Acta Astronautica最新文献

{"title":"Satellite surface charging in LEO with ProPIC","authors":"Simone Di Fede ,&nbsp;Basman Elhadidi ,&nbsp;Mirko Magarotto ,&nbsp;Wai Lee Chan","doi":"10.1016/j.actaastro.2024.10.057","DOIUrl":"10.1016/j.actaastro.2024.10.057","url":null,"abstract":"<div><div>ProPIC is a fully kinetic particle-in-cell (PIC) solver developed for space electric propulsion. This work has extended its capabilities to simulate satellite surface charging and wake generation in low Earth orbit (LEO). A novel scaling approach has been implemented, decreasing computational cost by more than one order of magnitude. The methodology and scaling approach have been verified against the revised orbital-motion-limited theory. The surface charging and wake generation in LEO have been examined for a satellite that is more complex and larger than what is typically handled with a fully kinetic PIC approach in LEO, particularly due to the presence of large solar panels. Notably, the simulated wake can be used to identify the optimal position for the plasma diagnostic sensor that minimizes interference with the wake. Moreover, despite not being a failure risk, the attitude greatly influences the surface charging of a satellite with large solar arrays installed parallel to the satellite speed vector. The study suggests that, for high positive pitch angles (<span><math><mo>&gt;</mo></math></span>45<span><math><msup><mrow></mrow><mrow><mo>∘</mo></mrow></msup></math></span>), the surface charging of the solar panels can increase by as much as 75% compared to low negative pitching cases. Additionally, the study highlights that the pitch angle and satellite envelope along the motion direction significantly influence the potential gradients on the solar panels.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 458-468"},"PeriodicalIF":3.1,"publicationDate":"2024-10-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142578640","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":"Martian buildings: Feasible cement/concrete for onsite sustainable construction from the structural point of view","authors":"Omid Karimzade Soureshjani,&nbsp;Ali Massumi,&nbsp;Gholamreza Nouri","doi":"10.1016/j.actaastro.2024.10.056","DOIUrl":"10.1016/j.actaastro.2024.10.056","url":null,"abstract":"<div><div>Colonizing other planets, like Mars, marks a significant milestone in the pursuit of a multi-planetary existence. Millions of people would settle on Mars in self-sufficient bases. Colonizing Mars is a long-term mission that demands self-sufficient, secure habitats and comprehensive planning. Importing structures, such as inflatable structures, from Earth is cost-prohibitive, making the utilization of in-situ resources and onsite construction the most viable approach for preparing the required buildings. Studies have shown that it is possible to produce and craft several kinds of binders and concretes with appropriate mechanical behavior using Martian soil composition; however, determining the optimal option for onsite construction remains a challenge. This study investigates available cement/concrete options for onsite construction on Mars from a structural engineering perspective, taking into account the available resources and technologies. In this regard, the observations and data provided by Martian landers, rovers, orbiters and methods such as Viking-1 &amp; 2, Pathfinder, Spirit, Opportunity, Curiosity, Mars Express, Ultraviolet–visible/Near-infrared reflectivity spectra and Alpha particle X-ray spectrometer were used to obtain a comprehensive and detailed investigation. Eleven types of Martian cement/concrete based on the in-situ resources, soil composition, and available technologies were compared based on the criteria and indices defined in accordance with the structural engineering point of view to select the best practical option for onsite construction. These criteria encompass factors such as mechanical behavior, Martian structural loads, raw material accessibility, available sources, energy required for production, water requirement, curing and hardening time, possibility of using 3D printers, byproduct usefulness, conditions required for hardening and curing, importation requirements from Earth, production complexity, long-term durability and behavior under galactic cosmic rays (GCRs) and solar energetic particles (SEPs). The pros and cons of each cement/concrete option are thoroughly assessed, considering the harsh conditions on Mars. Additionally, the study highlights extra considerations that are crucial for onsite construction on Mars. To determine the best practical option for onsite construction and sustainable colonization, the proposed cements/concretes were compared using multi-scale spider/radar diagrams and a quantitative point of view. This perspective was enabled by assigning weights to each criterion through expert consultation, experimental data, and literature review, ensuring that the diagrams accurately reflect the features of each concrete mix. This comprehensive investigation aims to provide valuable insights into selecting the most suitable cement/concrete for onsite construction on Mars, considering the structural engineering perspective and the long-term goal of sustainable colonization.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 494-520"},"PeriodicalIF":3.1,"publicationDate":"2024-10-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142587324","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":"Exploring potential candidates of alternative solid hydrocarbon propellants for cold-gas thrusters","authors":"Thimthana Lee,&nbsp;Mahdi Davoodianidalik,&nbsp;Dimitrios Tsifakis,&nbsp;Roderick W. Boswell,&nbsp;Christine Charles","doi":"10.1016/j.actaastro.2024.10.047","DOIUrl":"10.1016/j.actaastro.2024.10.047","url":null,"abstract":"<div><div>Cold-gas thrusters play a vital role as a subsystem in satellite operations facilitating space maneuvers in numerous missions. Achieving optimal propulsion necessitates not only continuous development of thruster design but also an exploration of novel propellant options to enhance overall performance. While an ideal propellant remains elusive, many studies have identified alternative options to replace commonly used inert gases. Choosing a solid-state propellant offers benefits such as the absence of a pressurised tank and sloshing effect. Hydrocarbon propellants are advantageous due to their non-corrosiveness and abundance as organic compounds on Earth. The sublimation process for manipulating solid propellants typically requires only a few watts, making it suitable for low-power budget missions. This work presents five solid hydrocarbon propellants for cold-gas thrusters, three of which have not yet been experimentally explored. The comparison between various aspects, including mass flow rate, power consumption, and several key performance parameters, is discussed. The measured mass flow rate is a function of the species and temperature, following the trend of the vapour pressure. The power consumption for all propellants only depends on the required heating temperature as they share similar thermal properties. The thrust generated by each propellant is comparable and linearly proportional to the mass flow rate when the flow is choked. Specific impulse remains relatively constant across different mass flow rates due to the strong correlation between thrust and mass flow rate. The thrust-to-power ratio is generally comparable among the propellants, except hexamine, which demands more power at higher operating temperatures due to increased heat loss. Among these alternatives, camphor emerges as the most promising candidate due to its low power consumption, thrust generation, and mass efficiency. On the other hand, naphthalene offers the best in terms of its superior thrust-to-power ratio and cost-per-kilogram advantage.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 427-438"},"PeriodicalIF":3.1,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142572361","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":"Methodology for robust analysis of bolts slippage in cryogenic space missions","authors":"Alejandro Fernández-Soler ,&nbsp;Andrés García-Pérez ,&nbsp;Gianluca Morgante ,&nbsp;Javier Pérez-Álvarez ,&nbsp;Gustavo Alonso ,&nbsp;Laura García-Moreno ,&nbsp;Antonio Scippa ,&nbsp;Daniele Gottini ,&nbsp;Ciro Del Vecchio","doi":"10.1016/j.actaastro.2024.10.048","DOIUrl":"10.1016/j.actaastro.2024.10.048","url":null,"abstract":"<div><div>The assessment of slippage in cryogenic space missions is fundamental from a mechanical point of view as it is one of the main failure modes of a bolt in a mechanical interface. It is usually performed on the basis of temperature maps obtained from the worst-case thermal design cases, with particular interest in the transient case during the cooldown. Traditionally, the thermal mapping has to be transferred to the detailed FEM model. This process requires a lot of interaction between the thermal and structural disciplines, which is often not easy. Moreover, the thermal mapping usually corresponds to the instant of maximum gradient between the clamped parts along the transient case. In this paper, a new methodology is proposed to speed up the evaluation of the temperature effect on the slippage from an analytical model correlated with the FEM model. Then, the interactions between the structural and the thermal responsible may be reduced. In addition, the proposed methodology evaluates the entire temperature curve of the transient case, rather than a single instant. In this way, the thermal effect on slippage can be evaluated in a robust and agile process, facilitating the definition of requirements in terms of the maximum allowable temperature gradient as a function of preload or vice versa. This methodology has been validated with the primary mirror of the ARIEL mission, which is a cryogenic European mission that aims to study exoplanets by making observations from a thermally stable orbit at L2 point of the Sun-Earth system. Therefore, the correct design of the primary mirror is essential for the successful science observations of the mission.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 570-584"},"PeriodicalIF":3.1,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142661012","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Combination of altimetry crossovers and Doppler observables for orbit determination and geodetic parameter recovery: Application to Callisto","authors":"William Desprats ,&nbsp;Stefano Bertone ,&nbsp;Daniel Arnold ,&nbsp;Martin Lasser ,&nbsp;Adrian Jäggi ,&nbsp;Michel Blanc","doi":"10.1016/j.actaastro.2024.10.045","DOIUrl":"10.1016/j.actaastro.2024.10.045","url":null,"abstract":"<div><div>An accurate knowledge of the orientation, the tidal deformability, and the gravity field of a celestial body is fundamental to provide constraints on its internal structure. These quantities may be retrieved by processing radiometric tracking and altimetry data from a probe in orbit around such body. This paper presents a method to combine altimetry crossovers with two-way Doppler tracking observations at normal equation level, using the Bernese GNSS Software and the pyXover software library. This method was applied to a proposed 200<!--> <!-->km altitude orbiter around Callisto, a privileged destination for the upcoming phase of Solar System exploration. Enhancing “standard” Doppler tracking with altimetry generally benefited both orbit determination and a joint estimation of the orientation of the north pole and of planetary librations. The retrieval of low-degree gravity field parameters was also improved by the addition of altimetry data. However, the improvements on the estimated parameters were highly dependent on the characteristics of the simulation, e.g., the underlying topography roughness. Overall, combining radioscience with altimetry data accounted for a visible reduction of correlations among estimated parameters, while also allowing for a consistent estimation of the “vertical” Love number <span><math><msub><mrow><mi>h</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span> along with gravity.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 585-600"},"PeriodicalIF":3.1,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142660948","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A review of international best practices in integrating space launch activities with air traffic management: Guidance for future space launch in the Singapore region","authors":"Imen Dhief ,&nbsp;Zhengyi Wang ,&nbsp;Wei Zhou ,&nbsp;Sameer Alam ,&nbsp;Anouk Stahnke ,&nbsp;Lorenz Losensky ,&nbsp;Tobias Rabus ,&nbsp;Sven Kaltenhäuser","doi":"10.1016/j.actaastro.2024.10.010","DOIUrl":"10.1016/j.actaastro.2024.10.010","url":null,"abstract":"&lt;div&gt;&lt;div&gt;The integration of space-based assets into our daily lives has seen a remarkable surge, with numerous industries and sectors heavily relying on satellite communications, remote sensing, and global navigation satellite system (GNSS) technology. As space emerges as an indispensable commercial domain, several countries and private companies have actively engaged in space activities.&lt;/div&gt;&lt;div&gt;Space launch operations involve a collaborative effort among diverse stakeholders, including space agencies, space companies, the military, and aviation sectors. While space launch processes share similarities globally, each country faces unique challenges and adopts distinct mechanisms due to its specificities. Thus, initiating space launch activities requires a thorough examination of a country’s unique features. This includes assessing their impact on existing air traffic, considering safety concerns, implementing temporary restrictions, promoting communication, and mitigating operational disruptions. This is crucial as space launch trajectories intersect with established flight paths, influencing aviation operations.&lt;/div&gt;&lt;div&gt;The proposed review aims to explore the details of space launch procedures and policies by various countries, namely the United States, France, the United Kingdom, Japan, South Korea, and New Zealand. The objective is to lay a foundation for establishing future procedures and policies to integrate space launch activities with air traffic, particularly for countries that are new to this field. This is performed by examining international best practices in space launch operations, considering the unique challenges faced by countries, such as geographical location, collaboration with neighbors, and their familiarity with such operations. The examination exposes the diverse approaches and considerations involved in different stages of the space launch activity process, including the pre-mission, execution, and post-mission phases, with an emphasis on the best practices adopted to integrate space launch activities within air traffic. Furthermore, the current review paper aims to evaluate the suitability of potential future space launches initiated from the Singapore Flight Information Region (FIR). Singapore’s equatorial positioning makes it particularly favorable for such initiatives. Nevertheless, the initiation of space launch activities from the Singapore FIR raises significant concerns regarding its potential impact on the substantial volume of air traffic traversing the airspace in regions encompassing Singapore, Malaysia, and Indonesia. Moreover, considering Singapore’s recognition as a maritime hub, there are potential implications for maritime traffic. Consequently, this study discusses the potential implications of a future space launch conducted from Singapore FIR on the broader regional landscape.&lt;/div&gt;&lt;div&gt;The paper also presents guidance to effectively plan and prepare for future space-launch requirements in the Sin","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 728-759"},"PeriodicalIF":3.1,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142661018","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":"Attitude tracking of rigid-liquid-flexible coupling spacecraft by active disturbance rejection control","authors":"Xiaowei Zhang ,&nbsp;Shuang Li ,&nbsp;He Zhu ,&nbsp;Jingji Wang","doi":"10.1016/j.actaastro.2024.10.053","DOIUrl":"10.1016/j.actaastro.2024.10.053","url":null,"abstract":"<div><div>Considering the complex attitude dynamics of Rigid-Liquid-Flexible Coupling Spacecraft, especially when the large amplitude sloshing of liquid exists in rapid attitude maneuver, the conventional control design method based on the linearized model is not suitable for the significant coupling and strong nonlinearity. By contrast, Active Disturbance Rejection Control is model-independent and easy to design and implement. In this paper, the three main components of Active Disturbance Rejection Control, Tracking Differentiator, Extended State Observer and Nonlinear State Error Feedback are comprehensively applied to the attitude tracking control of Rigid-Liquid-Flexible Coupling Spacecraft. Firstly, two cascaded Tracking Differentiators are used to arrange the transition process of the attitude command, which not only reduces overshoot and oscillation of the tracking process, but also obtains the angular acceleration information of attitude trajectory for feed-forward compensation. Secondly, the total disturbance caused by liquid sloshing and flexible vibration is observed by Extended State Observer and compensated synchronously. Finally, the Nonlinear State Error Feedback is used to further improve the transient behavior and steady-state quality of the control system. The simulation results show that the tracking accuracy of the attitude and angular velocity using the Active Disturbance Rejection Control are about 3–27 times and 6 to 115 times that of the PID control, respectively. The convergence time, overshooting are also significantly less than the PID control.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 913-927"},"PeriodicalIF":3.1,"publicationDate":"2024-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702603","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":"Mesenchymal stem cell transplant as an intervention to ameliorate disuse-induced muscle atrophy in a mouse model of simulated microgravity","authors":"Rizwan Qaisar ,&nbsp;Megna Srinivas ,&nbsp;Muhammad Tehsil Gul ,&nbsp;Amir Ali Khan ,&nbsp;Anu Ranade ,&nbsp;Josemin Jose ,&nbsp;Gopika Ramachandran ,&nbsp;Suni Ebby ,&nbsp;Firdos Ahmad ,&nbsp;Asima Karim","doi":"10.1016/j.actaastro.2024.10.060","DOIUrl":"10.1016/j.actaastro.2024.10.060","url":null,"abstract":"<div><h3>Background</h3><div>The hindlimb unloaded (HU) mouse model exhibits disuse-induced muscle atrophy. However, effective interventions remain elusive. We investigated the therapeutic potential of mesenchymal stem cells (MSC) transplant on muscle decline in HU mice.</div></div><div><h3>Methods</h3><div>We divided 4-month-old male c57BL/6j mice into controls and HU mice treated with PBS as placebo (HU-PBS) or MSCs (HU-MSC; one million cells/100 μl PBS into gastrocnemius muscles once a week) for three weeks. We measured muscle mass, grip strength, and an unbiased transcriptome analysis of gastrocnemius muscles.</div></div><div><h3>Results</h3><div>MSC treatment prevented muscle atrophy and improved grip strength in HU mice. Transcriptome analysis revealed MSC-induced unique (557 genes) and differential (1214 genes) expressions of several genes compared to the HU-PBS group. GO and KEGG term analysis revealed an HU-induced downregulation of pathways associated with the regulation of contractile apparatus, neuromuscular junction, and satellite cell function, which were partly reversed with MSC treatment. Lastly, MSC treatment also upregulated the pathways controlling muscle differentiation and growth in the HU mice.</div></div><div><h3>Conclusion</h3><div>Altogether, we report the therapeutic potential of MSCs in treating disuse-induced muscle atrophy and weakness. Our study may help unravel novel molecular mechanisms involved in MSCs-induced muscle restoration.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 275-282"},"PeriodicalIF":3.1,"publicationDate":"2024-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534904","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":"Penetration based lunar regolith thermal conductivity inversion: Method and verification","authors":"Jiachen Zhu ,&nbsp;Junyue Tang ,&nbsp;Cheng Chi ,&nbsp;Junxiao Xiao ,&nbsp;Shengyuan Jiang ,&nbsp;Weiwei Zhang ,&nbsp;Zixiao Lu ,&nbsp;Ziming Chen","doi":"10.1016/j.actaastro.2024.10.030","DOIUrl":"10.1016/j.actaastro.2024.10.030","url":null,"abstract":"<div><div>Based on the temperature change data of the penetrator, to achieve in-situ detection of the thermal conductivity of the lunar regolith profile, it is necessary to establish a heat conduction model between the penetrator and the lunar regolith. This study simplifies the heat conduction model of the complex shaped penetrator through simulation analysis results. Then, we proposed a thermal conductivity inversion method based on the transient thermal cylinder source model. The thermal diffusion test was carried out under normal temperature and pressure on a standard reference object with known thermal conductivity and the thermal conductivity inversion work was completed, which verified the feasibility of the inversion method. Then, we completed the thermal diffusion test of the penetrator and the lunar regolith simulant under the simulated low-temperature vacuum environment of the lunar surface, and carried out the thermal conductivity inversion of the lunar regolith simulant based on the thermal diffusion test data, which proved that the proposed thermal inversion method is applicable for the lunar regolith under the low-temperature vacuum. Finally, the thermal conductivity test was conducted on icy lunar regolith simulant with different water contents and a thermal diffusion test in a vacuum low-temperature environment was carried out. The thermal conductivity inversion was completed using the same method, which proved that the inversion method is suitable for icy lunar regolith simulant.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 414-426"},"PeriodicalIF":3.1,"publicationDate":"2024-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142560868","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":"DIANA: An underwater analog space mission","authors":"Marek Sokol ,&nbsp;Petr Volf ,&nbsp;Jan Hejda ,&nbsp;Lydie Leová ,&nbsp;Jan Hýbl ,&nbsp;Michal Schmirler ,&nbsp;Jakub Suchý ,&nbsp;Roman Procházka ,&nbsp;Miroslav Charvát ,&nbsp;Klára Seitlová ,&nbsp;Martin Dolejš ,&nbsp;Jiří Schneider ,&nbsp;Patrik Kutílek","doi":"10.1016/j.actaastro.2024.10.044","DOIUrl":"10.1016/j.actaastro.2024.10.044","url":null,"abstract":"<div><div>The DIANA mission represents an underwater analog space mission designed to simulate and study the impact of long-duration spaceflight and extraterrestrial habitation on crew performance, psychosocial dynamics, and technological systems. The mission utilized an underwater habitat, the Hydronaut H03 DeepLab, to mimic the isolated, confined, and extreme (ICE) environment of space. Over eight days, a six-member crew lived and worked in underwater (3) and water surface (3) habitats, performing scientific experiments and operational tasks. The mission schedule encompassed a variety of activities such as drone exploration, extravehicular activities (EVAs), soil sampling, and media interactions, culminating in a simulated departure from the lunar surface. Data collection methods included continuous biomedical monitoring, cognitive task assessments, and sociomapping to analyze team communication and cooperation. This paper provides an overview of the mission architecture and outcomes, offering valuable insights into the challenges of future human space exploration and informing improvements in crew selection, training, and support systems.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 349-360"},"PeriodicalIF":3.1,"publicationDate":"2024-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142538884","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}