Acta Astronautica最新文献_第3页

A survey of research on lunar dust dispersal due to rocket plume impingement

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-22 DOI: 10.1016/j.actaastro.2024.11.021

Jinyoung Kim, Jinhwi Kim, Bok Jik Lee

引用次数: 0

Propulsive landing of launchers’ first stages with Deep Reinforcement Learning

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-22 DOI: 10.1016/j.actaastro.2024.11.028

Davide Iafrate , Andrea Brandonisio , Robert Hinz , Michèle Lavagna

{"title":"Propulsive landing of launchers’ first stages with Deep Reinforcement Learning","authors":"Davide Iafrate , Andrea Brandonisio , Robert Hinz , Michèle Lavagna","doi":"10.1016/j.actaastro.2024.11.028","DOIUrl":"10.1016/j.actaastro.2024.11.028","url":null,"abstract":"<div><div>The planetary landing problem is gaining relevance in the space sector, spanning a wide range of applications from unmanned probes landing on other planetary bodies to reusable first and second stages of launcher vehicles. In the existing methodology there is a lack of flexibility in handling complex non-linear dynamics, in particular in the case of non-convexifiable constraints. It is therefore crucial to assess the performance of novel techniques and their advantages and disadvantages. The purpose of this work is the development of an integrated 6-DOF guidance and control approach based on reinforcement learning of deep neural network policies for fuel-optimal planetary landing control, specifically with application to a launcher first-stage terminal landing, and the assessment of its performance and robustness. 3-DOF and 6-DOF simulators are developed and encapsulated in MDP-like (Markov Decision Process) industry-standard compatible environments. Particular care is given in thoroughly shaping reward functions capable of achieving the landing both successfully and in a fuel-optimal manner. A cloud pipeline for effective training of an agent using a PPO reinforcement learning algorithm to successfully achieve the landing goal is developed.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"227 ","pages":"Pages 40-56"},"PeriodicalIF":3.1,"publicationDate":"2024-11-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744611","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}

引用次数: 0

Analytic solution for combined in-plane and out-of-plane spacecraft formation reconfiguration with passive collision avoidance

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-20 DOI: 10.1016/j.actaastro.2024.11.024

Chenglong Xu , Chengxi Zhang , Jihe Wang

引用次数: 0

Simulation of rarefied gas flow inside the satellite air intake in ultra-low Earth orbit

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-20 DOI: 10.1016/j.actaastro.2024.11.041

Artem Yakunchikov , Vasily Kosyanchuk , Alexander Filatyev , Alexander Golikov

引用次数: 0

In-orbit system identification of a flexible satellite with variable mass using dual Unscented Kalman filters

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-16 DOI: 10.1016/j.actaastro.2024.11.014

Alex J. Elliott , Aydin Nakhaeezadeh Gutierrez , Leonard Felicetti , Luca Zanotti Fragonara

{"title":"In-orbit system identification of a flexible satellite with variable mass using dual Unscented Kalman filters","authors":"Alex J. Elliott , Aydin Nakhaeezadeh Gutierrez , Leonard Felicetti , Luca Zanotti Fragonara","doi":"10.1016/j.actaastro.2024.11.014","DOIUrl":"10.1016/j.actaastro.2024.11.014","url":null,"abstract":"<div><div>Modern space mission concepts are increasingly dependent on the robust and reliable deployment of spacecraft with large appendages, such as antennas, booms or solar panels. Such deployment requires the ability to properly capture and control the coupled system dynamics, which requires accurate in-orbit system identification of the mass and structural properties. This paper utilises dual Unscented Kalman filters (DUKF) to develop an online system identification strategy that captures both the structural and mass properties, and the attitude and orbit dynamics. The dynamics of the flexible multibody problem are derived from the Lagrangian equations, with the flexible body characteristics modelled with finite element software. A genetic algorithm is used to optimise the accelerometer placement, and hence improve the DUKF performance. We demonstrate that this approach can accurately capture the coupled attitude, orbit, and structural dynamics, as well as being able to provide in-orbit updates for mass properties such as the moment of inertia. The methodology is explored for two illustrative cases: one in which the initial moment of inertia is incorrectly characterised, one in which the moment of inertia changes with time. In both cases, the DUKF approach captures both the system dynamics and the mass properties, which are captured with an error of less than 1%.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 71-86"},"PeriodicalIF":3.1,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744106","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}

引用次数: 0

MaiaSpace: Sustainability applied to the development of a semi-reusable solution for space mobility

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-16 DOI: 10.1016/j.actaastro.2024.11.027

Jérôme Vila , Antoinette Ott , Jérémie Hassin , Christophe Bonnal

{"title":"MaiaSpace: Sustainability applied to the development of a semi-reusable solution for space mobility","authors":"Jérôme Vila , Antoinette Ott , Jérémie Hassin , Christophe Bonnal","doi":"10.1016/j.actaastro.2024.11.027","DOIUrl":"10.1016/j.actaastro.2024.11.027","url":null,"abstract":"<div><div>MaiaSpace is a European NewSpace company aiming at developing a mini launcher to meet the future of the satellite market. Founded in 2022, the company is preparing for the maiden launch at the end of 2025. MaiaSpace is actively working towards environmental mitigation of its launch service through the implementation of a Life Cycle Assessment methodology from an early stage. Design choices for environmental mitigation include reusability of the first stage, the use of bio-methane as fuel, and the adding of a kick-stage for a performance increase or in-orbit services. This article aims to justify these choices in both fields of competitivity and sustainability.</div><div>On the one hand, while having two markets addressed by one launcher boosts competitiveness, environmental impact remains unclear, except for the resource depletion indicator, that shows clear benefits. On the other hand, if choosing bio-methane over fossil-based methane increases costs, it theoretically leads to environmental benefits. In addition, by choosing a methane-fuelled launcher, the launch phase climate change impact could be reduced by as much as 94 % compared to a similar RP-1 fuelled one, although more research is needed to confirm. Finally, the kick-stage allows a sharp increase of the payload capacity, improving both environmental performance (measured per ton of payload sent into orbit), as well as service flexibility, in addition to its business potential for in-orbit services.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 31-38"},"PeriodicalIF":3.1,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744168","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}

引用次数: 0

Improving landing stability and terrain adaptability in Lunar exploration with biomimetic lander design and control 利用仿生着陆器的设计和控制提高月球探测的着陆稳定性和地形适应性

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-14 DOI: 10.1016/j.actaastro.2024.11.020

Jinyao Zhu , Jia Ma , Jinbao Chen , Chen Wang , Yunfeng Li , Zhihao Fan , Chaoyu Lu

{"title":"Improving landing stability and terrain adaptability in Lunar exploration with biomimetic lander design and control","authors":"Jinyao Zhu , Jia Ma , Jinbao Chen , Chen Wang , Yunfeng Li , Zhihao Fan , Chaoyu Lu","doi":"10.1016/j.actaastro.2024.11.020","DOIUrl":"10.1016/j.actaastro.2024.11.020","url":null,"abstract":"<div><div>Traditional lunar landers face challenges due to strict flatness requirements at landing sites and the need to avoid complex terrains, which significantly limits their exploration capabilities and success rates. Additionally, their focus on stable landings often compromises their maneuverability, reducing adaptability to various lunar terrains. To address these issues, this study introduces a walkable cat-legged lander (WCLL) inspired by feline landing mechanisms. The WCLL integrates features from both traditional landers and rovers, enabling it to perform high-load landings and navigate effectively across diverse lunar surfaces. It utilizes magnetorheological dampers to dissipate impact energy and employs a soft-landing control method, achieving stable landings under various conditions, including vertical velocities of 3 m/s, payloads of 1280 kg, slopes of 15°, and horizontal disturbances at speeds of 2 m/s. Compared to the Chang'e−3 lander, the WCLL shows a 66.7 % increase in slope adaptability and a 22.6 % improvement in resistance to horizontal disturbances. Finally, experimental validation confirms the accuracy of the simulation model, providing valuable insights for future lunar exploration robot design.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 860-875"},"PeriodicalIF":3.1,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702666","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}

引用次数: 0

A deep neural network framework with Analytic Continuation for predicting hypervelocity fragment flyout from satellite explosions

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-13 DOI: 10.1016/j.actaastro.2024.10.070

Katharine E. Larsen, Tahsinul H. Tasif, Riccardo Bevilacqua

{"title":"A deep neural network framework with Analytic Continuation for predicting hypervelocity fragment flyout from satellite explosions","authors":"Katharine E. Larsen, Tahsinul H. Tasif, Riccardo Bevilacqua","doi":"10.1016/j.actaastro.2024.10.070","DOIUrl":"10.1016/j.actaastro.2024.10.070","url":null,"abstract":"<div><div>Hypervelocity breakup events contribute to the rapidly growing population of space debris orbiting Earth. To ensure a safe environment for future space missions, it is crucial to accurately characterize resulting fragments, which constitute a major portion of the orbital population but are often too small for conventional tracking methods. Currently, the Space Surveillance Network tracks satellites and debris within a specific altitude range and releases the data publicly as Two-Line Elements, though these datasets are limited in both size and accuracy. To supplement Two-Line Element data, this paper presents a novel Deep Neural Network approach to estimate orbital elements of hypervelocity fragments resulting from simulated satellite explosions. It employs initial conditions collected from realistic terrestrial explosions considered to be relative to 5 different detonation points on the polar orbit of the weather satellite, NOAA-16, to model the initial states of debris fragments immediately following an explosion. The debris trajectories are then propagated using a high-precision semi-analytic integration method, Analytic Continuation, considering <span><math><mrow><msub><mrow><mi>J</mi></mrow><mrow><mn>2</mn></mrow></msub><mo>−</mo><msub><mrow><mi>J</mi></mrow><mrow><mn>6</mn></mrow></msub></mrow></math></span> zonal gravitational terms and Earth’s atmospheric drag perturbations. The collected data is used to train a Deep Neural Network for each of the orbital elements. Finally, a testing data set is used to validate the results, finding that this technique accurately estimates most of the orbital elements, but is not suited to predict the true anomaly of the fragments. Therefore, K-Nearest Neighbor regression is utilized instead to predict the nature of the final orbital element.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 87-101"},"PeriodicalIF":3.1,"publicationDate":"2024-11-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744107","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}

引用次数: 0

Analysis and control of the equilibrium position in bare electrodynamic tether systems

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-13 DOI: 10.1016/j.actaastro.2024.11.006

Mingze Xie , Hongshi Lu , Changqing Wang , Aijun Li , Yuriy Zabolotnov

{"title":"Analysis and control of the equilibrium position in bare electrodynamic tether systems","authors":"Mingze Xie , Hongshi Lu , Changqing Wang , Aijun Li , Yuriy Zabolotnov","doi":"10.1016/j.actaastro.2024.11.006","DOIUrl":"10.1016/j.actaastro.2024.11.006","url":null,"abstract":"<div><div>This study focuses on the calculation of the equilibrium position of the bare electrodynamic tether (BEDT) and the implementation of stable control during the de-orbiting process. A novel method for calculating the equilibrium position of the BEDT system is proposed, utilizing integral variable substitution. This approach provides an analytical expression for the equilibrium position, thereby addressing the limitations of numerical curve-fitting methods and facilitating further dynamic analysis and controller design. To address the influence of variations in geomagnetic field strength and electron density on the tether attitude during deorbiting, a sliding mode controller based on prescribed performance is designed to stabilize the BEDT around its equilibrium position by adjusting the tether length. This adjustment simultaneously regulates angular momentum and current on the tether. In contrast to conventional current switching methods, the proposed strategy effectively mitigates undesired transient responses and additional system disturbances, and accurately stabilizing the BEDT system around the equilibrium position. Numerical simulations show that the analytical equilibrium calculations closely match the nonlinear model, with an error margin of less than 5%. Additionally, the tether length adjustment strategy successfully stabilizes the system around the equilibrium position, achieving an angular deviation of less than 0.2 degrees and enhanced deorbit efficiency compared to the current switching control method.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 60-70"},"PeriodicalIF":3.1,"publicationDate":"2024-11-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744169","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}

引用次数: 0

Habitat site selection on Mars: Suitability analysis and mapping

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-11-13 DOI: 10.1016/j.actaastro.2024.11.019

Sijie Zhu , Bing Zhao , Yu Yan , Xing Shi

{"title":"Habitat site selection on Mars: Suitability analysis and mapping","authors":"Sijie Zhu , Bing Zhao , Yu Yan , Xing Shi","doi":"10.1016/j.actaastro.2024.11.019","DOIUrl":"10.1016/j.actaastro.2024.11.019","url":null,"abstract":"<div><div>Growing interest in extraterrestrial colonization has increasingly centered on Mars, bolstered by extensive environmental data from Mars exploration missions. However, the planet's harsh conditions—including extreme temperatures, dust storms, varied terrain, high radiation, and scarce water resources—pose significant challenges to selecting suitable sites for human habitation. This study evaluated potential habitats on Mars by considering factors such as temperature, wind, radiation, terrain, dust, and water ice. Through the development of comprehensive suitability maps, we identified potential areas for future human construction, primarily concentrated in south Arcadia Planitia, south Utopia Planitia, and the junction of Acidalia Planitia and Arabia Terra. The analysis revealed that, except for Hellas Planitia, most of Mars' southern hemisphere is largely unsuitable for long-term human habitation. This work establishes a continually expandable novel framework and offers a new perspective for interdisciplinary approaches in studying human habitation environments in the context of future Martian exploration. Moreover, it can be adjusted based on different future technological scenarios.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 1-22"},"PeriodicalIF":3.1,"publicationDate":"2024-11-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142744137","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}

引用次数: 0