As the idea of crewed outposts on the Moon gains momentum, In-Situ Resource Utilization (ISRU) technologies tend to become imperative to fulfill astronauts' needs. This article explores a way to use the lunar regolith as a source material for the additive manufacturing of complex objects, based on the selective laser melting (SLM) technique. A lunar regolith analog, Basalt of Pic d’Ysson (BPY), is used as a starting point for this study, to investigate the now demonstrated impact of amorphous analog content in the powder bed, substrate type, and post-SLM annealing treatments on the mechanical properties of 3D-printed objects. Improvements to the manufacturing and sample extraction stages are proposed to systematically reproduce the high compressive strength values obtained, thus contributing to the robustness and reliability of the process.
随着在月球上建立载人前哨站的想法日益强烈，原地资源利用（ISRU）技术成为满足宇航员需求的当务之急。本文以选择性激光熔融（SLM）技术为基础，探讨了一种将月球碎屑岩用作复杂物体增材制造源材料的方法。本研究以月球残积岩类似物--Basalt of Pic d'Ysson (BPY)--为起点，研究现已证明的粉末床中非晶类似物含量、基质类型和选择性激光熔融（SLM）后退火处理对 3D 打印物体机械性能的影响。本研究建议改进制造和样品提取阶段，以系统地再现所获得的高抗压强度值，从而提高工艺的稳健性和可靠性。
{"title":"Selective laser melting of partially amorphous regolith analog for ISRU lunar applications","authors":"Julien Granier , Thierry Cutard , Patrick Pinet , Yannick Le Maoult , Serge Chevrel , Thierry Sentenac , Jean-Jacques Favier","doi":"10.1016/j.actaastro.2024.10.024","DOIUrl":"10.1016/j.actaastro.2024.10.024","url":null,"abstract":"<div><div>As the idea of crewed outposts on the Moon gains momentum, In-Situ Resource Utilization (ISRU) technologies tend to become imperative to fulfill astronauts' needs. This article explores a way to use the lunar regolith as a source material for the additive manufacturing of complex objects, based on the selective laser melting (SLM) technique. A lunar regolith analog, Basalt of Pic d’Ysson (BPY), is used as a starting point for this study, to investigate the now demonstrated impact of amorphous analog content in the powder bed, substrate type, and post-SLM annealing treatments on the mechanical properties of 3D-printed objects. Improvements to the manufacturing and sample extraction stages are proposed to systematically reproduce the high compressive strength values obtained, thus contributing to the robustness and reliability of the process.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 66-77"},"PeriodicalIF":3.1,"publicationDate":"2024-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142535399","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}
Pub Date : 2024-10-15DOI: 10.1016/j.actaastro.2024.09.062
Umberto De Filippis , Carlo Lefevre , Marco Lucente , Carmelo Magnafico , Francesco Santoli
The BepiColombo ESA-JAXA mission, launched on October 20, 2018, is scheduled to reach Mercury in November 2026. The Mercury Composite Spacecraft comprises three modules: the Mercury Planetary Orbiter, the Mercury Magnetospheric Orbiter, and the Mercury Transfer Module. Currently, BepiColombo is in its seven-year cruise phase, having completed one Earth flyby, two Venus flybys, and three Mercury flybys. The spacecraft is equipped with the high-accuracy Italian Spring Accelerometer, capable of measuring non-gravitational acceleration variations at frequencies between . Interpreting accelerometer data can be challenging due to overlapping dynamic effects. During the second Venus flyby, the accelerometer data revealed significant signatures of the gravity gradient signal induced by the planet on the proof masses. Notably, a large, unexpected acceleration spike was detected near the closest approach, lasting a few minutes. Further analysis determined that this spike was most likely caused by outgassing from the Mercury Planetary Orbiter radiator. This paper analyzes the Italian Spring Accelerometer data from the second Venus flyby, focusing on the unexpected acceleration spike. By combining the torque data from the reaction wheel with accelerometer data, the team was able to estimate the outgassing location, confirming it as the spacecraft radiator. Additionally, data from the Mass Spectrum Analyzer sensor, part of the Mercury Plasma Particle Experiment, suggest that outgassing occurred. The estimated mass of sublimated water is approximately 2 grams.
{"title":"Characterization of the outgassing event during BepiColombo second Venus flyby using Italian Spring Accelerometer data","authors":"Umberto De Filippis , Carlo Lefevre , Marco Lucente , Carmelo Magnafico , Francesco Santoli","doi":"10.1016/j.actaastro.2024.09.062","DOIUrl":"10.1016/j.actaastro.2024.09.062","url":null,"abstract":"<div><div>The BepiColombo ESA-JAXA mission, launched on October 20, 2018, is scheduled to reach Mercury in November 2026. The Mercury Composite Spacecraft comprises three modules: the Mercury Planetary Orbiter, the Mercury Magnetospheric Orbiter, and the Mercury Transfer Module. Currently, BepiColombo is in its seven-year cruise phase, having completed one Earth flyby, two Venus flybys, and three Mercury flybys. The spacecraft is equipped with the high-accuracy Italian Spring Accelerometer, capable of measuring non-gravitational acceleration variations at frequencies between <span><math><mrow><mrow><mo>[</mo><mn>3</mn><mo>×</mo><mn>1</mn><msup><mrow><mn>0</mn></mrow><mrow><mo>−</mo><mn>5</mn></mrow></msup><mo>,</mo><mn>1</mn><msup><mrow><mn>0</mn></mrow><mrow><mo>−</mo><mn>1</mn></mrow></msup><mo>]</mo></mrow><mspace></mspace><mi>Hz</mi></mrow></math></span>. Interpreting accelerometer data can be challenging due to overlapping dynamic effects. During the second Venus flyby, the accelerometer data revealed significant signatures of the gravity gradient signal induced by the planet on the proof masses. Notably, a large, unexpected acceleration spike was detected near the closest approach, lasting a few minutes. Further analysis determined that this spike was most likely caused by outgassing from the Mercury Planetary Orbiter radiator. This paper analyzes the Italian Spring Accelerometer data from the second Venus flyby, focusing on the unexpected acceleration spike. By combining the torque data from the reaction wheel with accelerometer data, the team was able to estimate the outgassing location, confirming it as the spacecraft radiator. Additionally, data from the Mass Spectrum Analyzer sensor, part of the Mercury Plasma Particle Experiment, suggest that <span><math><mrow><msub><mrow><mi>H</mi></mrow><mrow><mn>2</mn></mrow></msub><mi>O</mi></mrow></math></span> outgassing occurred. The estimated mass of sublimated water is approximately 2 grams.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 11-19"},"PeriodicalIF":3.1,"publicationDate":"2024-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142444905","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}
Pub Date : 2024-10-15DOI: 10.1016/j.actaastro.2024.10.026
Jay Michael Jaber , Joshua Ong , Ethan Waisberg , Prithul Sarker , Nasif Zaman , Alireza Tavakkoli , Andrew G. Lee
Outer space is an austere environment filled with unique and potentially dangerous stressors that can impact the physiologic function of astronauts during and after their stay above the atmosphere. Within 24 h of flight, astronauts may experience nausea and malaise, coined space motion sickness, due to vestibular and ocular sensory mismatch and changes in cranial and other fluid pressures. Although temporary, long-lasting conditions also arise. Spaceflight Associated Neuro-Ocular Syndrome is associated optic disc edema, globe flattening, and hyperopic refractive error shifts, and may lead to permanent structural changes. In addition, astronauts during space flight can lose up to 30 % of their muscle mass and 8–12 % of bone density. Some of these changes require months of rehabilitation and adaptation to make a full recovery. Radiation and secondary cellular alterations can lead to carcinogenesis, microbiome shifts, and immunological dysfunction. To combat these changes, NASA has continually researched ways to improve the spaceflight experience. New spin off technology from NASA to address these astronaut health concerns often find their way into the terrestrial consumer and healthcare markets. This paper aims to identify NASA associated breakthroughs in medical innovation including cutting-edge technology created for laser tracking of ballistic missiles, durable polymers for high-speed air travel, refractive eye surgery, and cardiac resynchronization devices.
外太空是一个充满独特和潜在危险压力的严酷环境，这些压力会在宇航员停留在大气层上空期间和之后影响他们的生理功能。在飞行 24 小时内，由于前庭和眼部感觉不匹配以及颅压和其他体液压力的变化，宇航员可能会感到恶心和不适，这就是所谓的太空运动病。虽然是暂时的，但也会出现长期的病症。与太空飞行相关的神经-眼综合症与视盘水肿、眼球变平和远视屈光不正偏移有关，并可能导致永久性的结构变化。此外，宇航员在太空飞行期间可能会失去多达 30% 的肌肉质量和 8-12% 的骨密度。其中一些变化需要数月的康复和适应才能完全恢复。辐射和继发性细胞改变会导致致癌、微生物群变化和免疫功能失调。为了应对这些变化，NASA 不断研究改善太空飞行体验的方法。美国国家航空航天局为解决这些宇航员健康问题而衍生出的新技术往往会进入地面消费和保健市场。本文旨在介绍与 NASA 相关的医疗创新突破，包括用于弹道导弹激光跟踪的尖端技术、用于高速航空旅行的耐用聚合物、屈光眼科手术和心脏再同步装置。
{"title":"NASA's impact on medical innovation: Breakthrough technologies from space research","authors":"Jay Michael Jaber , Joshua Ong , Ethan Waisberg , Prithul Sarker , Nasif Zaman , Alireza Tavakkoli , Andrew G. Lee","doi":"10.1016/j.actaastro.2024.10.026","DOIUrl":"10.1016/j.actaastro.2024.10.026","url":null,"abstract":"<div><div>Outer space is an austere environment filled with unique and potentially dangerous stressors that can impact the physiologic function of astronauts during and after their stay above the atmosphere. Within 24 h of flight, astronauts may experience nausea and malaise, coined space motion sickness, due to vestibular and ocular sensory mismatch and changes in cranial and other fluid pressures. Although temporary, long-lasting conditions also arise. Spaceflight Associated Neuro-Ocular Syndrome is associated optic disc edema, globe flattening, and hyperopic refractive error shifts, and may lead to permanent structural changes. In addition, astronauts during space flight can lose up to 30 % of their muscle mass and 8–12 % of bone density. Some of these changes require months of rehabilitation and adaptation to make a full recovery. Radiation and secondary cellular alterations can lead to carcinogenesis, microbiome shifts, and immunological dysfunction. To combat these changes, NASA has continually researched ways to improve the spaceflight experience. New spin off technology from NASA to address these astronaut health concerns often find their way into the terrestrial consumer and healthcare markets. This paper aims to identify NASA associated breakthroughs in medical innovation including cutting-edge technology created for laser tracking of ballistic missiles, durable polymers for high-speed air travel, refractive eye surgery, and cardiac resynchronization devices.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 34-41"},"PeriodicalIF":3.1,"publicationDate":"2024-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142444907","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}
Pub Date : 2024-10-12DOI: 10.1016/j.actaastro.2024.10.025
Chenxi Lu , Meng Yu , Hua Li , Hutao Cui
Planetary rover autonomous localization is paramount for a planetary surface exploration mission. However, existing methods demonstrate limited localization accuracy, mostly due to the unstructured texture characterization of planetary surface. In response, this study presents a novel Neural Radiance Field (NeRF) driven visual odometry correction method that allows for high-precision 6-DoF rover pose estimation and local map pruning. First, an innovative image saliency evaluation approach, combining binarization and feature detection, is introduced to meticulously select landmarks that are conducive to rover re-localization. Subsequently, we conduct 3D reconstruction and rendering of the chosen landmarks based on a-priori knowledge of planetary surface images and their Neural Radiance Field (NeRF) models. High-precision odometry correction is achieved through the optimization of photometric loss between NeRF rending images and real images. Simultaneously, the odometry correction mechanism is employed in an autonomous manner to refine the NeRF model of the corresponding landmark, leading to an improved local map and gradually enhanced rover localization accuracy. Numerical simulation and experiment trials are carried out to evaluate the performance of the proposed method, results of which demonstrate state-of-the-art rover re-localization accuracy and local map pruning.
{"title":"Landmark-aware autonomous odometry correction and map pruning for planetary rovers","authors":"Chenxi Lu , Meng Yu , Hua Li , Hutao Cui","doi":"10.1016/j.actaastro.2024.10.025","DOIUrl":"10.1016/j.actaastro.2024.10.025","url":null,"abstract":"<div><div>Planetary rover autonomous localization is paramount for a planetary surface exploration mission. However, existing methods demonstrate limited localization accuracy, mostly due to the unstructured texture characterization of planetary surface. In response, this study presents a novel Neural Radiance Field (NeRF) driven visual odometry correction method that allows for high-precision 6-DoF rover pose estimation and local map pruning. First, an innovative image saliency evaluation approach, combining binarization and feature detection, is introduced to meticulously select landmarks that are conducive to rover re-localization. Subsequently, we conduct 3D reconstruction and rendering of the chosen landmarks based on <em>a-priori</em> knowledge of planetary surface images and their Neural Radiance Field (NeRF) models. High-precision odometry correction is achieved through the optimization of photometric loss between NeRF rending images and real images. Simultaneously, the odometry correction mechanism is employed in an autonomous manner to refine the NeRF model of the corresponding landmark, leading to an improved local map and gradually enhanced rover localization accuracy. Numerical simulation and experiment trials are carried out to evaluate the performance of the proposed method, results of which demonstrate state-of-the-art rover re-localization accuracy and local map pruning.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 86-96"},"PeriodicalIF":3.1,"publicationDate":"2024-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534984","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}
Pub Date : 2024-10-11DOI: 10.1016/j.actaastro.2024.10.015
Zhe Zhang , Felix Schäfer , Muhammad Rawahid Ali , William Yeong Liang Ling , Xiangyang Liu
Plasma plumes are the end products ejected from electric propulsion after complex ionization and acceleration processes. The physics behind the plasma plumes has attracted significant interest due to their interactions with the critical components of satellites and an increased understanding of the relevant processes. Recently, in the front view from a pulsed plasma thruster (PPT), we observed an unclosed vortex structure in the plasma plume, which led us to reconsider the propagation process and the current flux directions inside a plasma plume. To study this plume structure in depth, a highly sensitive Rogowski coil is used here to obtain the current density of the plume over the operating period of a PPT in 3 perpendicular directions. Vector-time-resolved current flux maps were obtained through experimental measurements and the peak current densities were found to reach 50000 mA/cm2 to 250000 mA/cm2. From successive 3-D current flux maps, the complete process of current flow inside a transient plasma plume is observed. The vortex plume structure was found to form during the initial discharge period. The plasma in-plume current is shown to be involved by discharge circuit. After the main discharge is completed, the plasma plume tends to circuit-independent and in self-equilibrium.
{"title":"Vector-time-resolved in-plume plasma current density flux measurement in a pulsed plasma thruster","authors":"Zhe Zhang , Felix Schäfer , Muhammad Rawahid Ali , William Yeong Liang Ling , Xiangyang Liu","doi":"10.1016/j.actaastro.2024.10.015","DOIUrl":"10.1016/j.actaastro.2024.10.015","url":null,"abstract":"<div><div>Plasma plumes are the end products ejected from electric propulsion after complex ionization and acceleration processes. The physics behind the plasma plumes has attracted significant interest due to their interactions with the critical components of satellites and an increased understanding of the relevant processes. Recently, in the front view from a pulsed plasma thruster (PPT), we observed an unclosed vortex structure in the plasma plume, which led us to reconsider the propagation process and the current flux directions inside a plasma plume. To study this plume structure in depth, a highly sensitive Rogowski coil is used here to obtain the current density of the plume over the operating period of a PPT in 3 perpendicular directions. Vector-time-resolved current flux maps were obtained through experimental measurements and the peak current densities were found to reach 50000 mA/cm<sup>2</sup> to 250000 mA/cm<sup>2</sup>. From successive 3-D current flux maps, the complete process of current flow inside a transient plasma plume is observed. The vortex plume structure was found to form during the initial discharge period. The plasma in-plume current is shown to be involved by discharge circuit. After the main discharge is completed, the plasma plume tends to circuit-independent and in self-equilibrium.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 1-10"},"PeriodicalIF":3.1,"publicationDate":"2024-10-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142441315","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}
Pub Date : 2024-10-10DOI: 10.1016/j.actaastro.2024.10.021
Darshini Jayakumar , Jey Kumar Pachiyappan , Parikshit Roychowdhury , Gowthamarajan Kuppusamy , Jeyaprakash M R , Veera Venkata Satyanarayana Reddy Karri , Jayakumar Venkatesan , Samir Mallick , Priti Tagde , Nusrat K. Shaikh , Farhat S. Khan
Cardiovascular deconditioning in microgravity presents a significant challenge for astronauts on extended space missions. As astronauts contend with microgravity complexities, such as altered fluid distribution, reduced cardiac output, and vascular adaptations, understanding the multifaceted influence of ANP becomes vital for developing precise interventions. The findings are from various research approaches, including human analog studies, murine models, aquatic models, and primate studies. Human analog studies, utilizing methods like bedrest head-down techniques, lower body positive pressure, and parabolic flights, offer valuable insights into potential countermeasures by simulating microgravity conditions. Further, the studies involving aquatic models and primates contribute additional layers of complexity, enriching our understanding of cardiovascular changes in biological systems more analogous to humans. Ground studies, integrating lower body positive pressure and Gz centrifugation, establish controlled environments to simulate gravity-like conditions, refining potential countermeasures. Space flight simulations subject individuals to varying gravitational forces, replicating real-world space mission conditions. Current countermeasures, including fluid intake protocols, negative pressure breathing maneuvers, and innovative technologies like the Countermeasure Evaluation and Validation System (CEVIS), are reviewed as cutting-edge approaches to address cardiovascular deconditioning. The forward-looking perspective envisions the future of cardiovascular deconditioning research, emphasizing the development of personalized interventions tailored to individual responses, advanced exercise protocols, and the exploration of novel technologies such as artificial gravity generators.
{"title":"The impact of cardiovascular deconditioning in space: A review","authors":"Darshini Jayakumar , Jey Kumar Pachiyappan , Parikshit Roychowdhury , Gowthamarajan Kuppusamy , Jeyaprakash M R , Veera Venkata Satyanarayana Reddy Karri , Jayakumar Venkatesan , Samir Mallick , Priti Tagde , Nusrat K. Shaikh , Farhat S. Khan","doi":"10.1016/j.actaastro.2024.10.021","DOIUrl":"10.1016/j.actaastro.2024.10.021","url":null,"abstract":"<div><div>Cardiovascular deconditioning in microgravity presents a significant challenge for astronauts on extended space missions. As astronauts contend with microgravity complexities, such as altered fluid distribution, reduced cardiac output, and vascular adaptations, understanding the multifaceted influence of ANP becomes vital for developing precise interventions. The findings are from various research approaches, including human analog studies, murine models, aquatic models, and primate studies. Human analog studies, utilizing methods like bedrest head-down techniques, lower body positive pressure, and parabolic flights, offer valuable insights into potential countermeasures by simulating microgravity conditions. Further, the studies involving aquatic models and primates contribute additional layers of complexity, enriching our understanding of cardiovascular changes in biological systems more analogous to humans. Ground studies, integrating lower body positive pressure and Gz centrifugation, establish controlled environments to simulate gravity-like conditions, refining potential countermeasures. Space flight simulations subject individuals to varying gravitational forces, replicating real-world space mission conditions. Current countermeasures, including fluid intake protocols, negative pressure breathing maneuvers, and innovative technologies like the Countermeasure Evaluation and Validation System (CEVIS), are reviewed as cutting-edge approaches to address cardiovascular deconditioning. The forward-looking perspective envisions the future of cardiovascular deconditioning research, emphasizing the development of personalized interventions tailored to individual responses, advanced exercise protocols, and the exploration of novel technologies such as artificial gravity generators.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1001-1011"},"PeriodicalIF":3.1,"publicationDate":"2024-10-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426040","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}
Pub Date : 2024-10-10DOI: 10.1016/j.actaastro.2024.10.005
Paolo Marzioli , Daniel Oltrogge , Claudiu Mihai Taiatu , Mark A. Skinner , Andy Court
Radio-Frequency Interference (RFI) has a large impact on the business of commercial satellites communications and will have an increasingly important role in the next years and decades due to the spread of the launched spacecraft population.
This paper presents the current state-of-the-art for Space Traffic Management -related RFI from a regulatory point of view, with regards to preventing and correcting harmful interference, linked to the International Telecommunication Union, and from a technical point of view, with technical procedures, workflows and innovative technology solutions for preventing and mitigating RFI. Finally, emerging technology trends and future directions are presented.
{"title":"Management of radio-frequency interferences for space traffic management: Current regulations, operations practice, technology mitigation solutions and future trends","authors":"Paolo Marzioli , Daniel Oltrogge , Claudiu Mihai Taiatu , Mark A. Skinner , Andy Court","doi":"10.1016/j.actaastro.2024.10.005","DOIUrl":"10.1016/j.actaastro.2024.10.005","url":null,"abstract":"<div><div>Radio-Frequency Interference (RFI) has a large impact on the business of commercial satellites communications and will have an increasingly important role in the next years and decades due to the spread of the launched spacecraft population.</div><div>This paper presents the current state-of-the-art for Space Traffic Management -related RFI from a regulatory point of view, with regards to preventing and correcting harmful interference, linked to the International Telecommunication Union, and from a technical point of view, with technical procedures, workflows and innovative technology solutions for preventing and mitigating RFI. Finally, emerging technology trends and future directions are presented.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":""},"PeriodicalIF":3.1,"publicationDate":"2024-10-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142433393","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}
Pub Date : 2024-10-10DOI: 10.1016/j.actaastro.2024.10.018
E. Neefs , A.C. Vandaele , R. De Cock , J. Erwin , S. Robert , I.R. Thomas , S. Berkenbosch , L. Jacobs , P. Bogaert , B. Beeckman , A. Brassine , N. Messios , E. De Donder , D. Bolsée , N. Pereira , P. Tackley , T. Gerya , S. Kögl , P. Kögl , H.-P. Gröbelbauer , J. Jimenez
VenSpec is a spectrometer suite on board ESA's EnVision mission to planet Venus, due for launch in November 2031. VenSpec consists of three spectrometers, VenSpec-M, VenSpec-U and VenSpec-H. VenSpec-H stands for Venus Spectrometer with High resolution. It operates in the near-infrared wavelength range between 1.15 and 2.5 μm and it aims at mapping the near surface atmosphere during the night and the atmosphere above the cloud deck during the day. More specific, VenSpec-H will measure gases related to volcanism and surface changes on Venus. It will perform its measurements by means of nadir observations.
In this paper an overview is given of the main design requirements, followed by a description of the design activities performed during the feasibility study (phase A) and the preliminary definition (phase B1) of the instrument, including mathematical modeling and analysis, and prototyping. Focus is put on the optical working principle of the instrument, where an echelle grating, used as diffractive element, is combined with an inventive combination of filters for spectral band selection.
The design and development of VenSpec-H is done in a consortium under Belgian management and with important contributions from Belgian, Swiss, Spanish, and Dutch research institutes, universities, and industrial partners.
{"title":"VenSpec-H spectrometer on the ESA EnVision mission: Design, modeling, analysis","authors":"E. Neefs , A.C. Vandaele , R. De Cock , J. Erwin , S. Robert , I.R. Thomas , S. Berkenbosch , L. Jacobs , P. Bogaert , B. Beeckman , A. Brassine , N. Messios , E. De Donder , D. Bolsée , N. Pereira , P. Tackley , T. Gerya , S. Kögl , P. Kögl , H.-P. Gröbelbauer , J. Jimenez","doi":"10.1016/j.actaastro.2024.10.018","DOIUrl":"10.1016/j.actaastro.2024.10.018","url":null,"abstract":"<div><div>VenSpec is a spectrometer suite on board ESA's EnVision mission to planet Venus, due for launch in November 2031. VenSpec consists of three spectrometers, VenSpec-M, VenSpec-U and VenSpec-H. VenSpec-H stands for <strong><u>Ven</u></strong>us <strong><u>Spec</u></strong>trometer with <strong><u>H</u></strong>igh resolution. It operates in the near-infrared wavelength range between 1.15 and 2.5 μm and it aims at mapping the near surface atmosphere during the night and the atmosphere above the cloud deck during the day. More specific, VenSpec-H will measure gases related to volcanism and surface changes on Venus. It will perform its measurements by means of nadir observations.</div><div>In this paper an overview is given of the main design requirements, followed by a description of the design activities performed during the feasibility study (phase A) and the preliminary definition (phase B1) of the instrument, including mathematical modeling and analysis, and prototyping. Focus is put on the optical working principle of the instrument, where an echelle grating, used as diffractive element, is combined with an inventive combination of filters for spectral band selection.</div><div>The design and development of VenSpec-H is done in a consortium under Belgian management and with important contributions from Belgian, Swiss, Spanish, and Dutch research institutes, universities, and industrial partners.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 178-201"},"PeriodicalIF":3.1,"publicationDate":"2024-10-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534897","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}
Pub Date : 2024-10-10DOI: 10.1016/j.actaastro.2024.10.002
Manu H. Nair , Mini C. Rai , Mithun Poozhiyil
Robotics, Automation, and Autonomous Systems form the cornerstone for ambitious large-scale in-orbit missions. However, the harsh space environment presents unique challenges that demand careful consideration. Key requirements for next-generation space manipulators include dexterity, modularity, redundancy, workspace enhancement, and autonomous mobility. To address the limitations of conventional walking manipulators, this paper presents a novel seven-degrees-of-freedom dexterous End-Over-End Walking Robot (E-Walker) for future In-Space Assembly and Manufacturing missions. The use-case considers the in-situ robotic assembly of the primary mirror of a 25 m Large Aperture Space Telescope (LAST). This research is timely given the constant clamour for high-resolution astronomy and earth observation within the space community and serves as a baseline for future missions with telescopes of much larger aperture, missions requiring assembly of space stations, and solar-power generation satellites to list a few. The paper starts by eliciting the mission Concept of Operations (ConOps) for the in-situ assembly of a 25 m LAST utilising the next-generation E-Walker space manipulator, which serves as a narrative backdrop to present the feasibility analysis. Comparing the power, time, control and motion planning complexities of eleven mission ConOps, the trade-off analysis shortlists a potential mission scenario. Furthermore, operational assessments of two potential mission ConOps are compared to estimate the time required for assembly. The study offers new insights into mission time requirements for these scenarios, shedding light on multi-robot collaborative task-sharing and practical applicability of the E-Walker in executing complex and high-value in-orbit assembly missions.
{"title":"The new era of walking manipulators in space: Feasibility and operational assessment of assembling a 25 m Large Aperture Space Telescope in orbit","authors":"Manu H. Nair , Mini C. Rai , Mithun Poozhiyil","doi":"10.1016/j.actaastro.2024.10.002","DOIUrl":"10.1016/j.actaastro.2024.10.002","url":null,"abstract":"<div><div>Robotics, Automation, and Autonomous Systems form the cornerstone for ambitious large-scale in-orbit missions. However, the harsh space environment presents unique challenges that demand careful consideration. Key requirements for next-generation space manipulators include dexterity, modularity, redundancy, workspace enhancement, and autonomous mobility. To address the limitations of conventional walking manipulators, this paper presents a novel seven-degrees-of-freedom dexterous End-Over-End Walking Robot (E-Walker) for future In-Space Assembly and Manufacturing missions. The use-case considers the in-situ robotic assembly of the primary mirror of a 25 m Large Aperture Space Telescope (LAST). This research is timely given the constant clamour for high-resolution astronomy and earth observation within the space community and serves as a baseline for future missions with telescopes of much larger aperture, missions requiring assembly of space stations, and solar-power generation satellites to list a few. The paper starts by eliciting the mission Concept of Operations (ConOps) for the in-situ assembly of a 25 m LAST utilising the next-generation E-Walker space manipulator, which serves as a narrative backdrop to present the feasibility analysis. Comparing the power, time, control and motion planning complexities of eleven mission ConOps, the trade-off analysis shortlists a potential mission scenario. Furthermore, operational assessments of two potential mission ConOps are compared to estimate the time required for assembly. The study offers new insights into mission time requirements for these scenarios, shedding light on multi-robot collaborative task-sharing and practical applicability of the E-Walker in executing complex and high-value in-orbit assembly missions.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1061-1071"},"PeriodicalIF":3.1,"publicationDate":"2024-10-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142539188","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.011
Vitaly E. Borisov, Tatiana V. Konstantinovskaya, Alexander E. Lutskii
Numerical simulation of supersonic flow around sequentially arranged wings, which include a vortex generator wing and a downstream main wing, have been conducted. Aerodynamic configurations of this type can be found on various re-entry spacecraft. This study investigates the influence of vortex structures on the magnitude and distribution of pressure, temperature, and heat fluxes on the surface of the main wing. The supersonic incoming flow at Mach number M∞ = 3 and Reynolds number ReL = 1∗107 with different attack angles (10° - 20°) of the generator wing and the main wing is considered. It has been established that under certain parameter values, there is a reduction in the drag experienced by the main wing and a decrease in temperature on its surface.
{"title":"The influence of vortex structures on the aerothermodynamics of aerospace vehicles","authors":"Vitaly E. Borisov, Tatiana V. Konstantinovskaya, Alexander E. Lutskii","doi":"10.1016/j.actaastro.2024.10.011","DOIUrl":"10.1016/j.actaastro.2024.10.011","url":null,"abstract":"<div><div>Numerical simulation of supersonic flow around sequentially arranged wings, which include a vortex generator wing and a downstream main wing, have been conducted. Aerodynamic configurations of this type can be found on various re-entry spacecraft. This study investigates the influence of vortex structures on the magnitude and distribution of pressure, temperature, and heat fluxes on the surface of the main wing. The supersonic incoming flow at Mach number M<sub>∞</sub> = 3 and Reynolds number Re<sub><em>L</em></sub> = 1∗10<sup>7</sup> with different attack angles (10° - 20°) of the generator wing and the main wing is considered. It has been established that under certain parameter values, there is a reduction in the drag experienced by the main wing and a decrease in temperature on its surface.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1031-1038"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142442821","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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