Acta Astronautica最新文献

{"title":"Comparative study on kinetic energy dissipation of debris clouds between aluminum plates and Kevlar fabric","authors":"Duo Zhang,&nbsp;Gongshun Guan,&nbsp;Jianing Zhang","doi":"10.1016/j.actaastro.2025.09.058","DOIUrl":"10.1016/j.actaastro.2025.09.058","url":null,"abstract":"<div><div>Kevlar woven fabric has been extensively utilized as an intermediate layer in space debris shielding configurations. This investigation focuses on stuffed Whipple shields and employs a combined experimental and numerical simulation approach to systematically compare the protective performance differences between aluminum plates and Kevlar woven fabric as intermediate layers. Hypervelocity impact experiments were performed at velocities ranging from 3.0 to 4.4 km/s, yielding impact damage results for shielding configurations incorporating both materials. By integrating numerical simulations, the study quantitatively analyzed the enhancement effects of the two materials on protective performance based on debris cloud energy distribution, maximum fragment mass, and energy-location joint distribution of fragments. The study elucidates the mechanistic distinctions between the two materials and identifies their respective optimal velocity regimes, providing insights for material selection in shielding configurations.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 940-956"},"PeriodicalIF":3.4,"publicationDate":"2025-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145220943","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":"Segmented hybrid impedance wave based control for hyper-redundant space manipulators","authors":"Mohamed. Chihi,&nbsp;Chourouk. Ben Hassine,&nbsp;Quan. Hu","doi":"10.1016/j.actaastro.2025.09.062","DOIUrl":"10.1016/j.actaastro.2025.09.062","url":null,"abstract":"<div><div>Hyper-Redundant Space Manipulators (HRSMs) have become a pivotal solution for space operations, offering a safer and more economical alternative to the risks and costs of astronaut-led extravehicular activities. Initially designed to navigate and avoid obstacles, these manipulators have advanced significantly, now capable of actively interacting with their environment. However, traditional control methods face significant challenges in managing multiple contact points, often compromising stability in the dynamic and unpredictable conditions of microgravity. To address these limitations, this paper proposes a novel segmented hybrid impedance wave-based control strategy for HRSMs operating in multi-contact environments. Integrating wave-based control with hybrid impedance control, this approach leverages mechanical flexibility and bidirectional wave propagation to enable robust management of multiple contact points, effectively mitigate sensor noise, and ensure smooth transitions in contact forces. The wave-based control framework simplifies implementation by reducing the need for complex system modeling while simultaneously achieving precise position control and active vibration damping. The full non-linear dynamics of the HRSM system are modeled using Kane's method, accounting for both free-space motion and constrained operational phases. Extensive numerical simulations validate the proposed strategy, demonstrating its effectiveness in maintaining stable multi-point contact interactions and absorbing residual vibrations and outperforming the impedance control architecture. These results underline the potential of the proposed control strategy to enhance the reliability and performance of HRSMs, paving the way for advanced applications in space robotic operations.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 825-838"},"PeriodicalIF":3.4,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145220946","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 Burn-Coast-Burn Pointing Algorithm (BCBPA) for high-precision orbit insertion missions of solid rockets","authors":"Qi An,&nbsp;Ran Zhang,&nbsp;Huifeng Li","doi":"10.1016/j.actaastro.2025.09.052","DOIUrl":"10.1016/j.actaastro.2025.09.052","url":null,"abstract":"<div><div>This paper discusses a solid rocket guidance algorithm applied to orbit insertion missions. Providing continuous and smooth guidance commands to satisfy both terminal five orbit elements and propellant exhaustion constraints is the main difficulty to be solved. Dispersions in initial states and rocket engine parameters are also necessary to be addressed when high-precision is required. To simultaneously address the above issues, this paper proposes a Burn-Coast-Burn Pointing Algorithm (BCBPA) by introducing a Burn-Coast-Burn (BCB) mode in the well-established Pointing Algorithm (PA). By adding a coasting time as a new control parameter, the guidance problem is then converted to an energy management issue for a two-stage solid rocket. Subsequently, an N-BCBPA is proposed to address energy management issues for multi-stage solid rockets, thus providing converged guidance commands when the presented BCBPA fails. Based on a recursive algorithm, the N-BCBPA transforms the guidance problem of N-stage solid rockets into N-1 sub-problems under the BCB mode and solves them in order, thereby improving the robustness of the BCBPA against dispersions. Numerical simulations verify that the BCBPA is capable of guiding a two-stage solid rocket to the target orbit while satisfying propellant exhaustion constraints, and the N-BCBPA shows better robustness against dispersions than the BCBPA.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 1015-1029"},"PeriodicalIF":3.4,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145220941","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":"Transformer-based anomaly detection for satellite telemetry data","authors":"Asma Fejjari ,&nbsp;Alexis Delavault ,&nbsp;Robert Camilleri ,&nbsp;Gianluca Valentino","doi":"10.1016/j.actaastro.2025.09.035","DOIUrl":"10.1016/j.actaastro.2025.09.035","url":null,"abstract":"<div><div>Time series anomaly detection can help identify serious issues in complex systems, and can potentially reduce the risk of failures or operational disruptions by providing advance warning. Over the past decades, several methods, ranging from out-of-limit techniques to machine learning models have been developed to automate anomaly detection for satellite telemetry data. In recent years, transformer-based architectures have demonstrated considerable success in the problem of time series anomaly detection. In this paper, we present and compare the performance of various transformer architectures in detecting anomalies in satellite telemetry data, including the recently published ESA OPS-SAT telemetry dataset, and show how these architectures outperform the benchmarks conducted on this dataset.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 739-745"},"PeriodicalIF":3.4,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158844","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":"Where shall we live on the Moon? Multi-factor site selection and scenario-based planning for permanent lunar habitats","authors":"Siyan Wang ,&nbsp;Peixian Li ,&nbsp;Xiaoyu Wang ,&nbsp;Lan Luo ,&nbsp;Xing Shi","doi":"10.1016/j.actaastro.2025.09.066","DOIUrl":"10.1016/j.actaastro.2025.09.066","url":null,"abstract":"<div><div>The Moon is a prime target for permanent human settlement due to its proximity, resource availability, and geological stability. However, habitat suitability assessment is complicated by multiple interacting environmental factors. To evaluate lunar habitat suitability, we first identified eight key factors: temperature, topography, solar illumination, construction minerals, photovoltaic minerals, lunar dust activity, water resources, and radiation. And quantified them using data from LOLA, the Chang'e−2 microwave radiometer, and γ-ray spectrometer, then developed single-factor suitability indices and mapped their spatial distributions. We then evaluated six application scenarios relevant to a lunar base: scientific research base, residence, photovoltaic zones, water-supply hubs, transportation routes, and spacecraft landing sites. Each was assessed using a composite suitability index derived via the Analytic Hierarchy Process (AHP), which weighted the influence of the eight factors. High-suitability areas were mainly located in mid-to low-latitude mare plains. Multi-factor analysis identified three promising regions that meet the suitability criteria across all six scenarios. Region 1 lies within the mare plain enclosed by the Pytheas crater cluster (14.52° N–18.25° N, 16.24° W–20.26° W), covering 11287 <span><math><mrow><msup><mrow><mspace></mspace><mi>k</mi><mi>m</mi></mrow><mn>2</mn></msup></mrow></math></span>. Region 2 is situated in the mare plain enclosed by the Gambart crater cluster (5.08° N–1.77° S, 10.29° W–18.02° W), covering 48613 <span><math><mrow><msup><mrow><mspace></mspace><mi>k</mi><mi>m</mi></mrow><mn>2</mn></msup></mrow></math></span>. Region 3 occupies the mare plain enclosed by the Parry crater cluster (6.39° S–11.02° S, 10.29° W–14.28° W), covering 8480 <span><math><mrow><msup><mrow><mspace></mspace><mi>k</mi><mi>m</mi></mrow><mn>2</mn></msup></mrow></math></span>. Based on these findings, we propose a spatial layout for a multifunctional lunar base, offering a strategic foundation for long-term lunar habitation.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 804-824"},"PeriodicalIF":3.4,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145220944","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":"Mixing enhancement in direct numerical simulation of shock wave-mixing layer interaction for aerospace propulsion","authors":"Tao Yu,&nbsp;Qian Chen","doi":"10.1016/j.actaastro.2025.09.059","DOIUrl":"10.1016/j.actaastro.2025.09.059","url":null,"abstract":"<div><div>Efficient mixing of fuel and oxidizer in combustor is a key challenge in the design of high speed propulsion systems such as scramjets. Shock wave, which is commonly present in combustor, has been identified as a promising candidate for enhancing mixing through their interaction with supersonic mixing layer. This study employs direct numerical simulation (DNS) to investigate the interaction between an oblique shock and a supersonic mixing layer, and its influence on flow dynamics and mixing efficiency. A high-order finite difference scheme is used to solve the three-dimensional compressible Navier-Stokes equations, simulating the evolution of an H₂/N₂ and O₂/N₂ mixing layer under a convective Mach number of <em>M</em>c = 0.43. The analysis focuses on species transport, vorticity evolution, and turbulence statistics. Results show that the oblique shock undergoes refraction and reflection upon intersecting the mixing layer, significantly modifying the mean velocity profile—from a steep gradient to a smoother S-shaped curve. The shock-induced disturbance greatly promotes the diffusion of H₂/N₂ and O₂/N₂, resulting in accelerated mixing layer thickening. Initially large-scale vortices governed by Kelvin-Helmholtz instability break down into smaller structures under shock interaction, yielding a more diffused vorticity field and highly disordered turbulence. The shock further strengthens turbulent momentum and energy exchange via enhanced shear production, baroclinic vorticity generation, and vortex fragmentation, leading to a stepwise increase in Reynolds stresses and turbulent kinetic energy downstream. This study provides valuable insights into shock-driven mixing enhancement and offers theoretical and numerical support for optimizing mixing performance in supersonic combustors.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 839-855"},"PeriodicalIF":3.4,"publicationDate":"2025-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145221070","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":"ALPER: Vision based absolute localization for planetary exploration rovers - Statistical analysis of complementary approaches","authors":"Philemon Fieschi,&nbsp;Loic Le Cabec,&nbsp;Vincent Delort,&nbsp;Thierry Germa,&nbsp;Emma Villanueva-Rourera","doi":"10.1016/j.actaastro.2025.09.041","DOIUrl":"10.1016/j.actaastro.2025.09.041","url":null,"abstract":"<div><div>Future surface planetary missions, such as sample returns or base construction, require advanced Guidance, Navigation, and Control systems for long-distance autonomous operations. Current systems depend on relative localization, which accumulates error over extended distances. Absolute localization algorithms, akin to GNSS on Earth, are crucial for accurate, independent pose corrections.</div><div>Focusing initially on the Martian context and the availability of satellite imagery with 0.3 m/px resolution, the ALPER project developed three absolute localization algorithms: CM (Constellation Matching) using rock detection, DICOR (Dense Image Co-registration) aligning orthomosaics with orbital images, and SkyM (Skyline Matching) for horizon skyline comparison. These methods build upon landmark matching, dense image matching, and horizon data alignment techniques, introducing improvements in both the data processing and matching stages.</div><div>CM and DICOR were evaluated through Monte Carlo simulations and field trials in the Bardenas Reales, achieving localization accuracy below 0.6m under nominal conditions, and within the 1.25m criteria in 94 %–99 % of the cases, even with initial offsets of up to 20 m. The algorithms demonstrated complementary strengths: CM was effective across varying illumination conditions, while DICOR proved robust to rock density. These solutions have shown robustness, readiness, and high effectiveness for future planetary missions, reaching TRL6 maturity. SkyM obtained heading errors under 2° and position errors around 5 m, indicating promising potential for further development to increase its maturity level.</div><div>Preliminary results are also presented regarding the evaluation and adaptation of these localization methodologies to the lunar South Pole context, characterized by harsh illumination conditions. Tests are realized on a simulated realistic lunar dataset, and the method’s performances are compared to those obtained on the Martian context. The study then introduces advancements to their design, with the key improvement being the detection and use of craters as landmarks. First functional tests demonstrate that this enhancement extends the method’s operational domain, increasing the amount of estimations and overall accuracy.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 706-723"},"PeriodicalIF":3.4,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158840","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 Pontryagin Neural Network application to tracklets correlation of optical observations","authors":"Luca Ramponi ,&nbsp;Andrea D’Ambrosio ,&nbsp;Riccardo Cipollone ,&nbsp;Alessia De Riz ,&nbsp;Roberto Furfaro ,&nbsp;Vishnu Reddy ,&nbsp;Pierluigi Di Lizia","doi":"10.1016/j.actaastro.2025.09.032","DOIUrl":"10.1016/j.actaastro.2025.09.032","url":null,"abstract":"<div><div>As activity occurring in the region beyond the geostationary belt continues to grow, the number of satellites and space debris in this area is expected to rise significantly. As a direct consequence, the need of reliable methods to identify, correlate and catalog objects in this region will play a pivotal role to ensure the safety of space operations. This paper proposes a method based on Pontryagin Neural Networks (PoNNs), a specialized type of Physics-Informed Neural Networks (PINNs) designed to solve optimal control problems. By applying the Extreme Theory of Functional Connections, which combines the advantages of PINNs with the Theory of Functional Connections, the PoNN framework approximates the problem’s unknowns through a single-layer feed-forward neural network. The correlation problem is addressed by formulating an energy-optimal control problem that links two tracklets, under the assumption that the objects are non-maneuvering. When a successful correlation is achieved, the resulting solution corresponds to a ballistic trajectory that minimizes control effort. The Mahalanobis distance is then used to evaluate the correlation, which includes residuals on the data, the computed fuel cost associated to the optimal trajectory and the residuals on the physics. As a secondary goal, Initial Orbit Determination capabilities of the method are also investigated. The developed algorithm is validated using both simulated and real angles-only observations of objects governed by a two-body dynamical model. The real optical measurements, consisting of right ascension and declination data, were supplied by the telescopes operated by the Space4 Center at The University of Arizona.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 580-597"},"PeriodicalIF":3.4,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145119413","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":"On-orbit evaluation of variable-shape satellite attitude dynamics under atmospheric drag torque and gravity gradient torque","authors":"Kiyona Miyamoto ,&nbsp;Toshihiro Chujo ,&nbsp;Kei Watanabe ,&nbsp;Saburo Matunaga","doi":"10.1016/j.actaastro.2025.09.003","DOIUrl":"10.1016/j.actaastro.2025.09.003","url":null,"abstract":"<div><div>In low-Earth orbit, aerodynamic orbit control can be achieved by changing a satellite’s cross-sectional area or angle of attack. For this purpose, the satellite is required to maintain a prescribed attitude with respect to the atmospheric flow. However, aerodynamic forces can cause perturbing torques if the satellite’s attitude is not aligned with the atmospheric flow, which can make it difficult to maintain the target orientation. This issue is particularly pronounced for satellites with large cross-sectional areas or those in low-inclination orbits, where the directional limitations of magnetic torquers are more severe. To address these limitations, we propose an attitude control system that utilizes a variable-shape satellite and equilibrium points. This method enables the equilibrium point to be shifted to an arbitrary attitude by dynamically changing the satellite’s shape. Consequently, disturbance torques can be minimized at the desired attitude, expanding the applicability of aerodynamic orbit control to a wider range of satellite sizes and orbital conditions. This study evaluates attitude dynamics around the equilibrium point to demonstrate the feasibility of the proposed system in an actual orbital environment. The proposed strategy is demonstrated on orbit via the HIBARI satellite, a previously developed 50-kg-class microsatellite, and the experimental results are discussed. By changing the satellite’s shape and observing its attitude motion without active control on orbit, the effects of shape change on attitude dynamics are evaluated and disturbance-related parameters are estimated. Furthermore, the residual magnetic moment is identified as the primary factor that disturbs the ideal oscillatory motion around the equilibrium point. Under the assumption that the residual magnetic moment is properly managed, the attitude dynamics around the equilibrium point are evaluated based on on-orbit data. The results show oscillatory motion around the equilibrium point, demonstrating the applicability of the proposed system in orbit.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 873-888"},"PeriodicalIF":3.4,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145221071","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":"The ionizing particle shielding capability of multi-functional high-strength and low-Z composites in low earth orbit","authors":"Jarrod Moonen ,&nbsp;Andrea Mazzanti ,&nbsp;Jafar Shojaii ,&nbsp;Simon Barter ,&nbsp;Shannon Ryan ,&nbsp;Crystal Forrester ,&nbsp;Pier Marzocca ,&nbsp;Alex Shekhter","doi":"10.1016/j.actaastro.2025.08.055","DOIUrl":"10.1016/j.actaastro.2025.08.055","url":null,"abstract":"<div><div>The ionization shielding performance of orbital debris (OD) shields, containing Ultrahigh Molecular Weight Polyethylene (UHMWPE) and aramid, have been investigated. We report the SRIM-2013 numerical simulation of the protons and heavy ions interaction with the shield, based on the description of the orbital ion environment for the analogue satellite NOVASAR-1, validated by experimentation at the Australia National University’s Heavy Ion Accelerator Facility Space Radiation Beamline. The suitability of the structures as ionizing radiation shields were measured on two metrics induced in a notional commercial-off-the-shelf (COTS) Integrated Circuit chip (IC) and Radiation Hardened (RH) IC relative to a no-shield baseline: (1) change in Soft Error Rate (SER) using SER cross-section data for chip architectures published in literature, and (2) change in Total Ionizing Dose (TID) over a notional mission time frame. The analysis finds the all considered shields increase the SER for the RH chip architecture by approx. 20%, while an approx. 1.5% drop in SER independent of the shield constituent materials analysed was predicted in the COTS case. A significant drop in TID (68%–83%) was predicted due to the presence of a shielding structure, with the UHMWPE shield outperforming the aramid shield by a functionally negligible 2%.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"238 ","pages":"Pages 598-607"},"PeriodicalIF":3.4,"publicationDate":"2025-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145119438","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}