Acta Astronautica最新文献

英文中文

Parametric evaluation of a cavity flameholder with transverse reacting hydrogen injection applied to a scramjet combustor 超燃冲压发动机燃烧室横向反应喷氢腔式火焰座的参数评价

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.01.059

William Veber Moisés da Silva , André Fernando de Castro da Silva , Vinicius Malatesta , Cornelis Henricus Venner

Scramjet engines offer great potential for hypersonic propulsion and space access, but efficient combustion remains challenging due to the extremely short residence time for fuel–air mixing and burning. This study presents a parametric investigation of a cavity flameholder with upstream transverse hydrogen injection applied to the HyShot-IV scramjet combustor geometry, using RANS-based CFD simulations in Ansys CFX. The model incorporates the

k

–

ω

SST turbulence model and the Burning Velocity Model to analyze the impact of cavity aspect ratio (AR) on key performance parameters, including mixing efficiency, combustion-chamber efficiency, flame stabilization, and pressure recovery. Six configurations were examined: one baseline without a cavity and five cavity cases with

A R \in {3.2; 4.0; 4.5; 5.75; 7.0}

. Results demonstrate that cavity flameholders significantly enhance combustion performance by generating recirculation zones, stabilizing the flame, and intensifying turbulence, which collectively promote efficient fuel–air mixing, and these favorable effects are further amplified with increasing AR. Case E (

A R = 7.0

) achieved the highest performance, with mixing and combustion efficiencies of 72.3% and 72.5%, respectively, at the expense of a moderate reduction in pressure recovery to 53.8%. Conversely, smaller cavities, such as in Case A (

A R = 3.2

), provided limited mixing improvements, with a mixing efficiency of 55.9%, yet retained higher pressure recovery at 56.7%. Key flow features observed include shear layers, cavity expansion shocks, and counter-rotating vortex pairs (CVPs), which interact with shock waves and boundary layers to enhance fuel distribution and combustion. Larger cavities, such as in Cases D (

A R = 5.75

) and E, promoted earlier hydrogen consumption and sustained combustion zones. The baseline configuration, lacking a cavity, exhibited the lowest performance metrics, with poor mixing efficiency (51.3%) and delayed combustion, underscoring the importance of cavity-induced structures for efficient scramjet operation.

超燃冲压发动机为高超声速推进和空间进入提供了巨大的潜力，但由于燃料-空气混合和燃烧的停留时间极短，高效燃烧仍然是一个挑战。本研究采用Ansys CFX中基于ranss的CFD模拟，对HyShot-IV型超燃冲压发动机燃烧室几何结构中具有上游横向氢喷射的腔型火焰支架进行了参数化研究。该模型结合k -ω SST湍流模型和燃烧速度模型，分析了空腔展弦比（AR）对混合效率、燃烧室效率、火焰稳定性和压力恢复等关键性能参数的影响。研究了六种配置：一种无空腔基线和五种空腔病例，AR∈{3.2;4.0;4.5;5.75;7.0}。结果表明，腔式火焰支架通过形成再循环区、稳定火焰和增强湍流来显著提高燃烧性能，这些因素共同促进了燃料-空气的高效混合，并且这些有利作用随着AR的增加而进一步增强。情况E （AR=7.0）的性能最高，混合效率和燃烧效率分别达到72.3%和72.5%，而压力恢复则适度降低至53.8%。相反，较小的空腔，如情况A (AR=3.2)，提供了有限的混合改善，混合效率为55.9%，但保持了较高的压力恢复，达到56.7%。观察到的主要流动特征包括剪切层、空腔膨胀激波和反向旋转涡对（cvp），它们与激波和边界层相互作用，增强燃料分布和燃烧。更大的空腔，如情况D （AR=5.75）和E，促进了早期的氢消耗和持续燃烧区域。没有空腔的基准配置表现出最低的性能指标，混合效率很差（51.3%），燃烧延迟，强调了空腔诱导结构对高效超燃冲压发动机运行的重要性。

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引用次数: 0

ICOTOM post-flight analysis: Infrared radiative measurements from the Schiaparelli capsule entry within the ExoMars 2016 mission ICOTOM飞行后分析：ExoMars 2016任务中Schiaparelli太空舱进入的红外辐射测量

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.02.006

J. Annaloro, P. Hebert, P. Omaly, A. Gülhan, T. Thiele, F. Siebe, P. Boubert, A. Bultel, M. Jacquot, M. Spel, M. Lesage, Ph. Rivière, A. Soufiani

引用次数: 0

Electron-beam lunar dust mitigation under solar-like vacuum ultraviolet illumination 在类似太阳的真空紫外线照明下电子束月球尘埃减缓

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.01.070

Josef L. Richmond , Joshua R. Machacek , Christine Charles , Roderick W. Boswell

Electrostatic dust-cleaning with low-energy electron beams is a promising countermeasure against regolith contamination expected during sustained Lunar surface operations. Laboratory demonstrations, however, typically neglect the vacuum ultraviolet (VUV) component of solar radiation that dominates photoelectric charging on the Lunar dayside. Here we quantify, for the first time, the influence of a sun-like VUV spectrum on electron-beam-driven dust removal from spacesuit fabrics. Beta-cloth samples deliberately contaminated with OPRLJSCN Lunar Mare simulant were exposed to (i) a thermionic electron beam (

30 μ A

cm⁻²,

\leq

120 eV) and (ii) VUV fluxes generated by a mixed-gas 13.56 MHz RF plasma lamp that reproduces the solar spectrum in the 115–160 nm range. Three illumination regimes were tested: no VUV (dark), lunar-equivalent VUV (0.3 mW cm⁻²), and elevated VUV (5 mW cm⁻²). The inclusion of VUV photons significantly lowered the threshold beam current density and energy to initiate dust mobilisation, with the filament bias needed to initiate lift-off falling from –93 V (dark) to –52 V (lunar-equivalent VUV) and –37 V (elevated VUV), while the required beam current density dropped by up to two orders of magnitude. Dust removal efficiency improved from 76% after 72 s (dark) to 85% in 48 s (lunar VUV) and 95% in only 9 s under strong illumination. Furthermore, the mean particle size reduced with increasing VUV flux from

29 μ m

(brushing) to

16 μ m

(dark). Results indicate that the Solar VUV can be exploited to reduce power requirements and cleaning time for electron-beam dust mitigation, and motivates inclusion of realistic illumination environments in future mitigation trials.

低能量电子束静电除尘是一种很有前途的对抗月球表面持续运行中风化层污染的对策。然而，实验室演示通常忽略了太阳辐射的真空紫外线（VUV）成分，它主导着月球白天的光电充电。在这里，我们首次量化了类似太阳的紫外光谱对电子束驱动的航天服织物除尘的影响。用OPRLJSCN月球海模拟剂污染的β -布样品暴露在(i) 30μA cm−2，≤120 eV的热离子电子束和（ii）由混合气体13.56 MHz射频等离子体灯产生的VUV通量下，该灯再现了115-160 nm范围内的太阳光谱。测试了三种照明模式：无VUV（暗）、与月球相当的VUV （0.3 mW cm - 2）和高VUV （5 mW cm - 2）。VUV光子的包含显著降低了启动尘埃动员的阈值光束电流密度和能量，启动起飞所需的灯丝偏压从-93 V（暗）降至-52 V（月球等效VUV）和-37 V（高光VUV），而所需的光束电流密度下降了两个数量级。在强光照条件下，72 s（黑暗）除尘效率为76%，48 s（月球紫外线）除尘效率为85%，9 s除尘效率为95%。随着VUV通量的增加，平均粒径从29μm（刷色）减小到16μm（暗色）。结果表明，太阳能VUV可用于降低电子束粉尘缓解的功率要求和清洁时间，并激励在未来的缓解试验中纳入现实的照明环境。

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引用次数: 0

Evaluation of non-invasive brain stimulation techniques for use on long duration spaceflight missions 用于长时间航天飞行任务的非侵入性脑刺激技术的评估

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.02.007

Sage O. Sherman, Allison P. Hayman

Degraded mental performance is a risk for astronauts on long duration spaceflight missions for which non-invasive, unobtrusive countermeasures are currently under investigation. Inducing neuromodulation using non-invasive brain stimulation (NiBS) techniques may be a useful and safe countermeasure approach to stimulate neural processes, but to date a synthesis of promising techniques has not been performed. This work evaluates four NiBS techniques: transcranial electrical stimulation (tES), transcranial magnetic stimulation (TMS), transcranial photobiomodulation (tPBM), and stochastic resonance (SR). We identify each technique's most promising attributes for efficacy in improving human performance while demonstrating the ability to be administered in a spaceflight environment. The evaluation scored each technology on three variables related to supporting human performance and mental health, and three variables related to crew and mission implementation. This analysis suggests that the separate NiBS techniques map better to addressing these specific variables. However, none of the techniques evaluated have currently been demonstrated in space. It is unknown whether the spaceflight environment affects the brain and its neural mechanisms in a way that impacts its interaction with NiBS techniques. We recommend continued investment to address these limitations. Further, the methods in this paper to assess emergent medical countermeasures may be applied for other technologies and be directed toward specific mission requirements, be it spaceflight, ground-studies, or field assessments.

对于执行长时间太空飞行任务的宇航员来说，精神表现下降是一种风险，目前正在研究非侵入性、不引人注目的对策。使用非侵入性脑刺激（NiBS）技术诱导神经调节可能是刺激神经过程的一种有用且安全的对策方法，但迄今为止尚未进行有前途的技术综合。本研究评估了四种NiBS技术：经颅电刺激（tES）、经颅磁刺激（TMS）、经颅光生物调节（tPBM）和随机共振（SR）。我们确定了每种技术最有希望的属性，以提高人类的表现，同时展示了在航天环境中管理的能力。评估对每项技术在与支持人类表现和心理健康有关的三个变量以及与机组人员和任务执行有关的三个变量进行评分。这一分析表明，单独的NiBS技术可以更好地处理这些特定的变量。然而，所评估的技术目前都没有在空间中得到证实。目前尚不清楚太空飞行环境是否会影响大脑及其神经机制，从而影响其与NiBS技术的相互作用。我们建议继续投资以解决这些限制。此外，本文中评估紧急医疗对策的方法可以应用于其他技术，并针对具体的任务需求，无论是航天、地面研究还是实地评估。

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引用次数: 0

Tunable predefined-time trajectory tracking control for cable-driven space manipulators using extended state observer via fully-actuated system approaches 基于扩展状态观测器的全驱动索驱动空间机械臂可调时间轨迹跟踪控制

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.02.003

Xiangxiang Zou, Ruinan Chen, Yu Liu, Deshan Meng, Hui-Jie Sun

引用次数: 0

Advances in satellite thermal management systems: Challenges, innovations, and future directions 卫星热管理系统的进展：挑战、创新和未来方向

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

Acta Astronautica

Pub Date : 2026-02-05 DOI: 10.1016/j.actaastro.2026.02.002

Shaik Zaidaan , Ziyad Mulla , Ruaa Nakkar , Izhar Ullah , Abrar H. Baluch , Naef A.A. Qasem

Effective thermal management is a cornerstone of satellite functionality, ensuring reliability and operational success in extreme space environments. This study comprehensively reviews the state-of-the-art in satellite thermal management systems, encompassing both passive and active techniques. Passive systems, including multilayer insulation (MLI), thermal coatings, and phase-change materials (PCMs), offer energy efficiency and reliability for baseline thermal regulation. Conversely, active systems, such as heat pipes, loop heat pipes (LHPs), and mechanically pumped fluid loops (MPFLs), provide dynamic adaptability to manage high-power loads and fluctuating environmental conditions. The paper also explores recent advancements in thermal management, such as smart materials, variable-emittance coatings, and hybrid systems that combine the benefits of both passive and active approaches. Furthermore, the integration of computational techniques, such as the finite element method (FEM) and computational fluid dynamics (CFD), has significantly enhanced the prediction of thermal performance. Experimental validation through thermal-vacuum testing is also discussed as a critical step in refining and ensuring the accuracy of these systems. By integrating advances in materials, technologies, and modeling methods, this review highlights emerging trends and challenges in satellite thermal management. The findings underline the importance of hybrid systems, material innovations, and computational modeling in addressing the evolving demands of next-generation satellite missions. Future directions are proposed to guide continued research and development in this vital area of aerospace engineering.

有效的热管理是卫星功能的基石，确保在极端空间环境下的可靠性和运行成功。本研究全面回顾了卫星热管理系统的最新技术，包括被动和主动技术。被动系统，包括多层绝缘（MLI）、热涂层和相变材料（pcm），为基线热调节提供了能源效率和可靠性。相反，主动系统，如热管、环路热管（lhp）和机械泵送流体环路（mpfl），提供动态适应性，以管理高功率负载和波动的环境条件。本文还探讨了热管理方面的最新进展，如智能材料、变发射度涂层和结合被动和主动方法优点的混合系统。此外，计算技术，如有限元法（FEM）和计算流体力学（CFD）的集成，大大提高了热性能的预测。通过热真空测试进行实验验证是完善和确保这些系统精度的关键步骤。通过综合材料、技术和建模方法的进步，本综述强调了卫星热管理的新趋势和挑战。研究结果强调了混合系统、材料创新和计算建模在解决下一代卫星任务不断变化的需求中的重要性。提出了未来的发展方向，以指导航空航天工程这一重要领域的持续研究和发展。

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引用次数: 0

On the analytical study and convergence properties of state-dependent linearization of the CR3BP in the cislunar region 顺月区域CR3BP状态相关线性化的解析研究及其收敛性

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

Acta Astronautica

Pub Date : 2026-02-04 DOI: 10.1016/j.actaastro.2026.02.004

Salvatore Rea , Riccardo Bevilacqua , Emanuela Gaglio

This work characterizes linearized CR3BP propagation accuracy in the cislunar region through convergence analysis and Monte Carlo robustness assessment over hundreds of initial conditions. Results quantify order error scaling with timestep, identify phase-space regions where linearization remains valid, and provide practical guidelines for relinearization cadence selection in Earth–Moon mission design.

这项工作通过收敛分析和蒙特卡罗鲁棒性评估数百个初始条件来表征顺月区域线性化的CR3BP传播精度。结果量化了时间步长阶误差缩放，确定了线性化仍然有效的相空间区域，并为地月任务设计中线性化节奏选择提供了实用指导。

引用次数: 0

Improved space target detection and tracking via enhanced spatiotemporal representation 通过增强时空表征改进空间目标检测和跟踪

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

Acta Astronautica

Pub Date : 2026-02-03 DOI: 10.1016/j.actaastro.2026.01.027

Han Wang, Siyang Chen, Zhihua Shen, Tongsu Zhang, Guoyi Zhang, Xiaohu Zhang, Bin Lin, James A. Blake, Xia Yang

引用次数: 0

Spacecraft pursuit-evasion game with incomplete information: A pre-training approximate dynamic programming method 不完全信息航天器追逃博弈：一种预训练近似动态规划方法

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

Acta Astronautica

Pub Date : 2026-02-03 DOI: 10.1016/j.actaastro.2026.01.071

Jiancheng Zhang, Yidi Wang, Wei Zheng, Meijiao Zhao

This paper investigates a synchronous near-optimal control strategy for continuous-time spacecraft pursuit-evasion (PE) games subject to actuator saturation and incomplete information regarding the evader’s control weights. First, the evader’s unknown control weight parameters are identified online using a saturation-aware estimator, enabling real-time information acquisition by the pursuer. Second, to compute the synchronous control laws, a pre-training approximate dynamic programming (ADP) framework is proposed, which integrates offline neural network-based (NN-based) value function initialization with online iterative correction to approximately solve the Hamilton–Jacobi–Isaacs (HJI) equation. Furthermore, the sufficient conditions for the uniform ultimate boundedness (UUB) of the PE game system are analyzed via Lyapunov analysis. Finally, numerical simulations validate the effectiveness and robustness of the proposed method.

研究了在执行器饱和和逃避器控制权信息不完全的情况下，连续时间航天器追逃博弈的同步近最优控制策略。首先，利用饱和感知估计器在线识别逃避器的未知控制权参数，使跟踪器能够实时获取信息。其次，为了计算同步控制律，提出了一种预训练近似动态规划（ADP）框架，该框架将基于离线神经网络（nn）的值函数初始化与在线迭代修正相结合，近似求解Hamilton-Jacobi-Isaacs （HJI）方程。进一步，利用李亚普诺夫分析，分析了PE博弈系统一致最终有界性的充分条件。最后，通过数值仿真验证了该方法的有效性和鲁棒性。

引用次数: 0

Trajectory planning for cooperative on-orbit inspection over multiple waypoints 多航路点协同在轨巡检的轨迹规划

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

Acta Astronautica

Pub Date : 2026-02-03 DOI: 10.1016/j.actaastro.2026.01.056

Huida Yan, Li Yuan, Chuanjiang Li, Yanning Guo, Renjian Hao, Guangtao Ran

引用次数: 0

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