Acta Astronautica最新文献

{"title":"Thrust performance of pulsed-laser ablation impulses for wavelengths of 1064 nm and 532 nm","authors":"Yusuke Nakamura ,&nbsp;Kei Kikuchi ,&nbsp;Gakuto Sekine ,&nbsp;Atsushi Isomura ,&nbsp;Akihiro Sasoh ,&nbsp;Satoshi Wada ,&nbsp;Katsuhiko Tsuno ,&nbsp;Takayo Ogawa ,&nbsp;Tadanori Fukushima","doi":"10.1016/j.actaastro.2025.03.038","DOIUrl":"10.1016/j.actaastro.2025.03.038","url":null,"abstract":"<div><div>Space propulsion using pulsed-laser ablation of metals is a promising technology, particularly for deorbiting space debris or satellites at the end of life. The momentum coupling coefficient, a key parameter in this technology, depends on the incident laser wavelength. Although former studies have evaluated this dependency, they often overlooked the influence of variations in beam profiles. A method to estimate the local momentum coupling coefficient based on beam profiles was previously demonstrated using a nanosecond laser with a wavelength of 1064 nm. In this study, the local momentum coupling coefficient for a wavelength of 532 nm was estimated for the target materials of pure aluminum, extra-super duralumin, and oxygen-free copper using the same method and compared with that of the 1064 nm reported in the previous study. The comparison revealed that the local momentum coupling coefficient displays similar trends across materials for both wavelengths, except for oxygen-free copper, which exhibited a significantly higher ablation threshold for the wavelength of 1064 nm. The two important parameters for space propulsion, namely, the specific impulse and thrust efficiency, were also derived for both wavelengths based on the impulse and reduction mass of an ablation target. The specific impulse showed a weaker dependency on wavelength, with values ranging from approximately 2700 to 3100 s for pure aluminum, 2300–2600 s for extra-super duralumin, and 1500–2000 s for oxygen-free copper. These results are consistent with the tendency reported in a previous study that materials with a lower mean atomic weight yield higher specific impulse. In contrast, thrust efficiency clearly varied depending on material and wavelength, being approximately 40 %, 36 %, and 21 % at <em>λ</em> = 532 nm, and 32 %, 31 %, and 12 % at <em>λ</em> = 1064 nm for pure aluminum, extra-super duralumin, and oxygen-free copper, respectively. These findings provide valuable insights into the wavelength dependency of laser ablation thrust performance and its implications for space propulsion systems.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 557-563"},"PeriodicalIF":3.1,"publicationDate":"2025-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143785055","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":"Numerical study on flame stabilization by shock-induced in a supersonic combustor with parallel-cavity: Symmetric configuration","authors":"Zhiqun Meng ,&nbsp;Chibing Shen ,&nbsp;Kaijing Jia ,&nbsp;Haoming He","doi":"10.1016/j.actaastro.2025.03.037","DOIUrl":"10.1016/j.actaastro.2025.03.037","url":null,"abstract":"<div><div>Based on the base configuration (BC) of a supersonic combustor with parallel-cavity, a two-dimensional symmetric oblique shock configuration (OS) and a three-dimensional symmetric swept shock (SS) configuration are designed. The flame stabilization mode, local combustion mode and scatter plot for the three configurations are studied by large eddy simulation (LES). The computational results for BC are in good agreement with the experimental data and images. Compared to BC, analysis of the flame stabilization model reveals that the high temperature and subsonic zones are expanded and result in the heat release to move forward in OS and SS. The effect is most obvious in SS, but the total pressure loss is the highest. There are relatively few vortex cores and smaller scale of vortex structures in SS. A modified flame index introducing mixture fraction is proposed and the filter functions for the local combustion modes are developed. Quantitative analysis indicates that the total heat release power in SS is 304.7 kW, which is the largest for the three configurations; and the heat release power for its subsonic downstream-diffusion combined combustion mode is 118.7 kW, which is the most important local combustion mode. The scatter plot shows the most pronounced effects of heat release concentrated and forward moved, mixture fraction space distribution reduced and OH backward moved in SS.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 721-733"},"PeriodicalIF":3.1,"publicationDate":"2025-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143869436","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":"Feasibility study and prospects analysis of lunar regolith forming based on concentrated solar energy","authors":"Honglun Yang ,&nbsp;Haitao Wang ,&nbsp;Biao Xie ,&nbsp;Mingqi Sun ,&nbsp;Shuyi Chen ,&nbsp;Zhe Zhang ,&nbsp;Tianzhu Zhang ,&nbsp;Gang Pei ,&nbsp;Chenglin Yi ,&nbsp;Shunuan Liu","doi":"10.1016/j.actaastro.2025.03.031","DOIUrl":"10.1016/j.actaastro.2025.03.031","url":null,"abstract":"<div><div>The solidification and molding of lunar regolith are essential for constructing lunar habitats. This study introduces an innovative lunar regolith molding technique that synergistically combines solar concentration, flexible optical fiber bundle energy transfer, and powder bed fusion. A functional prototype is developed to validate the proposed scheme. Systematic experiments including fixed beam spot melting, line melting, surface melting, and body melting are conducted using simulated basalt lunar regolith. Through in-situ observation of the melt pool's formation, evolution, and expansion dynamics, we identify a sequential transformation mechanism on the powder bed's surface: initial curling evolves into detachment from the bed, subsequent incorporation into a molten droplet, and ultimate solidification. A comprehensive evaluation of density and mechanical properties across multiple parameter combinations reveals that energy flux density of 3.33 MW/m² with a scan speed of 30 mm/min, inter-track spacing of 3 mm, and layer thickness of 2 mm enables the production of structurally integral samples with continuous morphology. The resulting specimens demonstrate a maximum compressive strength of 4.25 MPa and a density of 2.31 g/cm³. This solar-powered additive manufacturing approach establishes a viable reference framework for large-scale on-site construction of lunar research stations.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 424-438"},"PeriodicalIF":3.1,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143748277","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":"A review of lunar regolith based alkali activated materials and sintered regolith for use as a construction material","authors":"Federico Pederson ,&nbsp;Liam Ellersick ,&nbsp;Hee-Jeong Kim","doi":"10.1016/j.actaastro.2025.03.032","DOIUrl":"10.1016/j.actaastro.2025.03.032","url":null,"abstract":"<div><div>Over the last decade there have been numerous studies that propose regolith-based materials, such as regolith based geopolymers and sintered blocks, for permanent manned missions on the lunar surface, like those proposed by space agencies like the National Aeronautics and Space Administration in the US. In this review paper the current state of research was investigated for both of the materials described above, providing an overview of the methods of manufacture for their deployment as well as the mix designs used to meet the harsh environmental conditions of the lunar surface. For regolith based geopolymers, the primary methods of deposition are cast parts and large-scale 3D extrusion printing. For this application researchers have been focused on finding the relationship between water content, extreme temperature curing, and vacuum curing on the final mechanical performance and morphology. Because of the wide range of activation solutions and regolith simulants available to researchers, the main concern has been placed on optimizing the process methods for deposition and simulant chemistry. A similar situation is seen in regolith sintering where the heating method, configuration, and pretreatment limit the shape of the parts and the final properties. These sintered blocks were shown to have a high compressive strength but are limited by the part size and have high variability in performance due to inconsistent powder compositions. Based on our review, the research discussed in this paper on the curing conditions, testing, and manufacturing methods for lunar construction materials, a research gap was seen in providing large scale mechanical and degradation datasets on these materials for construction applications. This gap was also paired with a lack of standardization in regolith simulants and curing methods that accurately predict the conditions expected by lunar mission planners.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 502-515"},"PeriodicalIF":3.1,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143768156","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":"Crater formation and particle ejection induced by supersonic jet impingement in near-vacuum","authors":"Senthilkumar Subramanian,&nbsp;Andrew Wilson,&nbsp;Craig White,&nbsp;Konstantinos Kontis","doi":"10.1016/j.actaastro.2025.03.017","DOIUrl":"10.1016/j.actaastro.2025.03.017","url":null,"abstract":"<div><div>This study investigates the formation and evolution of craters under near-vacuum conditions due to supersonic jet impingement, with a focus on regolith particle ejection dynamics. Experiments were conducted at the Plume-Regolith Facility of the University of Glasgow, where controlled jet pulses (0.1, 0.5 and 1.0 s) were directed to high- and low-density regolith simulants. Using Particle Image Velocimetry (PIV) and infrared imaging, the crater morphology and ejecta distribution were analysed over multiple sequential jet pulses. The results indicate that the high-density regolith forms compact, steep-walled U-shaped craters, while the low-density regolith produces larger, sloped V-shaped craters. Longer pulse durations result in increased crater expansion and higher ejection angles. In particular, steep-walled craters promote high-angle ejection near the nozzle axis, posing potential risks to spacecraft landers. Regardless of regolith density, expelled particles exhibit ejection angles between 40°and 50°, suggesting long-distance travel in low-gravity environments. These findings improve our understanding of plume-regolith interactions and contribute to safer planetary landing strategies by informing numerical models and spacecraft design considerations.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 439-452"},"PeriodicalIF":3.1,"publicationDate":"2025-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760559","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":"Low-thrust under-actuated satellite formation guidance and control strategies","authors":"Ahmed Mahfouz ,&nbsp;Gabriella Gaias ,&nbsp;Florio Dalla Vedova ,&nbsp;Holger Voos","doi":"10.1016/j.actaastro.2025.02.048","DOIUrl":"10.1016/j.actaastro.2025.02.048","url":null,"abstract":"<div><div>This study presents autonomous guidance and control strategies for reconfiguring close-range multi-satellite formations. The formation consists of <span><math><mi>N</mi></math></span> under-actuated deputy satellites and an uncontrolled virtual or physical chief spacecraft. Each deputy is equipped with a single throttleable but ungimbaled low-thrust nozzle, requiring a combination of thrust and coast arcs, during the latter attitude adjustments redirect the nozzle to the desired thrust direction. The guidance problem is formulated as a trajectory optimization task incorporating dynamical and physical constraints, along with a minimum acceleration threshold imposed by typical electric thrusters. Two frameworks are considered: centralized and distributed. The centralized approach ensures fuel-optimal solutions but is feasible only for small formations, with all calculations performed on a physical chief satellite. The distributed approach, while sub-optimal, scales better by treating the chief as a virtual point mass and allowing each deputy to handle its own computations. This study focuses on spaceborne closed-loop control implementation, ensuring reliability and automation in solving the optimal control problem. To mitigate infeasibility risks, constraints that pose potential threats are identified and softened. Two Model Predictive Control architectures, shrinking-horizon and fixed-horizon, are implemented and compared in terms of fuel consumption and control accuracy. Their performance is analyzed for typical close-range reconfigurations required in Earth observation missions and benchmarked against existing approaches in the literature.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 405-423"},"PeriodicalIF":3.1,"publicationDate":"2025-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143738150","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":"Combustion and microexplosion characteristics in droplets of kerosene with boron nanoparticles and 1-pentanol","authors":"Sinan Feng,&nbsp;Zhe Zhu,&nbsp;Hefeng Lin,&nbsp;Liyan Chen,&nbsp;Xiaoxia Wang,&nbsp;Dawen Zeng","doi":"10.1016/j.actaastro.2025.03.030","DOIUrl":"10.1016/j.actaastro.2025.03.030","url":null,"abstract":"<div><div>Boron-based nanofluid fuel demonstrates a high energy density due to the presence of B nanoparticles (BNPs). This paper presents a comprehensive study of nanofluid fuels composed of kerosene, 1-pentanol, and BNPs through both theoretical analysis and experimental investigation. The 1-pentanol not only possesses a high heat value and physical properties, such as density and viscosity, that are comparable to those of kerosene, but it also serves as an effective dispersing medium for BNPs. Furthermore, test results examining the impact of 1-pentanol content on the stability of BNPs show that a concentration of 10 vol% 1-pentanol significantly inhibits the contact and aggregation of BNPs and makes them stably dispersed in fuel. Single droplet combustion experiments demonstrate that the 10B/K90P10 sample exhibits the best all-around combustion characteristics with an ignition delay time of 35 ms and a liquid phase combustion rate of 1.5537 mm²/s. Finally, a mathematical model has been developed to analyze and validate the combustion performance of boron-based alcohol-containing nanofluid fuels. The predicted ignition delay time, liquid phase combustion rate, and microexplosion time are within acceptable limits of their experimental values. This work provides valuable insights for the research and application of boron-based alcohol-containing nanofluid fuels.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 364-373"},"PeriodicalIF":3.1,"publicationDate":"2025-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143738426","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":"Electrodynamic attitude stabilization of a satellite in an indirect position","authors":"M.V. Maksimenko,&nbsp;A.A. Tikhonov","doi":"10.1016/j.actaastro.2025.03.018","DOIUrl":"10.1016/j.actaastro.2025.03.018","url":null,"abstract":"<div><div>The problem of triaxial stabilization of the satellite position in the orbital reference frame is considered. The satellite moves in a medium-height circular orbit, has a controlled electrostatic charge and its own magnetic moment. The question is raised on the possibility of implementing such a system of electrodynamic control of the angular position of the satellite in which the influence of the disturbing gravitational torque is compensated by additional terms in the control torques. A constructive analytical approach to the analysis of nonlinear stability in the problem of the triaxial attitude stabilization of the satellite is presented. The constructed mathematical model has no restrictions on the orbit inclination, on the accuracy of the model of the Earth’s magnetic field as well. The theorem on the asymptotic stability of the stabilized angular position of the satellite is proved. The theorem substantiates the possibility of building the specified control system. Nonlinear analysis is based on the direct Lyapunov method. The effectiveness of the developed attitude control system has been confirmed by computer modeling.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 516-524"},"PeriodicalIF":3.1,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143777219","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":"Planning and optimal control of a Venus variable altitude aerobot","authors":"Patricia Apostol ,&nbsp;Jacob Izraelevitz ,&nbsp;Ashish Goel ,&nbsp;Mike Allenspach","doi":"10.1016/j.actaastro.2025.03.008","DOIUrl":"10.1016/j.actaastro.2025.03.008","url":null,"abstract":"<div><div>Venus has long been of interest in humankind’s understanding of how Earth, and Earth-like rocky bodies, form and evolve in our solar system. A key missing capability for our exploration of Venus are technologies which can navigate through the atmosphere recurrently and over extended periods of time, with minimal power. Recently, the Jet Propulsion Laboratory (JPL) has developed a variable altitude aerobot for operation in the Venus atmosphere. By exchanging helium gas within a dual chamber architecture, the aerobot is capable of smoothly navigating through a <span><math><mrow><mn>10</mn></mrow></math></span> km tall altitude range. Although the aerobot is open-loop stable, its atmospherically dependent non-linear oscillatory behavior introduces the need for finer trajectory tracking in order to meet the mission scientific objectives. This work aims at developing a simulation and first convex optimization optimal control framework for such an aerobot architecture, targeted towards accurate mission driven altitude changes and reference tracking. A prior test conducted by JPL on a scale-size aerobot prototype in the Black Rock desert is used for the control plant model matching. Finally, we consider multiple mission driven altitude change maneuvers and show smooth trajectory tracking with minimal overshoot satisfying the operational requirements and constraints.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 330-341"},"PeriodicalIF":3.1,"publicationDate":"2025-03-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143725583","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":"Impedance control in serial-parallel hybrid space robots for assembly operations","authors":"Quan An ,&nbsp;Yao Zhang ,&nbsp;Xuchao Huang ,&nbsp;Hao Li ,&nbsp;Xinhui Xia","doi":"10.1016/j.actaastro.2025.03.016","DOIUrl":"10.1016/j.actaastro.2025.03.016","url":null,"abstract":"<div><div>This article presents the impedance control method for a serial-parallel hybrid space robot system (HSRS) including a robotic arm and a parallel platform in Stewart configuration, and achieves compliance and stability during assembly operations. In this article, the dynamic model of the HSRS is established firstly with considering the influence of external forces, which is the foundation of subsequent research. Afterwards, the impedance control method of the HSRS is implemented by analyzing its dynamic coupling effect. Based on that, the compliance assembly operation is achieved by the coordination between the robotic arm and the parallel platform. The correctness of the HSRS dynamic model is demonstrated through the theorem of momentum and closed-chain constraint equations. The effectiveness of the impedance control method is verified through a simulation of modules assembly. Moreover, the operational abilities of traditional serial space robot and the HSRS are compared by introducing external disturbances. Simulation results show the efficiency of the HSRS.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 316-329"},"PeriodicalIF":3.1,"publicationDate":"2025-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143714697","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}