Acta Astronautica最新文献_第7页

The impact of actual and simulated space conditions on the gut microbiome and the modulatory role of nutrition: A systematic review and meta-analysis 实际和模拟空间条件对肠道微生物群的影响以及营养的调节作用：系统综述和荟萃分析

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

Acta Astronautica

Pub Date : 2026-01-14 DOI: 10.1016/j.actaastro.2026.01.006

Makreli Maria-Eleni, Charidemou Evelina

Purpose

This study aimed to evaluate the effects of spaceflight and simulated space environments on the human gut microbiome by examining also the role of nutrition as a modulator in these alterations.

Methods

Relevant studies were identified through searches of PubMed, PubMed Central and Scopus from 2000 through July 10, 2025. Alterations to gut microbial diversity, the Firmicutes-to-Bacteroidetes (F/B) ratio, and other physiological values were reported. Statistically significant fluctuations in gut microbial composition were collected as mean differences and standard deviations and statistically analysed with 95 % confidence intervals (CI) using SPSS. Heterogeneity was assessed using the I² statistic. The link between these changes and other confounding factors was statistically evaluated.

Results

15 studies were included, with 3 being actual spaceflights and 12 being space environment simulations. 6 out of the 11 studies that examined gut microbial diversity were included in the meta-analysis, and they presented a non-statistically significant trend toward increased diversity during the control phase (Hedges' g: −0.05, p = 0.84). The environment appeared to influence the observed alterations, with actual spaceflights having a greater impact (Hedges' g: 0.58, p = 0.19). Nutritional strategies, particularly those rich in fiber, probiotics, and vitamin D, were linked with stabilised or improved microbiome diversity, in contrast to ultra-processed foods (UPFs).

Conclusion

Overall, the findings suggest a negative effect of space conditions on gut microbial diversity, along with an adaptive microbiome response, with targeted nutritional interventions being promising in preserving gut health. Further research is needed to develop effective countermeasures that can be applied in both space and on Earth.

Systematic review registration

https://www.crd.york.ac.uk/PROSPERO/, identifier CRD420251068366.

目的本研究旨在评估太空飞行和模拟太空环境对人类肠道微生物组的影响，并研究营养在这些变化中的调节作用。方法通过PubMed、PubMed Central和Scopus检索2000年至2025年7月10日的相关研究。报告了肠道微生物多样性、厚壁菌与拟杆菌（F/B）比和其他生理值的变化。收集具有统计学意义的肠道微生物组成波动作为平均差异和标准差，并使用SPSS以95%置信区间（CI）进行统计分析。采用I2统计量评估异质性。这些变化与其他混杂因素之间的联系进行了统计评估。结果共纳入15项研究，其中3项为实际航天飞行，12项为空间环境模拟。研究肠道微生物多样性的11项研究中有6项纳入了荟萃分析，它们在对照阶段呈现出多样性增加的非统计显著趋势（Hedges的g: - 0.05, p = 0.84）。环境似乎对观测到的变化有影响，实际的航天飞行的影响更大（赫奇斯系数：0.58,p = 0.19）。与超加工食品（upf）相比，营养策略，特别是富含纤维、益生菌和维生素D的营养策略，与稳定或改善的微生物群多样性有关。总体而言，研究结果表明，空间条件对肠道微生物多样性以及适应性微生物组反应有负面影响，有针对性的营养干预有望保持肠道健康。需要进一步研究制定可在空间和地球上都适用的有效对策。系统评价注册https://www.crd.york.ac.uk/PROSPERO/，标识符CRD420251068366。

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引用次数: 0

From terrestrial basalt to customizable lunar regolith simulant: Preparation via thermal phase-tailoring 从陆地玄武岩到可定制的月球风化模拟物：通过热相位裁剪制备

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

Acta Astronautica

Pub Date : 2026-01-13 DOI: 10.1016/j.actaastro.2025.12.051

Rui Wang, Guofu Qiao

The advancement of In-Situ Resource Utilization (ISRU) technologies necessitates the development of lunar regolith simulants (LRS) that accurately reflect the chemical composition of natural lunar materials, while allowing for research on mineral composition disparities. Current methods for producing LRS mostly involve mechanically mixing different terrestrial counterparts. However, the mineral phase compositions in these LRS remain as a result rather than as refined objects. It restricts the clarity of the minimal composition variation's effect on ISRU processes involving multiple physical chemistry reactions. This study introduces a new method for preparing and programming LRS by thermal phase-tailoring a single type of terrestrial basalt simulant. The approach involves controlled melting, amorphization, and recrystallization cycles. It focuses on programming the primary mineral phase abundances in LRS materials, including plagioclase, pyroxene, olivine, and glass. A proposed nonlinear programming model identified the best blending ratios of these thermally treated products. The mineralogy's fitness matched the specific lunar regolith data from Apollo 67,701 and CE5C0600. The customized simulants replicated the mineral intergrowth textures observed in natural basalt. The spectral reflection features highly correlate with the corresponding nature of lunar regolith data. Additionally, the integrated solar absorptivity of the customized LRS was within 4 % of natural regolith samples. The melting temperatures of these simulants are also much closer to those of natural lunar samples compared to the original basalt material. This work highlights the effectiveness of controlling mineral phases through thermal processing. It provides a reliable approach for developing composition designability and high-thermal-physical fidelity LRS. These advancements are crucial for ground-researching ISRU technologies that depend on accurate optical and thermal properties, including sintering and solar manufacturing applications.

原位资源利用（ISRU）技术的进步要求开发准确反映天然月球物质化学成分的月球风化模拟物（LRS），同时允许对矿物成分差异进行研究。目前生产LRS的方法主要是机械混合不同的地面对应物。然而，这些LRS中的矿物相组成仍然是结果，而不是精炼的物体。它限制了最小组成变化对涉及多个物理化学反应的ISRU过程的影响的清晰度。本文介绍了一种采用热相位裁剪的方法对单一陆相玄武岩模拟物进行LRS制备和编程的新方法。该方法包括控制熔融、非晶化和再结晶循环。它侧重于编程LRS材料中的主要矿物相丰度，包括斜长石，辉石，橄榄石和玻璃。提出了一种非线性规划模型，确定了这些热处理产品的最佳混合比例。矿物学的适应性与阿波罗67,701和CE5C0600的特定月球风化数据相匹配。定制的模拟物复制了在天然玄武岩中观察到的矿物共生结构。光谱反射特征与月壤数据的相应性质高度相关。此外，定制LRS的综合太阳吸收率在天然风化土样品的4%以内。与原始玄武岩材料相比，这些模拟物的熔化温度也更接近自然月球样品的熔化温度。这项工作突出了通过热处理控制矿物相的有效性。它为开发具有可设计性和高热物理保真度的LRS提供了可靠的方法。这些进步对于地面研究ISRU技术至关重要，这些技术依赖于精确的光学和热性能，包括烧结和太阳能制造应用。

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引用次数: 0

Performance design and optimization for 100 kWe space nuclear power system: A review 100千瓦空间核动力系统性能设计与优化综述

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

Acta Astronautica

Pub Date : 2026-01-13 DOI: 10.1016/j.actaastro.2026.01.026

Baihui Jiang , Yu Ji , Jun Sun , Yingjie Wu , Lei Shi

The demand for high power and long lifetime energy systems in space exploration, crewed missions, and orbital infrastructure necessitates nuclear space power systems beyond the capabilities of conventional chemical or photovoltaic sources. Among candidate technical pathways, helium–xenon mixture cooled reactors coupled with closed Brayton cycles exhibit significant advantages in energy conversion efficiency, specific power, and structural compactness. Compared to terrestrial nuclear systems, system optimization in space applications presents more stringent trade-offs due to power output requirements, mass sensitivity, and difficulty of maintenance. This work reviews the current state of performance optimization for space nuclear power systems, including redundancy architectures, bleeding flow schemes, and system-level optimization methodologies targeting thermodynamic efficiency, total mass, and system reliability. Future research suggestions include high-fidelity multidisciplinary modeling, integrated full-lifetime optimization, and effective multi-objective optimization approaches. The development of optimization frameworks and methods is expected to accelerate the development of efficient, lightweight, and reliable space nuclear power systems, enabling the future high power space missions.

空间探索、载人任务和轨道基础设施对高功率和长寿命能源系统的需求需要超越传统化学或光伏源能力的核空间动力系统。在候选的技术路径中，氦-氙混合冷却反应堆与封闭布雷顿循环耦合在能量转换效率、比功率和结构紧凑性方面具有显著的优势。与地面核系统相比，由于功率输出要求、质量灵敏度和维护难度，空间应用中的系统优化提出了更严格的权衡。这项工作回顾了目前空间核动力系统性能优化的现状，包括冗余架构、放血流程方案和针对热力学效率、总质量和系统可靠性的系统级优化方法。未来的研究建议包括高保真多学科建模、集成全寿命优化和有效的多目标优化方法。优化框架和方法的发展有望加速高效、轻量化和可靠的空间核动力系统的发展，使未来的高功率空间任务成为可能。

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引用次数: 0

Propellantless space exploration 无推进剂太空探索

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.024

Roman Ya. Kezerashvili

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.

Gravitational assist uses planetary gravity to change a spacecraft’s speed and direction without fuel. It is effective but limited to specific alignments.

Solar sails 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.

Magnetic sails 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.

Electric sails 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.

Lastly, quantum effects, such as the Casimir force, offer a speculative but intriguing route to propellantless propulsion based on the vacuum energy of space.

无推进剂推进是指不需要机载推进剂，而是依靠自然力或外部能源的太空旅行方法。在本文中，我回顾了已经探索的不同方法，并讨论了每种方法在星际空间探索中的利弊。重力辅助利用行星引力来改变航天器的速度和方向，而不需要燃料。它是有效的，但仅限于特定的对齐。太阳帆利用太阳光的辐射压力来实现连续的、无燃料的加速。虽然随着时间的推移而有效，但它们需要在空间中降解的大型反射材料。太阳辐射引发的热解吸可以提高速度。磁帆通过超导环与太阳风相互作用，产生磁场，从而产生推力。与太阳帆相比，它们提供的加速度更低，而且它们的性能取决于可用功率和太阳风条件的可变性。电动帆利用带电系绳排斥太阳风质子，产生逐渐加速。它们的有效性取决于成功部署非常长，重量轻的导电导线。它们可以获得比太阳帆更高的加速度，它们的性能受到可用功率和太阳风条件的影响。最后，量子效应，如卡西米尔力，为基于空间真空能的无推进剂推进提供了一条推测性但有趣的途径。

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引用次数: 0

Overall results of the SMPAG work package on mission scenarios definition in response to the 2025 Planetary Defense Conference Hypothetical Asteroid Impact Threat Scenario 为响应2025年行星防御会议假想小行星撞击威胁情景，SMPAG任务情景定义工作包的总体结果

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.023

Juan L. Cano , Michael Khan , Camilla Colombo , Massimiliano Vasile , Richard Moissl , Detlef Koschny

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.

空间任务规划咨询小组（SMPAG）成员于2041年4月24日对一颗有撞击机会的中型小行星进行了一次小行星撞击模拟演习，为2025年行星防御会议做准备。这项工作分为两个不同的模拟阶段，分别为两个半月和四个月。在第一个时期，纪元1，小行星撞击概率从1.6%增长到10%，并且是实时播放的。在2024年10月10日举行的SMPAG全体会议上，对需要实施的必要行动进行了初步评估，并提出了一套建议。Epoch 2是在小行星于2028年4月快速飞越侦察任务后模拟的，这使得小行星的大小和撞击位置得以改进。对需要作出的决定和可行的特派团备选办法进行了评估，以便于管理小组全体会议提出建议。在权衡多种偏转任务策略的基础上，选择了动力撞击器、离子束偏转和核爆炸装置。

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引用次数: 0

Real-time discovery of near-earth objects via accelerated image analysis with AI methods 利用人工智能方法加速图像分析，实时发现近地天体

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.019

Szabolcs Velkei , László L. Kiss , Károly Vass , Norton O. Szabó , Krisztián Sárneczky

Konkoly Observatory is conducting the most successful NEO survey project in Europe with a total number of NEOs found in the past four years in excess of 250, with three imminent impactors discovered between 2022 and 2024. Recently, supported by the European Space Agency, we started the implementation of a new search technique that is using machine learning algorithms to accelerate real-time image analysis with the scope of finding extreme trailed images of the smallest and nearest NEOs passing by. We have created a custom deep-learning model that was trained on a large dataset of astronomical images and their associated annotations. In addition to the real observations from the Piszkéstető Mountain Station of the Konkoly Observatory, we have also created a huge synthetic photorealistic training dataset to improve the precision and accuracy of the neural network. As a result, the model successfully learnt to recognize patterns and features in the images that are indicative of NEOs and space debris. The main goal was to have an optimized deep learning model to perform this analysis in real-time, providing quick and reliable detection that is made possible by the AI-based robust image-artifact decomposition for false positive suppression. The outcome of this project is a service that can quickly and accurately detect NEOs and space debris on astronomical images, potentially increasing the number of discoveries and improving the speed and reliability of the discovery process. The system has been evaluated using a set of rigorous tests and is benchmarked against existing methods. We provide valuable insights into the feasibility of using deep learning techniques for this type of image analysis problem and will lay the groundwork for future work in this field.

Konkoly天文台正在进行欧洲最成功的近地天体调查项目，在过去四年中发现的近地天体总数超过250个，在2022年至2024年间发现了三个即将到来的撞击天体。最近，在欧洲航天局的支持下，我们开始实施一项新的搜索技术，该技术使用机器学习算法来加速实时图像分析，以找到最小和最近的近地天体经过的极端尾随图像。我们创建了一个定制的深度学习模型，该模型是在天文图像及其相关注释的大型数据集上进行训练的。除了Konkoly天文台piszksamustetje山站的真实观测数据外，我们还创建了一个巨大的合成真实感训练数据集，以提高神经网络的精度和准确性。结果，该模型成功地学会了识别图像中的模式和特征，这些模式和特征表明是近地天体和空间碎片。主要目标是拥有一个优化的深度学习模型来实时执行此分析，通过基于人工智能的鲁棒图像伪影分解来实现快速可靠的检测，以抑制误报。该项目的成果是一项服务，可以快速准确地检测天文图像上的近地天体和空间碎片，有可能增加发现的数量，提高发现过程的速度和可靠性。该系统已通过一系列严格的测试进行了评估，并与现有方法进行了基准测试。我们为使用深度学习技术解决这类图像分析问题的可行性提供了有价值的见解，并将为该领域的未来工作奠定基础。

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引用次数: 0

The behavior of sulfur regolith concrete under micrometeoroid impacts for lunar surface structures 月球表面结构在微流星体撞击下硫风化层混凝土的行为

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.005

Hamed Seifamiri , Antonio Bobet , Ramesh Malla , Pooneh Maghoul

The need to reduce launch payload, which is critical for sustainable lunar missions and long-term surface operations, has driven the development of in-situ resource utilization (ISRU) materials. Sulfur-based regolith concrete (SRC), produced by mixing lunar regolith with sulfur as a binder, has emerged as a promising ISRU-based construction material. However, lunar structures remain vulnerable to micrometeoroid hypervelocity impacts (HVI), which can cause severe structural damage. In this study, a calibrated Johnson–Holmquist II (JH-2) constitutive model was parameterized for SRC using numerical simulations in Abaqus/Explicit across a range of impact conditions, including varying projectile sizes, velocities, and angles. The model parameters were determined through a detailed calibration process, synthesizing experimental data from similar brittle materials to capture the strength, damage, and equation-of-state (EOS) behavior of SRC within the available validation envelope. Additionally, a sensitivity analysis was conducted to identify critical material properties (such as compressive strength, density, and Hugoniot Elastic Limit) that significantly influence impact resistance. Simulation results demonstrated good agreement with experimental crater dimensions and damage morphologies for the available SRC benchmark condition. The predicted crater-depth trends were further benchmarked against classical strength-regime

π

-group scaling to contextualize extrapolation beyond the available experimental conditions. The resulting framework supports design-oriented assessment of SRC crater geometry and damage under a broader set of HVI scenarios, while highlighting the need for additional SRC impact benchmarks at higher velocities and oblique incidence. Findings from this study provide quantitative guidance for designing resilient lunar infrastructure capable of withstanding micrometeoroid bombardment.

减少发射有效载荷的需求对可持续的月球任务和长期的地面作业至关重要，这推动了原位资源利用（ISRU）材料的发展。硫基风化层混凝土（SRC）是由月球风化层与硫作为粘合剂混合而成的，已经成为一种很有前途的isru基建筑材料。然而，月球结构仍然容易受到微流星体超高速撞击（HVI）的影响，这可能导致严重的结构损坏。在本研究中，使用Abaqus/Explicit进行了一系列冲击条件（包括不同的弹丸尺寸、速度和角度）的数值模拟，对校正后的Johnson-Holmquist II （JH-2）本构模型进行了参数化。模型参数是通过详细的校准过程确定的，综合了类似脆性材料的实验数据，以在可用的验证范围内捕获SRC的强度、损伤和状态方程（EOS）行为。此外，还进行了敏感性分析，以确定显著影响抗冲击性的关键材料特性（如抗压强度、密度和Hugoniot弹性极限）。模拟结果表明，在现有的SRC基准条件下，弹坑尺寸和损伤形态与实验结果吻合较好。预测的弹坑深度趋势进一步以经典强度-制度π-群标度为基准，以便在现有实验条件之外进行外推。由此产生的框架支持在更广泛的HVI场景下以设计为导向的SRC撞击坑几何形状和损伤评估，同时强调需要在更高速度和斜入射下进行额外的SRC撞击基准测试。这项研究的发现为设计能够承受微流星体轰击的弹性月球基础设施提供了定量指导。

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引用次数: 0

A double-layer sensing system combining thin-film resistor and acoustic emission networks towards an in situ real-time quantitative monitoring of hypervelocity impact 一种结合薄膜电阻和声发射网络的双层传感系统，用于超高速撞击的现场实时定量监测

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.025

Pinliang Zhang , Qian Yu , Qiang Wu , Jilong Peng , Jingtai Li , Shun Lu , Menglong Liu , Junfeng Wang , Yu Jiang , Rong Song

Massive orbital debris consisting of remnants from previous missions orbit the Earth. The acquisition of data pertaining to the orbital debris is of paramount importance for the development and validation of debris environment models. In this study, a novel in situ real-time quantitative hybrid perception method for hypervelocity impact (HVI) from space debris is proposed, integrating a thin-film resistive grid with acoustic emission (AE) technology. The thin-film resistive grid is fabricated by etching a cross-shaped array of micrometer-scale resistive wires on the respective sides of a polyimide film. In the event of the film being penetrated by debris and the resistive wires being broken, the electrical resistance status of the wires can then be used to determine the location and size of the debris. Following the penetration of the thin-film layer, the debris strike a second aluminum plate equipped with an AE sensor array. The arrival times of the acoustic signals are processed using a hyperbolic localization algorithm to determine the HVI location. By correlating the time and location data from both layers, the velocity and direction of HVI can be derived. This facilitates the quantitative perception of multiple debris parameters. Then, the HVI numerical simulations, which combine smooth particle hydrodynamics and finite element method, are performed to validate the effectiveness of the proposed perception approach. Finally, a physical prototype of the in situ debris detector is developed for experimental validation. Two ground-based two-stage light gas guns are used to propel several projectiles with diameters ranging from hundreds of micrometers to several millimeters. The average absolute errors for the three tested cases are 0.10 km/s for the projectile velocity, 1.0° for the impact angle, and 0.30 cm for the HVI location at the aluminum plate, demonstrating the effectiveness for multi-parameter perception of space debris.

大量的轨道碎片由以前的任务遗留下来的地球轨道碎片组成。获取有关轨道碎片的数据对于制定和验证碎片环境模型至关重要。本文提出了一种结合薄膜电阻网格和声发射技术的空间碎片超高速碰撞（HVI）原位实时定量混合感知方法。薄膜电阻栅格是通过在聚酰亚胺薄膜的各自侧面蚀刻一个微米级电阻线的十字形阵列来制造的。在薄膜被碎片穿透和电阻导线被折断的情况下，导线的电阻状态可以用来确定碎片的位置和大小。穿透薄膜层后，碎片撞击装有声发射传感器阵列的第二个铝板。使用双曲定位算法处理声信号的到达时间以确定HVI的位置。通过将两层的时间和位置数据相关联，可以推导出HVI的速度和方向。这有助于对多个碎片参数的定量感知。然后，结合光滑颗粒流体力学和有限元方法进行了HVI数值模拟，验证了所提感知方法的有效性。最后，研制了原位碎片探测器的物理样机，进行了实验验证。两个地面两级轻型气枪用于推进几个直径从几百微米到几毫米不等的弹丸。3个测试案例的平均绝对误差分别为：弹丸速度0.10 km/s、冲击角1.0 km/s、铝板处HVI位置0.30 cm，验证了该方法对空间碎片多参数感知的有效性。

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引用次数: 0

Launch window design for crewed lunar mission with lunar orbit rendezvous and two launches 月球轨道交会和两次发射的载人月球任务发射窗口设计

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

Acta Astronautica

Pub Date : 2026-01-12 DOI: 10.1016/j.actaastro.2026.01.020

Tianshan Dong , Xiaobing Ma , Wenyan Zhou , Lin Lu

Lunar Orbit Rendezvous (LOR) is a crucial mode for crewed lunar missions. Unlike the Apollo mission, a variant of LOR involving two launches and the assembly of modules in lunar orbit has emerged as a notable pattern in recent lunar return missions. This paper presents a methodology for determining the launch window of a crewed lunar mission using LOR with two launches. First, nominal launch windows are defined by constructing its calculation model based on the flight scheme and integrated launch windows are introduced considering a delay strategy. Second, a method for determining nominal launch windows based on mission geometry is proposed, which solves the nominal launch window in a tiered analytical process by constraints’ temporal geometry. Finally, the integrated launch windows are first estimated by orbital plane matching and then solved by introducing virtual planes. Numerical simulations for nominal launch windows and integrated launch windows validate the proposed method and the satisfaction of the constraints. The methodology offers a systematic solution to the launch window for crewed lunar missions with lunar orbit rendezvous and two launches and addresses the integrated launch window for spacecraft under a complex delay strategy.

月球轨道交会（LOR）是载人登月任务的关键模式。与阿波罗任务不同，在最近的月球返回任务中，一种涉及两次发射和在月球轨道上组装模块的LOR变体已成为一种引人注目的模式。本文提出了一种利用二次发射的LOR确定载人探月任务发射窗口的方法。首先，基于飞行方案构建了标称发射窗口的计算模型，定义了标称发射窗口，并考虑延迟策略引入了综合发射窗口。其次，提出了一种基于任务几何的公称发射窗口确定方法，利用约束条件的时间几何特征分层解析求解公称发射窗口；最后，首先通过轨道平面匹配估计综合发射窗口，然后引入虚拟平面求解。对标称发射窗口和集成发射窗口的数值仿真验证了所提方法的有效性和约束条件的满足性。该方法系统地解决了载人月轨交会两次发射任务的发射窗口问题，解决了复杂延迟策略下航天器的综合发射窗口问题。

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引用次数: 0

Fly me to the moon: Family conferencing with communication delays on lunar missions 带我去月球：月球任务中通信延迟的家庭会议

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

Acta Astronautica

Pub Date : 2026-01-10 DOI: 10.1016/j.actaastro.2026.01.022

Sheena I. Dev , Nikole D. Moody , Diana P. Arias , Suzanne T. Bell

Background

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.

Methods

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.

Results

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.

Conclusion

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.

目前国际空间站上的宇航员已经安排了时间，通过虚拟音频和视频私人家庭会议（pfc）与家人联系。然而，在月球任务期间，单向通信延迟预计在4到12秒之间，这对迄今为止一直使用实时通信的pfc来说是一个重大的范式转变。本研究的目的是确定月球通信延迟对类宇航员参与者及其家属的pfc预期收益的影响。方法招募了35名主要参与者，以接近德克萨斯州休斯顿美国宇航局约翰逊航天中心的宇航员人口统计数据。他们被要求找到一个住在休斯敦以外的家庭成员作为他们的研究伙伴。每对研究对象在0、4、6、8、10或12秒的单向延迟下，每周参加6次虚拟视听PFC会话。在每次PFC之前和之后评估关系和个人幸福感结果。在每次PFC之后，根据实施的延迟评估沟通质量。有计划对比的线性混合模型检验了每个PFC对关系、个人幸福感和沟通质量的影响。结果与基线相比，无论延迟与否，spfcs均可改善关系结果。与没有延迟的pfc相比，单向延迟8秒或更长时间的pfc对人际关系和个人幸福感的影响更大。参与者还表示，所有延迟大大降低了他们的通信质量，如果要求他们在这些条件下继续通信六个月，将影响他们的关系。结论pfc有利于航天员类家庭之间的异地关系。虽然在这个时间有限的实验室环境中，参与者通常可以容忍较短的通信延迟，但我们的研究结果表明，通信延迟的pfc，特别是8秒或更长时间，可能不足以在未来的长期月球任务中维持家庭联系。这些发现强调了在太空飞行期间保持与家人和朋友联系的重要性，并为制定创新解决方案提供了基础，以便在沟通障碍的情况下保持联系。

{"title":"Fly me to the moon: Family conferencing with communication delays on lunar missions","authors":"Sheena I. Dev , Nikole D. Moody , Diana P. Arias , 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":"2026-01-10","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}

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