Acta Astronautica最新文献

{"title":"Digital maximum power point tracking for electrical power system of CubeSats based on bat algorithm","authors":"Zhi Yin ,&nbsp;Tianxing Chen ,&nbsp;Xueqin Chen ,&nbsp;Ming Liu ,&nbsp;Jian Chen","doi":"10.1016/j.actaastro.2026.01.010","DOIUrl":"10.1016/j.actaastro.2026.01.010","url":null,"abstract":"<div><div>Size constraints restrict the surface area of solar arrays and thus the generated power for CubeSats. Therefore, the efficiency of the electrical power system (EPS) is the most important feature in the design of CubeSats. To maintain a high efficiency over long-term use of CubeSats, this work describes the implementation of a digital maximum power point tracking (MPPT) technique devised for EPS, which is based on an improved bat algorithm (BA) and runs on the lower computer. To ensure the universality of the designed control method, a typical system of a 6U CubeSat is constructed for subsequent simulations and experiments. The new proposed MPPT method utilizes the predicted degradation and telemetry temperature of solar arrays to change the initial population of BA, and refers to the convergence process of gray wolf optimization (GWO) to optimize tracking speed. Numerical simulation results show that the average efficiency of the new proposed algorithm is 97.29% across all simulations, compared to 94.48% for conventional BA. Meanwhile, the proposed algorithm shows a marked reduction in both standard deviation and coefficient of variation, providing a more stable tracking. Finally, a hardware testing system is established to validate the MPPT method based on the improved BA, and it can approach the maximum power point (MPP) of the simulated solar array within about 30 ms with a 2.5 ms control cycle.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 170-180"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145897508","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":"Multi-to-multi spacecraft impulsive cooperative interception based on reachable domain coverage","authors":"Chen Qing,&nbsp;Gang Zhang","doi":"10.1016/j.actaastro.2026.01.013","DOIUrl":"10.1016/j.actaastro.2026.01.013","url":null,"abstract":"<div><div>This paper studies the multi-interceptor and multi-target impulsive cooperative interception problem based on reachable domain coverage. Two problems are mainly solved including the multi-to-multi target assignment problem and the multi-to-one cooperative interception problem. According to the linearized uncertainty propagation model, the envelopes of fixed-time reachable domains for both the interceptors and the targets are described by ellipsoidal equation. Then, for the one-to-one interception case, an analytical method is proposed to obtain the impulse magnitude for covering the target’s reachable domain with given impulse time. Based on the rapid estimations of fuel consumption for the one-to-one case, the particle swarm optimization technique is employed to resolve the multi-to-multi target assignment problem. In addition, the multi-to-one reachable domain coverage constraint is converted into the inequality constraint, which is easy to judge in the optimization process. Finally, the multi-to-one cooperative interception problem for optimal fuel consumption is optimized through the interior-point algorithm. Numerical results show that the proposed multi-to-multi target assignment method can rapidly obtain the assignment scheme, and the multi-to-one cooperative interception strategy can reduce the fuel consumption when compared with the one-to-one interception.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 234-244"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145902756","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":"Numerical investigation of gas transpiration cooling for rotating detonation combustor","authors":"Yingxin Zhang ,&nbsp;Jia Tian ,&nbsp;Shufeng Zhang ,&nbsp;Xiaoming Tan ,&nbsp;Jingzhou Zhang ,&nbsp;Fulei Zhu ,&nbsp;Zhengwei Fan ,&nbsp;Jingyang Li ,&nbsp;Wenqian Hao","doi":"10.1016/j.actaastro.2026.01.007","DOIUrl":"10.1016/j.actaastro.2026.01.007","url":null,"abstract":"<div><div>The extreme thermal loads induced by rotating detonation waves pose critical challenges to the thermal protection of rotating detonation combustors (RDCs). This study investigates the feasibility of gas transpiration cooling for RDC thermal protection, establishing a localized physical model of axial porous media to simulate detonation wave-coolant interactions. By comparing transpiration cooling characteristics under varying coolant mass flow rates and porosities, the study reveals distinct cooling mechanisms between rotating detonation wave and oblique shock wave regions. Numerical results indicate that transpiration cooling forms a 200–720 K porous wall thermal barrier, isolates the 2280–2800 K detonation core, and reduces wall heat flux by 72 % and pressure peaks by 20–83 %. Optimal cooling performance requires partitioned porosity: a sloping shock zone of 0.5 maximizes efficiency, while a detonation zone of 0.4 avoids increased heat flux due to flow instability. A 0.5 % coolant-to-mainstream mass flow ratio provides continuous thermal protection with a cooling efficiency of 0.72, while 1.0 % causes film breakage and temperature fluctuations. The porous medium acts as a chemical regulator to inhibit combustion and increase water vapor concentration through reverse osmosis to achieve inert gas buffering. The pressure dissipates within 12μs, but the thermal decay lags due to solid-phase inertia, which underscores the need for zonal porosity design and precise coolant control to achieve RDC stability.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 293-313"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145903432","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":"Kinematic orbit determination for BDS-3 satellites with inter-satellite link data","authors":"Chao Yang ,&nbsp;Jing Guo ,&nbsp;Xiaolong Mi ,&nbsp;Yuanfan Deng ,&nbsp;Xuexi Liu ,&nbsp;Qile Zhao ,&nbsp;Wu Chen","doi":"10.1016/j.actaastro.2026.01.015","DOIUrl":"10.1016/j.actaastro.2026.01.015","url":null,"abstract":"<div><div>Kinematic orbit determination offers an efficient and highly accurate alternative to traditional methods by eliminating the need for time-consuming orbit integration and complex satellite dynamics modeling (e.g., solar radiation pressure, earth radiation pressure, etc.). Leveraging the Ka-band inter-satellite link (ISL) payloads deployed on the BeiDou global navigation satellite system (BDS-3), this study presents, for the first time, kinematic orbit determination results for BDS-3 satellites using real ISL measurements. The analysis reveals that the position dilution of precision (PDOP) for Medium Earth Orbit (MEO) satellites ranges from 0.8 to 2.0, while for Inclined Geosynchronous Orbit (IGSO) and Geostationary (GEO) satellites, PDOP values remain within 1.2–2.5 and 1.2–2.0, respectively. The mean 3D RMS values of kinematic orbits are approximately 13.6 cm, 23.5 cm, and 33.7 cm for MEO, IGSO and GEO satellites, respectively, when the orbits of all satellites except one are constrained to the precise dynamic solutions. The mean cross-track accuracy of BDS-3 satellites is 7.3 cm, which is more than 1.5 cm larger than that of the along-track and radial directions. Furthermore, this work systematically investigates the impact of the number of fixed satellites on kinematic solutions, demonstrating that fixing two satellites improves orbit accuracy by 29 % over fixing just one, and that constraining all IGSO and GEO satellites yields optimal results for MEO satellites, with mean 3D RMS values of 15.8 cm (along-track), 14.5 cm (cross-track), and 14.0 cm (radial). Notably, the kinematic orbit accuracy remains robust, as no significant decrease is detected during eclipse seasons.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 608-619"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145979119","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":"Noordung's “Wohnrad” – the precursor to rotating space station architecture","authors":"DrIng Sandra Haeuplik-Meusburger","doi":"10.1016/j.actaastro.2025.12.006","DOIUrl":"10.1016/j.actaastro.2025.12.006","url":null,"abstract":"<div><div>The drawings of a rotating space station, introduced by Hermann Potočnik, known as Noordung, in his book <em>The Problem of Space Travel</em> in 1929, mark a milestone in the history of spaceflight concepts. While scientists and rocket engineers like Konstantin Tsiolkovsky, Hermann Oberth and others had already discussed the concept of a spacestation in the 1880s, Noordung presented the first detailed technical description and drawings of a space station. Many of these ideas have propelled other interesting concepts for rotating space stations.</div><div>This paper provides an overview of the rotating wheel-shaped space station concept, with a special attention to the ‘Wohnrad’ and the ‘Observatory’, and its interior architectural design features. It provides information about its historical context, and the dissemination of this concept by figures such as Wernher von Braun and the artist Chesley Bonestell, and others, who promoted the vision of a spacestation to the general public in the 1950s.</div><div>The unique part of this paper is the re-assessment of its space-architectural concept, based on a digital reconstruction of Noordung's space station. The original drawings, plans, images, and textual descriptions from Noordung's book were translated into a detailed three-dimensional virtual model. The model was subsequently produced as a physical prototype using 3D printing. Through this process of reconstructing the station's geometry, new insights emerged regarding the overall architectural concept — including the proportional relationships between the different habitat modules, spatial layout, and operational logic. Additionally, the reconstruction revealed unexpected findings related to the interior architecture and functional use of space, allowing us to better understand Noordung's design intentions and evaluate the feasibility of his concept from a contemporary perspective. This research deepens the historical understanding of early space habitat concepts, and also provides valuable lessons for future rotating space habitats and the evolving field of space architecture.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 594-607"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145979118","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":"Design and analysis of a foldable pyramid-shaped architecture for environmental protection at Lunar surface","authors":"Ghulam Muhammad Owaisi ,&nbsp;Wente Pan ,&nbsp;Sandra Haeuplik-Meusburger ,&nbsp;Shuai Yuan","doi":"10.1016/j.actaastro.2025.12.041","DOIUrl":"10.1016/j.actaastro.2025.12.041","url":null,"abstract":"<div><div>The foundation of sustainable lunar architecture demands a creative structural design that can withstand the extreme conditions of lunar environment. This study proposes an innovative design for a hybrid lunar structure, containing a foldable internal frame, a lightweight expandable layer, and a regolith layer. This design can significantly reduce the variation in temperature during the day and night. Thermal and mechanical properties are studied to evaluate the stability of structure. In thermal analysis, thermal dynamics of the structure describe the input and output flux of heat. The surface temperature distribution and variations across a lunar day at different solar elevation angles are explained to demonstrate the thermal behavior of the structure. Regolith layer thickness optimization is conducted to ensure interior thermal stability through heat transfer analysis. To provide mechanical flexibility, solid mechanics analysis optimized the expandable layer thickness and evaluated the different boundary loads applied to the internal frame. The application of in-situ lunar regolith enhances cost efficiency, deployability, and reduces launch mass. The design and results support the structure’s capacity for storage compartments, which protect mission assets, such as habitation chambers, scientific instruments, and rovers, from extreme temperatures and micrometeorite impacts. This provides a stable platform for operations. This research paves the way for advanced lunar exploration by contributing a minimal-approach, resource-efficient design that facilitates early-stage missions and lays the foundation for lunar settlements. Future work will focus on enhancing material resilience, exploring geometric intricacies, and conducting experimental validation to further improve this infrastructure.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 97-113"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145845196","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":"Anthropogenic Space Object attitude and material characterisation through multi-colour light curve inversion","authors":"Luís Filipe Pino Gonçalves ,&nbsp;Nevan Simone ,&nbsp;A.K. de Almeida Jr ,&nbsp;Domingos Barbosa ,&nbsp;Moriba Jah ,&nbsp;Timothée Vaillant ,&nbsp;Bruno Coelho ,&nbsp;Alexandre C.M. Correia","doi":"10.1016/j.actaastro.2025.12.060","DOIUrl":"10.1016/j.actaastro.2025.12.060","url":null,"abstract":"<div><div>Light-curve inversion for anthropogenic space objects (ASOs) is ill-posed when performed in a single band, which leads to non-unique combinations of attitude and material parameters. We present a physically grounded forward model based on a Cook–Torrance bidirectional reflectance distribution function, explicit shadowing by Earth and self-occlusion, and a satellite-centred geometry. We cast attitude–material retrieval as a constrained optimisation problem and use multi-colour light curves (Johnson–Cousins <span><math><mi>B</mi></math></span>, <span><math><mi>V</mi></math></span>, <span><math><mi>R</mi></math></span>) to regularise the inversion by coupling wavelength-invariant parameters. On four space objects of distinct morphology, the multi-colour constraint improves fit quality and narrows the admissible solution set relative to panchromatic inversions. We report parameter uncertainties from multi-start annealing and provide sensitivity of the fit to key BRDF and attitude parameters. Results support multi-colour optical surveys as an efficient path to unambiguous ASO characterisation from a single site.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 378-408"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145940442","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":"Managing delay-induced challenges in remote monitoring of uncrewed space habitats: The impact of forecasting telemetry visualizations","authors":"Zixu Zhang ,&nbsp;Sreehari Manikkan ,&nbsp;Murali Krishnan ,&nbsp;Mohsen Azimi ,&nbsp;Luca Vaccino ,&nbsp;Jiachen Wang ,&nbsp;Chuanyu Xue ,&nbsp;Shirley J. Dyke ,&nbsp;Ilias Bilionis ,&nbsp;Song Han ,&nbsp;Paul Parsons","doi":"10.1016/j.actaastro.2025.12.036","DOIUrl":"10.1016/j.actaastro.2025.12.036","url":null,"abstract":"<div><div>Future deep-space missions will require ground teams to monitor and manage uncrewed habitats under significant communication delays, forcing operators to anticipate system behavior and respond to anomalies without real-time feedback. This study investigates whether visual forecasting aids can support these cognitive demands. In a controlled experiment, 35 participants performed a simulated habitat monitoring task under one of three conditions: no delay and no forecast, delay without forecast, or delay with forecasting support. We measured task performance, mental workload (NASA TLX), and debrief responses. Participants with forecasting aids maintained system stability more effectively, reported significantly lower temporal demand, with trends toward lower frustration and effort, and described using forecasts to guide proactive planning. These findings suggest that forecasting tools can enhance expectation management and decision-making in delayed supervisory control. Future work should examine their application with expert operators and across more varied operational scenarios.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 1-18"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145786117","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":"Hypervelocity impact on Whipple shields with varying bumper material at 3 and 7 km/s: A numerical study using a coupled FEM/DEM method","authors":"Rannveig M. Færgestad ,&nbsp;Christopher J. Cline II ,&nbsp;Eric L. Christiansen ,&nbsp;Joshua E. Miller ,&nbsp;Kevin A. Ford ,&nbsp;Odd S. Hopperstad ,&nbsp;Jens K. Holmen ,&nbsp;Tore Børvik","doi":"10.1016/j.actaastro.2025.12.040","DOIUrl":"10.1016/j.actaastro.2025.12.040","url":null,"abstract":"<div><div>The bumper in a Whipple shield is the first layer to interact with an incoming projectile, playing a critical role in the projectile fragmentation and debris cloud formation. This study presents a numerical investigation into the performance of different bumper materials under hypervelocity impact, validated against experimental data where spherical projectiles impact Whipple shields at 3 and 7 km/s. Five bumper material configurations — Nextel woven fabric, open-cell aluminum foam with a front face sheet, steel wire mesh, aluminum wire mesh and Beta cloth with an aluminum plate — are studied and compared to a conventional thin Al 6061-T6 bumper of near equal areal density. Numerical simulations are performed using a coupled finite element–discrete element method (FEM/DEM), where failed solid elements are converted to discrete particles. Numerical models of the bumper materials are created to capture the structure and geometry of the materials, employing a mesoscale approach for the woven fabrics where yarns are modeled as continuous, homogenized entities, and a stochastic Voronoi cell approach to generate an open-cell foam structure. The debris clouds and damage on the bumpers and rear walls are studied and compared to the corresponding experimental results at 3 and 7 km/s, showing overall similarity and resulting in the same ”Pass/Fail” result. Projectile fragments remaining in solid element form after impacting the bumpers are important for the resulting rear wall damage. The sizes of the projectile fragments are underestimated for some configurations, leading to smaller and fewer craters on the rear walls. Further, ballistic limit curves are estimated for all six Whipple shield configurations for impact velocities from 1 to 11 km/s, by performing numerical simulations with different combinations of impact velocity and projectile diameter. The study presents a numerical modeling approach with a coupled FEM/DEM method that can be applied consistently to hypervelocity impact problems which include materials with different structures and scales, showing overall good results across the investigated configurations and impact velocities.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 61-84"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145823367","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":"The feasibility of potentially hazardous asteroids flybys using multiple Venus gravity assists","authors":"Vladislav Zubko","doi":"10.1016/j.actaastro.2026.01.016","DOIUrl":"10.1016/j.actaastro.2026.01.016","url":null,"abstract":"<div><div>This work develops low-energy spacecraft (SC) trajectories using Venus gravity assists to study asteroids during heliocentric transfer segments between planetary encounters. The study focuses on potentially hazardous asteroids (PHAs) as primary exploration targets. This paper proposes a method for calculating SC trajectories that enable asteroid flybys after a Venus gravity assist. The method involves formulating and solving an optimization problem to design trajectories incorporating flybys of selected asteroids and Venus. Trajectories are calculated using two-body dynamics by solving the Lambert problem. A preliminary search for candidate asteroids uses an algorithm to narrow the search space of the optimization problem. This algorithm uses the V-infinity globe technique to connect planetary gravity assists with resonant orbits. The resonant orbit in this case serves as an initial approximation for the SC’s trajectory between two successive planetary flybys. Four flight schemes were analyzed, including multiple flybys of Venus and asteroids, with the possibility of an SC returning to Earth. The proposed solutions reduce flight time between asteroid approaches, increase gravity assist frequency, and enhance mission design flexibility. The use of Venus gravity assists and resonant orbits ensures a close encounter with at least one asteroid during the SC’s trajectory between two consecutive flybys of Venus, and demonstrates the feasibility of periodic Venus gravity assists and encounters with PHAs. The developed method was applied to construct trajectories that allow an SC to approach both co-orbital asteroids with Venus and PHAs via multiple Venus gravity assists. An additional study was carried out to identify asteroids accessible during the Earth–Venus segment in launch windows between 2029 and 2050.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"241 ","pages":"Pages 504-528"},"PeriodicalIF":3.4,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145978440","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}