Acta Astronautica最新文献

英文中文

Covariance estimation and fusion for ephemeris-only catalogues applied to the Special Perturbations Catalogue 应用于特殊摄动星表的星历表协方差估计和融合

IF 3.5 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-29 DOI: 10.1016/j.actaastro.2026.01.063

Pietro Canal, Alejandro Cano, Santiago Martínez, Adrián Hernández, Pierluigi Di Lizia, Diego Escobar

引用次数: 0

Flexible PVA/BA gel for passive radiation shielding in spacesuit applications beyond LEO 柔性PVA/BA凝胶，用于低轨道以外航天服的被动辐射屏蔽

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

Acta Astronautica

Pub Date : 2026-01-28 DOI: 10.1016/j.actaastro.2026.01.066

Lucia Lambertini , Maria Gabriella Santonicola , Susanna Laurenzi

Protection of astronauts from intense space radiation during long-term missions to the Moon or Mars remains a critical challenge. With space agencies planning permanent lunar bases as gateways for deep-space exploration, enhancing radiation shielding in spacesuits during extravehicular activities (EVAs) is essential. This study explores the feasibility of integrating poly(vinyl alcohol) (PVA)-based gels as an intermediate shielding layer between the pressure bladder garment (PBG) and the liquid cooling and ventilation garment (LCVG), without altering suit geometry or increasing layer thickness. Due to their high water content, PVA-based gels combine flexibility, softness, and ductility with effective radiation attenuation. Experimental analyses compared the physical and mechanical properties of PVA gels to nylon, the primary material of PBG and LCVG. The gels exhibited similar density and thermal conductivity but demonstrated superior deformability, achieving elongations up to ∼65 % despite a lower Young's modulus. Numerical simulations performed with the OLTARIS confirmed the shielding potential of the proposed configuration. While protection against Galactic Cosmic Rays (GCR) remained limited due to their high penetration depth, the inclusion of PVA-based gel layers significantly reduced proton doses from Solar Particle Events (SPE), indicating their potential as an effective, lightweight enhancement to current spacesuit designs.

在前往月球或火星的长期任务中，保护宇航员免受强烈的太空辐射仍然是一项重大挑战。随着航天机构计划将永久月球基地作为深空探测的门户，在舱外活动（eva）期间加强宇航服的辐射屏蔽是必不可少的。本研究探讨了将聚乙烯醇（PVA）基凝胶作为压力气囊服（PBG）和液体冷却通风服（LCVG）之间的中间屏蔽层的可行性，而不改变服装的几何形状或增加层厚。由于其高含水量，pva基凝胶结合了柔韧性，柔软性和延展性与有效的辐射衰减。实验分析了PVA凝胶与尼龙（PBG和LCVG的主要材料）的物理力学性能。凝胶具有相似的密度和导热性，但表现出优异的变形能力，尽管杨氏模量较低，但伸长率高达65%。利用OLTARIS进行的数值模拟证实了所提出结构的屏蔽电位。尽管由于其高穿透深度，对银河宇宙射线（GCR）的防护仍然有限，但pva基凝胶层的包含显着减少了太阳粒子事件（SPE）的质子剂量，表明它们有潜力成为当前宇航服设计的有效轻量级增强。

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引用次数: 0

Autonomous optical flow-based initial orbit determination 基于自主光流的初始轨道确定

IF 3.5 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-28 DOI: 10.1016/j.actaastro.2026.01.054

Willem Oliveira

引用次数: 0

Numerical simulation of water migration in lunar soil based on the Monte Carlo model 基于蒙特卡罗模型的月壤水分迁移数值模拟

IF 3.5 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-28 DOI: 10.1016/j.actaastro.2026.01.067

Yan Zhang, Yongjun Wang, Jin Wang, Chengdan He, Wenfeng Li, Huzhong Zhang, Yasheng Li, Detian Li

引用次数: 0

Microgravity-induced alterations in left atrial hemodynamics and thrombogenic risk: Insights from healthy and atrial fibrillation models 微重力诱导的左心房血流动力学改变和血栓形成风险：来自健康和心房颤动模型的见解

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

Acta Astronautica

Pub Date : 2026-01-27 DOI: 10.1016/j.actaastro.2026.01.058

Grace Hoeppner , Ahmad Bshennaty , Brennan Vogl , Ghasaq Saleh , Mohamad Alkhouli , Hoda Hatoum

Background

Microgravity exposure alters cardiovascular loading, yet its impact on left atrial flow dynamics and thrombotic risk remains poorly understood. This study investigates how spaceflight-relevant microgravity-induced changes in cardiac outflow affect left atrial hemodynamics in healthy individuals and patients with atrial fibrillation.

Methods

Patient-specific left atrial models were generated for three healthy individuals and three AF patients. Computational fluid dynamics (CFD) simulations were performed using each patient's baseline mitral outflow waveform and two modified waveforms representing short- and long-duration post-flight cardiac loading changes derived from echocardiographic observations. Hemodynamic metrics included left atrial velocity, time averaged wall shear stress, oscillatory shear index, relative residence time, and stasis volume, which were used to assess thrombogenic flow conditions.

Results

Post-flight, microgravity-associated modifications to mitral outflow conditions produced distinct hemodynamic responses across cohorts. In healthy individuals, short-duration post-flight loading reduced time-averaged wall shear stress from 1.51 to 1.00 Pa and increased velocity-defined stasis from 19.6 % to 64.2 %, indicating substantially reduced atrial washout. Under long-duration post-flight conditions, these metrics recovered toward or above baseline values (time-averaged wall shear stress 1.68 Pa; stasis 18.5 %), consistent with hemodynamic adaptation. In contrast, patients with atrial fibrillation exhibited high baseline stasis and showed minimal changes in time-averaged wall shear stress, oscillatory shear, or relative residence time across all loading conditions. Across all cohorts, the left atrial appendage consistently demonstrated the lowest shear and highest residence time.

Conclusion

These findings indicate that spaceflight-related microgravity exposure may transiently increase atrial flow stasis and thrombotic risk in individuals with normal atrial function, while individuals with atrial fibrillation remain in a persistently high-risk hemodynamic state that is relatively insensitive to microgravity-induced loading changes. This study provides the first patient-specific, chamber-level computational assessment of how spaceflight-documented cardiac adaptations influence left atrial hemodynamics and highlights the importance of accounting for duration-dependent hemodynamic adaptation when assessing thrombotic risk associated with human spaceflight.

微重力暴露会改变心血管负荷，但其对左心房血流动力学和血栓形成风险的影响仍知之甚少。本研究探讨了与太空飞行相关的微重力诱导的心流出物变化如何影响健康个体和心房颤动患者的左心房血流动力学。方法建立3例健康人左心房模型和3例房颤患者左心房模型。计算流体动力学（CFD）模拟使用每位患者的基线二尖瓣流出波形和两个修改波形，代表飞行后心脏负荷的短期和长期变化，这些变化来自超声心动图观察。血流动力学指标包括左心房速度、时间平均壁剪切应力、振荡剪切指数、相对停留时间和停滞体积，这些指标用于评估血栓性血流状况。结果飞行后，微重力相关的二尖瓣流出条件的改变在队列中产生了不同的血流动力学反应。在健康个体中，短时间的飞行后负荷将时间平均壁剪切应力从1.51降低到1.00 Pa，并将速度定义的停滞从19.6%增加到64.2%，这表明心房冲洗明显减少。在长时间的飞行后条件下，这些指标恢复到接近或高于基线值（时间平均壁剪切应力1.68 Pa；停滞18.5%），与血流动力学适应一致。相比之下，房颤患者表现出较高的基线停滞，在所有负载条件下，时间平均壁剪切应力、振荡剪切或相对停留时间的变化最小。在所有队列中，左心耳一致表现出最低的剪切和最高的停留时间。结论航天飞行相关的微重力暴露可能会短暂增加心房功能正常个体的房流停滞和血栓形成风险，而心房颤动患者仍处于持续的高危血流动力学状态，对微重力引起的负荷变化相对不敏感。这项研究首次提供了患者特异性的、舱室水平的计算评估，以了解航天记录的心脏适应如何影响左房血流动力学，并强调了在评估与人类航天相关的血栓风险时考虑持续时间依赖性血流动力学适应的重要性。

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引用次数: 0

A 698 nm laser system for excitation of fluorescent quantum light sources on a CubeSat mission 立方体卫星任务中用于荧光量子光源激发的698 nm激光系统

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

Acta Astronautica

Pub Date : 2026-01-27 DOI: 10.1016/j.actaastro.2026.01.060

Sven Schwertfeger , Elisa Da Ros , Marcel Bursy , Andreas Wicht , Daniel Pardo , Ankush Sharma , Subash Sachidananda , Alexander Ling , Markus Krutzik

This manuscript reports on the development and qualification of an ECDL-based, fiber-coupled laser system at a wavelength of

λ = 698

nm for space applications. We designed and developed the optical and mechanical configuration, along with the laser driving and thermal management electronics, to meet space compatibility requirements. Validation tests were conducted on off-the-shelf components to assess their suitability for satellite deployment. The final system integrates all components into a compact design optimized for CubeSat platforms.

本文报道了一种基于ecdl的、波长为λ=698 nm的用于空间应用的光纤耦合激光系统的开发和鉴定。我们设计并开发了光学和机械配置，以及激光驱动和热管理电子设备，以满足空间兼容性要求。对现成组件进行了验证测试，以评估其是否适合卫星部署。最终系统将所有组件集成到一个针对立方体卫星平台优化的紧凑设计中。

引用次数: 0

Dynamic Cone Penetration Test in Lunar Highlands Regolith Simulant 模拟月球高地风土的动态锥突试验

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

Acta Astronautica

Pub Date : 2026-01-25 DOI: 10.1016/j.actaastro.2026.01.055

Kārlis Šļumba, Brendan T. Scott, Mark B. Jaksa

It is essential to understand the geotechnical properties of the ground before anything can be built on Earth, the Moon, or elsewhere. The cone penetrometer is a simple but very important instrument that yields quantitative and qualitative information about the geotechnical properties of the material. Quantitative information is the penetration resistance from which density and layering can be inferred, and ground improvement can be evaluated. Qualitative information includes identifying layering and inhomogeneities, as well as the existence of boulders.

Cone penetrometers are often proposed for space missions (e.g., Beagle 2, InSight, Philae) and were even used by Apollo astronauts. All cone penetrometers that have been used extra-terrestrially so far have either experienced difficulties with penetration or were designed to penetrate less than 100 mm deep and stop before encountering any meaningful resistance. An optimally developed dynamic cone penetrometer might work better because it requires less reaction force.

This research consists of the development of a bespoke dynamic cone penetrometer with variable cone size and hammering energy. Further, this instrument is tested in a large-scale regolith compaction chamber with lunar highlands regolith simulant LHS-1E at a wide range of densities to find the optimal setup where penetration captures enough data by moving slowly but also does not stagnate. Results from dynamic cone penetration tests at many different densities are compared and successfully correlated to cone penetration and nuclear density gauge test results. Calculated coefficients allow for the conversion directly between dynamic and regular cone penetration tests at any density, which shows promise for greater use of dynamic cone penetrometers in lunar applications.

在地球、月球或其他地方建造任何东西之前，了解地面的岩土力学特性是至关重要的。圆锥贯入仪是一种简单但非常重要的仪器，它可以提供有关材料岩土特性的定量和定性信息。定量信息是穿透阻力，从中可以推断密度和分层，并可以评估地面改善情况。定性信息包括识别分层和非均质性，以及巨石的存在。

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引用次数: 0

Efficiency Metrics and Numerical Simulation Procedure for Atmosphere-Breathing Electric Propulsion (ABEP) Intake Designs 空气呼吸式电力推进（ABEP）进气设计的效率度量和数值模拟程序

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

Acta Astronautica

Pub Date : 2026-01-24 DOI: 10.1016/j.actaastro.2026.01.037

M.B. Agir , N.H. Crisp , K.L. Smith , P.C.E. Roberts , Z. Xiang , M. Newsam , M. Griffiths

The intake of an atmosphere-breathing electric propulsion system plays a pivotal role in capturing and collimating atmospheric residuals prior to the propulsion stage. Accurate assessment of intake performance necessitates accounting for rarefied gas dynamics, flow compression, and gas-surface interactions. In this study, the DSMC solver, dsmcFoam, is rigorously validated against fundamental benchmarks, including Clausing empirical cases and comparisons with the PICLas solver. Furthermore, dsmcFoam-dsmcFoam comparison is also conducted and observed deviations between our results and existing dsmcFoam results in the literature highlight the critical importance of careful simulation setup and procedural rigour. A systematic analysis of the simulation workflow, supplemented by additional computational strategies, demonstrates their pronounced impact on intake performance metrics. Furthermore, distinct definitions for efficiency – namely, collection efficiency and transmission efficiency for vacuum, standalone, and integrated configurations – are introduced, establishing a comprehensive framework for evaluating intake performance across varying operational altitudes and surface properties. The findings confirm that (i) dsmcFoam represents a reliable tool for ABEP intake design, providing a foundation for further developments, (ii) a structured and generic simulation procedure tailored for ABEP intakes is essential, and (iii) conventional efficiency metrics for ABEP intakes needs reconsideration for broader applicability and accurate performance evaluation.

空气呼吸式电力推进系统的进气口在推进阶段前的大气残留捕获和准直中起着关键作用。进气性能的准确评估需要考虑稀薄气体动力学、流动压缩和气体表面相互作用。在本研究中，DSMC求解器，dsmcFoam，严格验证了基本基准，包括条款的经验案例和与PICLas求解器的比较。此外，还进行了dsmcFoam-dsmcFoam比较，并观察到我们的结果与文献中现有的dsmcFoam结果之间的偏差，强调了仔细模拟设置和程序严谨性的重要性。仿真工作流程的系统分析，辅以额外的计算策略，证明了它们对进气性能指标的显著影响。此外，介绍了不同的效率定义，即真空、独立和集成配置的收集效率和传输效率，建立了一个综合框架，用于评估不同操作高度和表面特性的进气性能。研究结果证实：(1)dsmcFoam是ABEP进气设计的可靠工具，为进一步开发提供了基础；(2)为ABEP进气定制的结构化和通用模拟程序是必不可少的；(3)ABEP进气的传统效率指标需要重新考虑，以获得更广泛的适用性和准确的性能评估。

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引用次数: 0

“Getting Things Done” or “Doing the Right Things”? Micro-foundations of Product-Service Strategies in Earth Observation “把事情做好”还是“做正确的事情”？地球观测产品服务策略的微观基础

IF 3.5 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-24 DOI: 10.1016/j.actaastro.2026.01.040

Valentina Zancan, Paolo Trucco, Giorgio Locatelli

引用次数: 0

Feasibility-guaranteed analytical mars landing guidance in hazardous terrains with disturbances 具有干扰的危险地形中可行性保证的分析火星着陆制导

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

Acta Astronautica

Pub Date : 2026-01-23 DOI: 10.1016/j.actaastro.2026.01.053

Yan Wang , Yaxuan Li , Xinfu Liu

This paper investigates the Mars landing guidance problem in hazardous terrains. Disturbances during landing, including parameter uncertainties and external forces, may cause the guidance problem infeasible, preventing the lander from avoiding the terrains. To ensure a safe landing, it is crucial, though challenging, to maintain the recursive feasibility of the guidance problem in each guidance cycle. To this end, we propose a two-phase guidance framework, where recursive feasibility is considered only in the first phase and the terminal constraints in this phase are significantly relaxed. This turns the recursive feasibility requirement into the assured satisfaction of the terrain avoidance constraint under disturbances in each guidance cycle. The main contribution of this work lies in analytically deriving a feasible control set and proving that, as long as the control command is within this set, the state at the next guidance cycle must be able to reach the required terminal state while satisfying the terrain avoidance constraint. This guarantees the recursive feasibility of the guidance problem, provided it is feasible in the initial time. As a result, guidance commands in the first phase can be generated by the well-known ZEM/ZEV guidance law, and then simply saturated by the derived feasible control set. In the second phase, the terrain avoidance constraint no longer needs to be considered and the ZEM/ZEV guidance law is applied to drive the lander to the desired location with a safe touchdown velocity. Numerical examples demonstrate that the proposed method can ensure recursive feasibility of the guidance problem under disturbances and is capable of achieving meter-level landing accuracy.

研究了危险地形下的火星着陆制导问题。着陆过程中的干扰，包括参数不确定性和外力，可能导致制导问题不可行，阻止着陆器避开地形。为了确保安全着陆，在每个制导周期中保持制导问题的递归可行性是至关重要的，尽管这是一项挑战。为此，我们提出了一个两阶段的指导框架，其中仅在第一阶段考虑递归可行性，并且该阶段的终端约束明显放宽。这将递归的可行性要求转化为在每个制导周期中干扰下地形回避约束的保证满足。本工作的主要贡献在于解析导出了可行控制集，并证明了只要控制命令在可行控制集内，下一个制导周期的状态一定能够在满足地形回避约束的情况下达到所要求的终端状态。这保证了制导问题的递归可行性，只要它在初始时间内是可行的。因此，第一阶段的制导命令可以由已知的ZEM/ZEV制导律生成，然后由推导的可行控制集简单饱和。在第二阶段，不再考虑地形回避约束，采用ZEM/ZEV制导律驱动着陆器以安全的着陆速度到达目标位置。数值算例表明，该方法能保证制导问题在扰动下的递归可行性，并能达到米级着陆精度。

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