Acta Astronautica最新文献

{"title":"The Fifth Volta Congress, Rome 1935. The birth of supersonic aerodynamics","authors":"Mario Marchetti","doi":"10.1016/j.actaastro.2025.02.039","DOIUrl":"10.1016/j.actaastro.2025.02.039","url":null,"abstract":"<div><div>The Fifth Volta Congress, the first International Congress on High Speeds in Aeronautics, organized by the Royal Academy of Italy and AIDA, the Italian Association of Aerotechnics, was held in Rome in 1935. The topic was chosen in response to the specific needs of a time when the main interest of the various countries was to have high-speed aircraft at their disposal to increase the prestige of each nation. The research carried out in the 1930s had not as yet reached a sufficient scientific level to clear up the many issues regarding high-speed flight. The nature of the physical transformations brought about by fluid compressibility at high speeds and their effects within the well-known laws of aerodynamics and the point at which they are no longer negligible were still not clear.</div><div>Italy was keen to enhance its aeronautical development, and the Fascist regime under Benito Mussolini was well aware of the fact. Mussolini’s intention was to consolidate his power yet further, and together with Adolf Hitler, he created the Rome-Berlin Axis in the field of aeronautical technology, Achse Berlin-Rom - auch in der Luftfahrttechnik.</div><div>Under this agreement, two eminent Italian scientists, Gaetano Arturo Crocco, Dean of the School of Aeronautical Engineering of Rome, President of AIDA, the Italian Association of Aerotechnics, and Guglielmo Marconi, Nobel Prize in Physics in 1909, President of the Royal Academy of Italy and of the CNR, National Research Council of Italy, decided to organize a special event: “The Fifth Volta Congress”, dedicated exclusively to the study of high-speed aerodynamics.</div><div>Attendance was by invitation only, and the greatest international experts on subsonic and supersonic aerodynamics took part, Theodore von Kàrmàn, Ludwig Prandtl, Adolf Busemann, Eastman N. Jacobs, Jakob Ackeret, Wladimir Margoulis, Geoffrey Ingram Taylor, Eugen Sänger and others.</div><div>The Congress saw the presence of many Italian scientists from universities and research centres, among which the DSSE, the Air Force Ministry’s High Directorate for Studies and Tests located in Guidonia near Rome and equipped with specific subsonic and transonic wind tunnels.</div><div>The Fifth Volta Congress was the event that laid the foundations for supersonic aerodynamics, thus opening up once and for all the Age of Astronautics.</div><div>As well as describing the scientific and political aspects of the Congress, the aim of the present work is also to analyze its influence on the development of supersonic and hypersonic aerodynamics which was then further accentuated with the research of Antonio Ferri and Luigi Broglio, the father of Italian Space.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 235-245"},"PeriodicalIF":3.1,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143550484","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 design methodology for flat slab lunar landing and launch pad systems","authors":"Ian E. Jehn ,&nbsp;Christopher B. Dreyer","doi":"10.1016/j.actaastro.2025.02.046","DOIUrl":"10.1016/j.actaastro.2025.02.046","url":null,"abstract":"<div><div>This work applies established civil, structural, and geotechnical engineering design practices to a flat slab Landing and Launch Pad (LLP) or Vertical Takeoff Vertical Landing (VTVL) pad systems constructed on the lunar surface. While terrestrial launch and landing facilities exist as a potential starting point for understanding the analysis and design of these lunar pad systems, a design method has yet to be established within the space and lunar surface construction industry. The Basis of Design and analysis method outlined in this document are the result of feasibility and design studies conducted by the authors for LLP design and construction. It is meant to establish a baseline approach conducted by a licensed structural engineer with the ability and competency to design similar systems terrestrially. This work also identifies areas of knowledge gaps conducted in an effort to inform the industry of areas where future work can be conducted.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 175-192"},"PeriodicalIF":3.1,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143550606","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":"Effects of exercise intervention on executive function in 90-day head-down bed rest","authors":"Yaping Wang ,&nbsp;Zewei Li ,&nbsp;Rui Su ,&nbsp;Xieshun Wang ,&nbsp;Shihuan Gao ,&nbsp;Yining Wang ,&nbsp;Youran Zhang ,&nbsp;Yanjie Su","doi":"10.1016/j.actaastro.2025.02.033","DOIUrl":"10.1016/j.actaastro.2025.02.033","url":null,"abstract":"<div><div>Exercise is commonly used as an intervention strategy to enhance individual executive function. However, its effectiveness in improving executive function under prolonged head-down bed rest (HDBR) conditions remains unclear. The objective of this research is to examine whether physical exercise can improve executive function under HDBR conditions. We conducted a 135-day HDBR study involving 36 participants randomly allocated to five groups: control group (C), aerobic exercise combined with low-intensity resistance training (E1), aerobic exercise combined with high-intensity resistance training (E2), aerobic exercise alone (E3), and resistance training alone (E4). These exercise interventions were conducted during HDBR conditions. Additionally, we assessed working memory and cognitive flexibility throughout the study, including baseline (-3d), three intervention period assessments (30d, 60d, 90d), and a post-assessment (+30d). Findings revealed that during the early stage (30d) of HDBR, the intervention combining higher intensity resistance and aerobic exercises (E2) significantly enhanced cognitive flexibility. Conversely, in the mid-stage (60d) of HDBR, resistance training alone (E4) demonstrated superior improvement in cognitive flexibility compared to other intervention modalities. In conclusion, this study provides experimental evidence on the alterations in individual executive function under simulated long-term weightlessness conditions and offers guidance on the implementation of exercise interventions at various stages of HDBR conditions.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 23-31"},"PeriodicalIF":3.1,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143562846","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":"Sintering of Lunar regolith: A review","authors":"Sk S. Hossain ,&nbsp;Jeffrey W. Bullard","doi":"10.1016/j.actaastro.2025.02.038","DOIUrl":"10.1016/j.actaastro.2025.02.038","url":null,"abstract":"<div><div>The prospect of sustainable Lunar construction has received significant attention in recent years, driven by ambitions for Moon exploration and colonization. Among the various techniques explored, regolith sintering has emerged as a promising method due to its potential to efficiently utilize local resources like Lunar regolith and solar energy. Significant research has been conducted in recent years to advance regolith sintering through various innovative approaches using both mare and highland Lunar regolith simulants. This review presents a comprehensive overview of recent advances and obstacles in regolith sintering for Lunar construction. We focus on state-of-the-art regolith sintering techniques and their key parameters, highlighting their potential to design shapes with uniform density and microstructure. In addition, we review how the particle size distribution and mineralogical composition of the regolith simulants affect the physical and mechanical properties of the sintered shapes. Densification and key aspects of 3D printed regolith shapes are also discussed. Moreover, we evaluate the opportunities and current limitations for the further development of regolith sintering in Lunar construction. The review provides a perspective on in-situ resource utilization for Lunar construction through sintering technology, paving the way for future Lunar settlements.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 153-174"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143550605","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":"Improving specific impulse of Hall thruster by pulse power technology","authors":"Haochen Ma ,&nbsp;Tiance Liang ,&nbsp;He Zheng ,&nbsp;Jiapeng Li ,&nbsp;Liqiu Wei ,&nbsp;Liang Han ,&nbsp;Hong Li ,&nbsp;Yongjie Ding","doi":"10.1016/j.actaastro.2025.02.043","DOIUrl":"10.1016/j.actaastro.2025.02.043","url":null,"abstract":"<div><div>It is necessary to increase the voltage and reduce the anode volume flow rate to improve the specific Hall thruster impulse under power constraints. This leads to a low density of neutral gas flow in the channel and results in insufficient ionization. This study proposes pulse power technology to improve the specific Hall thruster impulse. The influence of pulsed discharge on the discharge and plasma plume characteristics of a Hall thruster was investigated. The experimental results show that the high voltage provided by the pulsed mode was beneficial to the acceleration of ions at constant power and anode flow. As a result, the specific impulse, efficiency, and thrust of Hall thruster improved. The specific impulse of the Hall thruster at constant power is 1770 s in the pulsed mode and 1570 s in the direct current (DC) mode. This represents an increase of about 12.7 %, which significantly raises the upper limit of the Hall thruster's specific impulse. The results of this study are significant for the design of high-specific-impulse Hall thrusters.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 127-133"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143527320","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":"Hypergolic solid propellant using NaBH4/KNO3 with paraffin for HTP-based hybrid rockets","authors":"C.-S. Chang ,&nbsp;S.-S. Wei ,&nbsp;Zu Puayen Tan ,&nbsp;Y.-X. Chang ,&nbsp;Jong-Shinn Wu","doi":"10.1016/j.actaastro.2025.02.041","DOIUrl":"10.1016/j.actaastro.2025.02.041","url":null,"abstract":"<div><div>To improve the ignition system of a hybrid rocket engine, this paper reports the experimental study of the performance of the hypergolic solid fuel grain (HSF) consisting of a mixture of NaBH₄/KNO₃ with paraffin for a hybrid rocket engine using 90 % HTP as the oxidizer. Drop tests were conducted to examine the ignition delay time (IDT) of HSF compositions with varying ratios of sodium borohydride (NaBH₄) and potassium nitrate (KNO₃) mixing with paraffin. The results showed that IDT decreased with increasing amount of NaBH₄, and decreased further with KNO₃ addition. For comparison purpose, two formulations were selected for the tests: HSF01 (80 wt% paraffin, 20 wt% NaBH₄) and HSF02 (65 wt% paraffin, 20 wt% NaBH₄, 15 wt% KNO₃). A series of image visualizations using high-resolution and high-speed cameras, and event cameras revealed similar ignition mechanisms for both tests, in which flamelets were formed upon the contact of HTP droplet, leading to explosive combustion. However, KNO₃ in HSF02 consumed the smoke-like mixture produced during the explosion, in which behavior was absent in HSF01. In addition, atmospheric combustion tests (ACT) were conducted in a PMMA tube (10 mm in diameter and 100 mm in length) and the results showed that only HSF02 was successfully ignited, with flamelets forming ∼4 ms after HTP injection and full combustion was established at ∼0.7 s. The test results indicated that the KNO₃ as an oxidant additive added to the hypergolic solid fuel grain (HSF) plays an important role in the HSF ignition mechanism. It decreases not only the IDT of the fuel grain, but also increases the flammability of the HSF.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 103-112"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143519578","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":"Configuration acquisition of gravitational wave detector based on differential geometry guidance","authors":"Xianda Liu ,&nbsp;Yunhe Meng","doi":"10.1016/j.actaastro.2025.02.040","DOIUrl":"10.1016/j.actaastro.2025.02.040","url":null,"abstract":"<div><div>This paper studies the configuration acquisition problem of the TianQin space gravitational wave detector. For the characteristics of the TianQin gravitational wave detector configuration, such as large scale, high precision requirements, and small upper limit of thrust, firstly, the large-scale configuration acquisition problem is transformed into a small-scale rendezvous problem using the virtual formation idea. Then, using the differential geometry guidance method, high-precision, and rapid rendezvous is achieved through continuous small thrust, and the process of achieving configuration acquisition through collaborative optimization using genetic algorithms is designed. Finally, the influence of differential geometry guidance law parameters on rendezvous performance is analyzed through simulation, and the feasibility of collaborative optimization to achieve configuration acquisition is verified.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 134-147"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143527317","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":"Improving efficiency in CubeSat mass production: A modular and standardized approach","authors":"Eyoas E. Areda ,&nbsp;Masui Hirokazu ,&nbsp;Mengu Cho","doi":"10.1016/j.actaastro.2025.02.017","DOIUrl":"10.1016/j.actaastro.2025.02.017","url":null,"abstract":"<div><div>Advancements in CubeSat technologies are revolutionizing space research and commercial satellite applications, enabling CubeSats to conduct advanced, complex missions. A key development is the deployment of CubeSat constellations for continuous monitoring, driven by private space firms due to low costs and scalability. As demand for CubeSat constellations grows, standardized design and development processes are crucial for mass production. Traditional CubeSat interfaces, using a stacking arrangement, increase assembly time and costs due to a lack of standardization. Customizing interfaces for specific missions complicates testing and repairs, reducing reliability and flexibility. System complexity in satellite development causes inefficiency, yet the impact on mass CubeSat production remains unassessed, with no established methods to evaluate satellite assembly complexity. To address these issues, this study investigates CubeSat platform interfaces using industrial design tools like design for manufacturing and assembly and advanced complexity analysis. The goal is to develop a modular, flexible platform with a standardized interface to enhance compatibility and reduce costs. This study describes the development and interface standardization process of a 1U structure platform using a slot-type mechanical interface and a backplane-board-type electrical interface for efficient mass production. The concept, previously demonstrated on a 3U CubeSat, employs a unique method for mounting internal subsystems onto the main structural frame, facilitating integration while minimizing structural parts. Important design parameters influencing efficiency are evaluated against conventional designs for suitability in high-demand applications. Evaluation methods are validated with assembly and disassembly tests, resulting in reduced integration time, lower costs, and improved reliability. Assembly tests and environmental testing under launch conditions have shown promising results, ensuring the design can withstand launch loads.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 51-67"},"PeriodicalIF":3.1,"publicationDate":"2025-02-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143580590","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":"Speeding up heterogeneous binary asteroid system propagation through the physics-informed neural network","authors":"Jucheng Lu,&nbsp;Haibin Shang,&nbsp;Xuefen Zhang","doi":"10.1016/j.actaastro.2025.02.022","DOIUrl":"10.1016/j.actaastro.2025.02.022","url":null,"abstract":"<div><div>This paper proposes the application of a physics-informed neural network (PINN) to the propagation of heterogeneous binary asteroid systems. The accuracy and efficiency of such propagation are important in the study of celestial mechanics and mission analysis, where we devote to achieving a reasonable balance. The gravitational interactions, which are necessary quantities for this integration, are formulated in Taylor expansion representation that incorporates the derivatives of the primary’s gravitational potential, the secondary’s generalized inertia integrals, and the relative geometry. To represent the gravity field of the primary with heterogeneous mass distribution, a hybrid model combining a quadrature-based polyhedron model and a PINN-based model is developed. The derivatives of the resultant gravitational potential are obtained by superposing those from the polyhedron and PINN-based models, with calculations performed using analytical formulas and automatic differentiation, respectively. For the gravitational potential evaluations, the hybrid model offers faster computation speed and comparable precision compared to the benchmark model. Its application to binary asteroid system propagation demonstrates that the PINN component can effectively capture the effects of non-uniform mass distribution of the body. Furthermore, our mutual dynamics simulations suggest that the heterogeneous mass distribution of the primary may significantly influence the orbital period of the system.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 64-79"},"PeriodicalIF":3.1,"publicationDate":"2025-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143508768","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":"Preliminary analysis and design of an optical space surveillance and tracking constellation for LEO coverage","authors":"A. D’Anniballe,&nbsp;L. Felicetti,&nbsp;S. Hobbs","doi":"10.1016/j.actaastro.2025.02.019","DOIUrl":"10.1016/j.actaastro.2025.02.019","url":null,"abstract":"<div><div>Accurately tracking space debris and operational satellites is the foundation of the long-term sustainability of space operations. To improve upon some of the inherent limitations of ground radars, a constellation of satellites carrying optical sensors for the surveillance of the Low Earth Orbit (LEO) region is analysed. This analysis aims to understand the performance drivers of such a system in terms of constellation geometry and provide a general methodology for the preliminary design of the system. First, a method for decoupling the design of the optical payload and the constellation geometry while retaining statistically significant results is shown. Using the resulting estimate for the maximum observable distance, an approximate method for computing the coverage of the system is proposed. The expected daily and yearly variation of coverage depending on its own dynamics and the position of the Sun is analysed, showing that it has a small impact on the design process. The dependence of the coverage on constellation parameters such as altitude, inclination and distribution of satellites is investigated through parametric analysis, retrieving an estimate for the Pareto front of the system. Building upon the previous results, a random search method is shown to be effective in finding a design point lying on the Pareto front that is robust to both random satellite loss and deployment strategy. Finally, a reduced budget architecture is proposed to achieve acceptable performance while using only a few tens of satellites. The resulting work answers the problems of estimating and optimising the performance of a distributed system for space-based surveillance of the LEO region, a stepping stone for future cost–benefit analyses for the enhancement of space surveillance networks.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 47-63"},"PeriodicalIF":3.1,"publicationDate":"2025-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143478586","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}