemis and future space exploration programs","authors":"Kim Lane ,&nbsp;Aditi Nilvarna ,&nbsp;George W.S. Abbey Jr. ,&nbsp;Michael T. Kezirian","doi":"10.1016/j.actaastro.2025.06.045","DOIUrl":"10.1016/j.actaastro.2025.06.045","url":null,"abstract":"<div><div>NASA has developed a comprehensive safety process for complex programs. Integral to all programs are relevant safety requirements which establish hazard controls, typically without regard to the likelihood of corresponding failure modes. NASA has added the Probabilistic Risk Assessment (PRA) to the suite of tools for complex space programs. This paper reviews the use of PRA across NASA's human spaceflight programs and examines how the scope and influence of the methodology have evolved over time. Although there is a tendency to focus on the final numerical result of a PRA, its true value lies in the complete PRA model—including the identification of top failure modes that contribute to overall risk. This insight enables both design and operational decisions aimed at reducing those contributors and improving overall system safety. PRA was first introduced during the operational phase of the Space Shuttle Program—not as part of the original design—but as a tool for ongoing program evaluation and improvement. A similar approach was taken with the International Space Station (ISS), where PRA was applied post-design to support maintenance planning, operational rule development, and crew training.</div><div>In the Commercial Crew Program (CCP), PRA became integral to the design process, with formal thresholds for Loss of Crew (LOC) and Loss of Mission (LOM) used to guide system development in parallel with traditional safety requirements. In contrast, for the Artemis program, PRA is used solely as an evaluation tool to inform program management and communicate risk.</div><div>A key limitation of PRA is its dependence on data to estimate the probability of failure. For newer programs with limited operational history, generating this data involves considerable subjectivity, with varying methods and assumptions across organizations. To strengthen the consistency and credibility of PRA, it is recommended that the space industry develop a consensus-based approach—bringing together NASA, commercial providers, and spaceflight participants to align data inputs, modeling practices, and application scope.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 127-140"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146039835","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}

{"title":"Optimization of vacuum arc thruster efficiency through inductive energy storage circuit control","authors":"Ping-Han Huang ,&nbsp;Yueh-Heng Li","doi":"10.1016/j.actaastro.2025.12.063","DOIUrl":"10.1016/j.actaastro.2025.12.063","url":null,"abstract":"<div><div>This study explores the optimization of vacuum arc thruster (VAT) performance through precise control of an inductive energy storage circuit. Two experimental approaches were investigated: (1) By varying the inductor charging time under single-pulse ignition, this experiment aims to determine the relationship between the circuit components and the performance of the VAT. (2) Implementing a dual-pulse ignition scheme with controlled inter-pulse delays, which aims to determine whether two ignitions interact with each other. In the single-pulse tests, maximum thrust performance occurred when the inductor current reached its peak. Reducing the charging current to approximately 76 % of this peak resulted in decreases of 28 %, 38 %, and 42 % in discharge energy, plasma plume, and mass ablation rate, respectively. These results demonstrate that VAT performance is strongly dependent on the energy stored in the inductor and the magnitude of the induced voltage generated upon IGBT turn-off.</div><div>In the dual-pulse tests, triggering two identical inductive circuits with a <strong>3</strong> μs inter-pulse delay significantly enhanced performance. Compared to a 3000 μs delay, this shortest delay resulted in a 68.74 % lower breakdown voltage for the second pulse, a 15.22 % increase in total discharge energy, a 98.7 % extension in discharge duration, and a 356 % increase in the ablation rate.</div><div>The highest thrust of 12.07 μN s and thrust-to-power ratio of 29.97 μN s/W were achieved at this shortest delay. These findings highlight that both induced voltage characteristics and short inter-pulse plasma dynamics play critical roles in maximizing VAT performance, offering practical insights for high-efficiency pulsed electric propulsion system design.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"242 ","pages":"Pages 32-47"},"PeriodicalIF":3.4,"publicationDate":"2026-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145902739","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"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}