Acta Astronautica最新文献_第10页

Digital maximum power point tracking for electrical power system of CubeSats based on bat algorithm 基于bat算法的立方体卫星电力系统最大功率点数字跟踪

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.010

Zhi Yin , Tianxing Chen , Xueqin Chen , Ming Liu , Jian Chen

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.

尺寸限制限制了太阳能电池阵列的表面积，从而限制了立方体卫星的发电量。因此，电力系统（EPS）的效率是立方体卫星设计中最重要的特征。为了在长期使用CubeSats的过程中保持高效率，本工作描述了为EPS设计的数字最大功率点跟踪（MPPT）技术的实现，该技术基于改进的bat算法（BA），并在低层计算机上运行。为了保证所设计控制方法的通用性，构建了6U立方体卫星的典型系统进行后续仿真和实验。该方法利用太阳能电池阵的预测退化和遥测温度来改变BA的初始种群，并利用灰狼优化（GWO）的收敛过程来优化跟踪速度。数值模拟结果表明，该算法的平均效率为97.29%，而传统BA算法的平均效率为94.48%。同时，该算法在标准差和变异系数上都有明显的减小，提供了更稳定的跟踪。最后，建立了一个硬件测试系统来验证基于改进BA的MPPT方法，该方法可以在约30 ms内接近模拟太阳能电池阵的最大功率点，控制周期为2.5 ms。

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引用次数: 0

Multi-to-multi spacecraft impulsive cooperative interception based on reachable domain coverage 基于可达域覆盖的多对多航天器脉冲协同拦截

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.013

Chen Qing, Gang Zhang

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.

研究了基于可达域覆盖的多拦截器、多目标脉冲协同拦截问题。主要解决了多对多目标分配问题和多对一协同拦截问题。根据线性化的不确定性传播模型，用椭球方程描述了拦截弹和目标弹的定时可达域包络。然后，针对一对一拦截情况，提出了在给定脉冲时间下覆盖目标可达域的脉冲幅度的解析方法。基于一对一情况下燃料消耗的快速估计，采用粒子群优化技术解决多对多目标分配问题。此外，将多对一可达域覆盖约束转化为不等式约束，便于优化过程中的判断。最后，通过内点算法对多对一协同拦截问题进行优化。数值结果表明，所提出的多对多目标分配方法能够快速获得目标分配方案，多对一协同拦截策略与一对一拦截策略相比能够降低燃油消耗。

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引用次数: 0

Numerical investigation of gas transpiration cooling for rotating detonation combustor 旋转爆震燃烧室气体蒸腾冷却的数值研究

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.007

Yingxin Zhang , Jia Tian , Shufeng Zhang , Xiaoming Tan , Jingzhou Zhang , Fulei Zhu , Zhengwei Fan , Jingyang Li , Wenqian Hao

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.

旋转爆震波引起的极端热负荷对旋转爆震燃烧室的热防护提出了严峻的挑战。本研究探讨了气体蒸腾冷却用于RDC热防护的可行性，建立了轴向多孔介质的局部物理模型来模拟爆震波与冷却剂的相互作用。通过比较不同冷却剂质量流量和孔隙率下的蒸腾冷却特性，揭示了旋转爆震波区和斜激波区的不同冷却机制。数值结果表明，蒸腾冷却形成200-720 K的多孔壁面热障，隔离了2280-2800 K的爆轰核心，使壁面热流密度降低72%，压力峰值降低20 - 83%。最佳的冷却性能要求孔隙度的分割：0.5的倾斜激波区使效率最大化，而0.4的爆震区则避免了由于流动不稳定而增加的热流密度。0.5%的冷却剂与主流质量流量比提供了连续的热保护，冷却效率为0.72，而1.0%的冷却剂会导致膜破裂和温度波动。多孔介质作为化学调节剂，通过反渗透作用抑制燃烧，增加水蒸气浓度，实现惰性气体缓冲。压力在12μs内消散，但由于固相惯性，热衰减滞后，因此需要进行层状孔隙度设计和精确的冷却剂控制来实现RDC稳定性。

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引用次数: 0

Kinematic orbit determination for BDS-3 satellites with inter-satellite link data 基于星间链路数据的BDS-3卫星运动学定轨

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-06 DOI: 10.1016/j.actaastro.2026.01.015

Chao Yang , Jing Guo , Xiaolong Mi , Yuanfan Deng , Xuexi Liu , Qile Zhao , Wu Chen

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.

运动学定轨方法消除了耗时的轨道整合和复杂的卫星动力学建模（如太阳辐射压力、地球辐射压力等），为传统方法提供了一种高效、高精度的替代方案。利用部署在北斗全球导航卫星系统（BDS-3）上的ka波段星间链路（ISL）有效载荷，本研究首次展示了使用实际ISL测量的BDS-3卫星的运动学定轨结果。分析表明，中地球轨道（MEO）卫星的位置精度稀释系数（PDOP）在0.8 ~ 2.0之间，而倾斜地球同步轨道（IGSO）和静止地球轨道（GEO）卫星的位置精度稀释系数（PDOP）分别在1.2 ~ 2.5和1.2 ~ 2.0之间。除1颗卫星外，MEO、IGSO和GEO卫星在精确动力学解约束下的运动轨道三维均方根值分别约为13.6 cm、23.5 cm和33.7 cm。北斗三号卫星的平均横航迹精度为7.3 cm，比顺航迹和径向精度高1.5 cm以上。此外，本工作系统地研究了固定卫星数量对运动学解的影响，表明固定两颗卫星比只固定一颗卫星可提高29%的轨道精度，并且约束所有IGSO和GEO卫星对MEO卫星产生最佳结果，平均3D均方根值为15.8 cm（沿轨道），14.5 cm（交叉轨道）和14.0 cm（径向）。值得注意的是，由于在日食季节没有检测到明显的下降，运动学轨道精度保持稳定。

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引用次数: 0

Noordung's “Wohnrad” – the precursor to rotating space station architecture Noordung的“Wohnrad”——旋转空间站建筑的先驱

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2025-12-16 DOI: 10.1016/j.actaastro.2025.12.006

DrIng Sandra Haeuplik-Meusburger

The drawings of a rotating space station, introduced by Hermann Potočnik, known as Noordung, in his book The Problem of Space Travel 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.

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.

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.

赫尔曼·波托尼克（Hermann poto nik，又名Noordung）在1929年出版的《太空旅行的问题》一书中介绍了旋转空间站的图纸，这是太空飞行概念史上的一个里程碑。19世纪80年代，康斯坦丁·齐奥尔科夫斯基（Konstantin Tsiolkovsky）、赫尔曼·奥伯特（Hermann Oberth）等科学家和火箭工程师已经讨论过空间站的概念，而诺顿则首次提出了空间站的详细技术描述和图纸。其中许多想法推动了旋转空间站的其他有趣概念。本文概述了旋转轮形空间站的概念，特别关注了“Wohnrad”和“天文台”，以及它的内部建筑设计特点。它提供了有关其历史背景的信息，以及这一概念在20世纪50年代由沃纳·冯·布劳恩（Wernher von Braun）和艺术家切斯利·博尼斯特尔（Chesley Bonestell）等人传播的信息，他们向公众推广了空间站的愿景。本文的独特之处在于对其空间建筑概念的重新评估，该概念基于对诺顿空间站的数字重建。书中的原始图纸、平面图、图像和文字描述被翻译成一个详细的三维虚拟模型。该模型随后使用3D打印制作为物理原型。通过这个重建空间站几何形状的过程，对整体建筑概念产生了新的见解，包括不同栖息地模块之间的比例关系、空间布局和操作逻辑。此外，重建揭示了与室内建筑和空间功能使用相关的意想不到的发现，使我们能够更好地理解Noordung的设计意图，并从当代的角度评估他的概念的可行性。本研究深化了对早期空间栖息地概念的历史认识，也为未来的旋转空间栖息地和空间建筑领域的发展提供了宝贵的经验教训。

{"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}

引用次数: 0

Design and analysis of a foldable pyramid-shaped architecture for environmental protection at Lunar surface 月球表面可折叠金字塔型环保建筑的设计与分析

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2025-12-26 DOI: 10.1016/j.actaastro.2025.12.041

Ghulam Muhammad Owaisi , Wente Pan , Sandra Haeuplik-Meusburger , Shuai Yuan

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.

可持续月球建筑的基础要求创造性的结构设计能够承受月球环境的极端条件。这项研究提出了一种混合月球结构的创新设计，它包含一个可折叠的内部框架，一个轻量级的可扩展层和一个风化层。这种设计可以显著减少昼夜温度的变化。研究了热性能和力学性能，以评价结构的稳定性。在热分析中，结构的热动力学描述了热的输入和输出通量。在不同的太阳仰角下，月球日的表面温度分布和变化被解释来证明结构的热行为。通过传热分析，优化风化层厚度，保证内部热稳定性。为了提供机械灵活性，固体力学分析优化了可膨胀层厚度，并评估了施加在内部框架上的不同边界载荷。原位月球风化层的应用提高了成本效率和可部署性，并减少了发射质量。该设计和结果支持该结构的储层能力，以保护任务资产，如居住室，科学仪器和漫游者，免受极端温度和微陨石撞击。这为操作提供了一个稳定的平台。这项研究为先进的月球探测铺平了道路，提供了一种最小的方法，资源高效的设计，促进了早期任务，并为月球定居奠定了基础。未来的工作将集中在提高材料的弹性，探索几何复杂性，并进行实验验证，以进一步改善这种基础设施。

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引用次数: 0

Anthropogenic Space Object attitude and material characterisation through multi-colour light curve inversion 基于多色光曲线反演的人为空间物体姿态和材料表征

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-08 DOI: 10.1016/j.actaastro.2025.12.060

Luís Filipe Pino Gonçalves , Nevan Simone , A.K. de Almeida Jr , Domingos Barbosa , Moriba Jah , Timothée Vaillant , Bruno Coelho , Alexandre C.M. Correia

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

B

,

V

,

R

) 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.

人为空间目标的光曲线反演在单波段进行时存在病态性，导致姿态和材料参数的非唯一组合。我们提出了一个基于Cook-Torrance双向反射分布函数、地球和自遮挡的显式阴影以及以卫星为中心的几何形状的物理接地正演模型。我们将姿态-材料检索作为一个约束优化问题，并使用多色光曲线（Johnson-Cousins B， V， R）通过耦合波长不变参数来规范反演。在四个不同形态的空间对象上，多色约束提高了拟合质量，缩小了相对全色反演的可接受解集。我们报告了多起点退火的参数不确定性，并提供了对关键BRDF和姿态参数的拟合灵敏度。结果支持多色光学测量作为单一地点明确ASO特征的有效途径。

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引用次数: 0

Managing delay-induced challenges in remote monitoring of uncrewed space habitats: The impact of forecasting telemetry visualizations 管理无人空间栖息地远程监测中延迟引起的挑战：预测遥测可视化的影响

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2025-12-20 DOI: 10.1016/j.actaastro.2025.12.036

Zixu Zhang , Sreehari Manikkan , Murali Krishnan , Mohsen Azimi , Luca Vaccino , Jiachen Wang , Chuanyu Xue , Shirley J. Dyke , Ilias Bilionis , Song Han , Paul Parsons

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.

未来的深空任务将需要地面团队在严重的通信延迟下监控和管理无人栖息地，这迫使操作人员在没有实时反馈的情况下预测系统行为并对异常情况做出反应。本研究探讨视觉预测辅助工具是否能支持这些认知需求。在一项对照实验中，35名参与者在三种条件下进行模拟栖息地监测任务：无延迟和无预测、无预测的延迟和有预测支持的延迟。我们测量了任务表现、心理工作量（NASA TLX）和汇报反应。具有预测辅助的参与者更有效地维护了系统稳定性，报告了明显较低的时间需求，具有更低挫折和努力的趋势，并描述了使用预测来指导前瞻性计划。这些研究结果表明，预测工具可以增强延迟监督控制的期望管理和决策。未来的工作应该在专家操作人员和更多不同的操作场景中检查它们的应用。

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引用次数: 0

Hypervelocity impact on Whipple shields with varying bumper material at 3 and 7 km/s: A numerical study using a coupled FEM/DEM method 在3和7 km/s速度下，不同保险杠材料对惠普尔护盾的超高速撞击：采用FEM/DEM耦合方法的数值研究

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2025-12-23 DOI: 10.1016/j.actaastro.2025.12.040

Rannveig M. Færgestad , Christopher J. Cline II , Eric L. Christiansen , Joshua E. Miller , Kevin A. Ford , Odd S. Hopperstad , Jens K. Holmen , Tore Børvik

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.

惠普尔护盾中的缓冲器是与来袭弹丸相互作用的第一层，对弹丸破片和碎片云的形成起着至关重要的作用。本研究对不同保险杠材料在超高速撞击下的性能进行了数值研究，并通过球面弹丸以3和7 km/s的速度撞击惠普尔护盾的实验数据进行了验证。研究了五种保险杠材料配置——Nextel编织织物、带前面板的开放式泡沫铝、钢丝网、铝丝网和带铝板的贝塔布——并将其与面积密度接近相等的传统薄铝6061-T6保险杠进行了比较。采用有限元-离散元耦合方法（FEM/DEM）进行数值模拟，将失效的实体单元转换为离散颗粒。创建保险杠材料的数值模型来捕捉材料的结构和几何形状，采用中尺度方法对编织织物进行建模，其中纱线被建模为连续的、均匀的实体，并采用随机Voronoi细胞方法来生成开孔泡沫结构。对保险杠和后壁上的碎片云和损伤进行了研究，并与3 km/s和7 km/s下的相应实验结果进行了比较，总体上相似，得出了相同的“及格/不及格”结果。弹丸碎片在撞击缓冲器后仍以固体形式存在，这对造成后壁损伤至关重要。在某些配置中，弹丸碎片的大小被低估了，导致后壁上的弹坑更小、更少。此外，通过不同的冲击速度和弹丸直径组合进行数值模拟，估计了冲击速度从1到11 km/s的所有六种惠普尔盾构型的弹道极限曲线。该研究提出了一种采用FEM/DEM耦合方法的数值模拟方法，该方法可以一致地应用于包括不同结构和尺度的材料的超高速冲击问题，在所研究的配置和冲击速度中显示出总体良好的结果。

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引用次数: 0

The feasibility of potentially hazardous asteroids flybys using multiple Venus gravity assists 利用多个金星引力辅助，潜在危险小行星飞掠的可行性

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-04-01 Epub Date: 2026-01-08 DOI: 10.1016/j.actaastro.2026.01.016

Vladislav Zubko

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.

这项工作开发了低能航天器（SC）的轨迹，利用金星引力辅助研究小行星在行星相遇之间的日心转移段。这项研究将潜在危险小行星（PHAs）作为主要的探测目标。本文提出了一种计算金星重力辅助后小行星飞掠的SC轨迹的方法。该方法包括制定和解决一个优化问题，以设计包含选定小行星和金星飞越的轨迹。通过求解朗伯问题，利用二体动力学计算轨迹。对候选小行星的初步搜索使用了一种算法来缩小优化问题的搜索空间。该算法使用v无限球技术将行星引力辅助与共振轨道连接起来。在这种情况下，共振轨道作为SC在两次连续的行星飞掠之间的轨迹的初始近似。分析了四种飞行方案，包括多次飞越金星和小行星，以及SC返回地球的可能性。提出的解决方案减少了小行星接近之间的飞行时间，增加了重力辅助频率，并增强了任务设计的灵活性。金星引力辅助和共振轨道的使用确保了在连续两次飞越金星之间的SC轨道上至少与一颗小行星近距离接触，并证明了金星引力辅助和周期性接触pha的可行性。该方法被应用于构建轨道，允许SC通过多个金星重力辅助来接近与金星和pha共轨道的小行星。另一项研究是在2029年至2050年的发射窗口期间，确定地球-金星段可到达的小行星。

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引用次数: 0