Pub Date : 2025-02-04DOI: 10.1016/j.actaastro.2025.02.003
Miranda Fateri , Achim Frick , Constantin Schuler , Tim Schubert , Jochen Hoffmann , Jacobus van der Walt , Michael Salinas
On-site manufacturing using lunar regolith holds significant importance for lunar explorations. Concerning the lunar on-site manufacturing, the layer-wise material extrusion approach enables an automated method for fabricating components from lunar regolith blends. In this study, several samples of Thermoplastic Elastomer (TPU) mixed with lunar regolith simulant (10 %, 20 %, and 30 % by weight) were 3D printed using ARBURG Plastic Freeforming (APF) technology within a feasibility study. The mixture ratio and homogeneity of the lunar regolith simulant distribution within the 3D printed samples was assessed using Thermogravimetric Analysis (TGA) and X-Ray Microscopy (XRM). Mechanical properties of the 3D printed TPU samples as well as the mixed TPU with different mixture ratios of lunar regolith simulant were examined using a universal tensile testing machine. Moreover, the internal structures of the 3D printed samples were analysed using XRM. Finally, several functional samples, such as flexible tubes for lunar applications, were 3D printed to demonstrate the capabilities of the APF process.
利用月球碎石进行现场制造对月球探测具有重要意义。在月球现场制造方面，分层材料挤压法是利用月球碎屑混合料制造部件的自动化方法。在本研究中，在可行性研究中使用 ARBURG 塑料自由成型（APF）技术 3D 打印了几种热塑性弹性体（TPU）与月球碎屑模拟物（按重量计分别为 10%、20% 和 30%）混合的样品。使用热重分析（TGA）和 X 射线显微镜（XRM）评估了三维打印样品中的混合比例和月球岩石模拟物分布的均匀性。使用通用拉伸试验机检测了三维打印热塑性聚氨酯样品以及不同月球碎屑模拟物混合比例的混合热塑性聚氨酯的机械性能。此外，还使用 XRM 分析了 3D 打印样品的内部结构。最后，还三维打印了一些功能性样品，如月球应用的柔性管，以展示 APF 工艺的能力。
{"title":"3D printing of flexible parts out of lunar regolith simulant","authors":"Miranda Fateri , Achim Frick , Constantin Schuler , Tim Schubert , Jochen Hoffmann , Jacobus van der Walt , Michael Salinas","doi":"10.1016/j.actaastro.2025.02.003","DOIUrl":"10.1016/j.actaastro.2025.02.003","url":null,"abstract":"<div><div>On-site manufacturing using lunar regolith holds significant importance for lunar explorations. Concerning the lunar on-site manufacturing, the layer-wise material extrusion approach enables an automated method for fabricating components from lunar regolith blends. In this study, several samples of Thermoplastic Elastomer (TPU) mixed with lunar regolith simulant (10 %, 20 %, and 30 % by weight) were 3D printed using ARBURG Plastic Freeforming (APF) technology within a feasibility study. The mixture ratio and homogeneity of the lunar regolith simulant distribution within the 3D printed samples was assessed using Thermogravimetric Analysis (TGA) and X-Ray Microscopy (XRM). Mechanical properties of the 3D printed TPU samples as well as the mixed TPU with different mixture ratios of lunar regolith simulant were examined using a universal tensile testing machine. Moreover, the internal structures of the 3D printed samples were analysed using XRM. Finally, several functional samples, such as flexible tubes for lunar applications, were 3D printed to demonstrate the capabilities of the APF process.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 779-786"},"PeriodicalIF":3.1,"publicationDate":"2025-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143368334","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 : 2025-02-03DOI: 10.1016/j.actaastro.2025.02.001
Chengwei Bao , Yanen Wang , Garth Pearce , Pan Zhao , Minyan Liu , Ray Tahir Mushtaq
Preparing regolith-based composites for 3D printing is crucial in lunar base construction, leveraging cost-effective and mechanically favorable materials for lunar construction by utilizing lunar regolith as the reinforcing phase. This research focuses on developing lunar regolith simulant as a matrix for 3D printing, which is crucial for in-situ resource utilization on the Moon. Resin-based composites, well-established in aerospace, are explored for their simple manufacturing and robust properties. The formulation involves simulated regolith-based polymer for direct ink writing printing. Rheological properties, including yield stress and plastic viscosity, are characterized across various cementite-sand ratios and printing temperatures. The relationship between extrudability, the time interval of the printing material and its rheological attributes is investigated. Quantitative assessment of material buildability employs three-dimensional scanning of the printed parts. Freeze-thaw cycle tests explore its temperature resilience. The influence of varying the printing infill rate on printing efficiency and the performance of the printed parts was assessed. It was found that modulating the printing infill rate affects the efficiency and performance of parts, with a 1:4 cementite-sand ratio and a 40 print temperature demonstrating optimal printing workability. These findings offer an efficient scheme for the automated production of regolith-based epoxy composites with precise structural, temperature-resistant, and favorable mechanical properties.
{"title":"3D printing of regolith-based epoxy composites with excellent temperature resistance and mechanical strength","authors":"Chengwei Bao , Yanen Wang , Garth Pearce , Pan Zhao , Minyan Liu , Ray Tahir Mushtaq","doi":"10.1016/j.actaastro.2025.02.001","DOIUrl":"10.1016/j.actaastro.2025.02.001","url":null,"abstract":"<div><div>Preparing regolith-based composites for 3D printing is crucial in lunar base construction, leveraging cost-effective and mechanically favorable materials for lunar construction by utilizing lunar regolith as the reinforcing phase. This research focuses on developing lunar regolith simulant as a matrix for 3D printing, which is crucial for in-situ resource utilization on the Moon. Resin-based composites, well-established in aerospace, are explored for their simple manufacturing and robust properties. The formulation involves simulated regolith-based polymer for direct ink writing printing. Rheological properties, including yield stress and plastic viscosity, are characterized across various cementite-sand ratios and printing temperatures. The relationship between extrudability, the time interval of the printing material and its rheological attributes is investigated. Quantitative assessment of material buildability employs three-dimensional scanning of the printed parts. Freeze-thaw cycle tests explore its temperature resilience. The influence of varying the printing infill rate on printing efficiency and the performance of the printed parts was assessed. It was found that modulating the printing infill rate affects the efficiency and performance of parts, with a 1:4 cementite-sand ratio and a 40 <span><math><mrow><mo>°C</mo></mrow></math></span> print temperature demonstrating optimal printing workability. These findings offer an efficient scheme for the automated production of regolith-based epoxy composites with precise structural, temperature-resistant, and favorable mechanical properties.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 787-803"},"PeriodicalIF":3.1,"publicationDate":"2025-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143368333","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 : 2025-02-03DOI: 10.1016/j.actaastro.2025.02.002
V.V. Tyurenkova , P.P. Zakharov , N.N. Smirnov , E.V. Mikhalchenko , E.I. Skryleva , F. Chen , Y. Meng
Droplet-laser interaction is a process being encountered in many Space applications: igniting fuel-oxidant mixtures in engines of different types, removing small debris fragments from low Earth orbits, etc. The present paper describes the results of ground-based research of the process of droplet breakup under the effect of a laser pulse. The laser pulse effect is simulated as momentum applied to the boundary having Gaussian distribution both in space and time. The results of simulations testify that fragmentation of a droplet begins first in the rarefaction wave following the converging compression wave caused by the pulse. The second stage of fragmentation begins on compression wave coming to the opposite border of the droplet and reflecting from the free surface of the droplet in the form of a strong rarefaction wave.
{"title":"Mathematical simulation of a droplet breakup under the effect of a laser pulse","authors":"V.V. Tyurenkova , P.P. Zakharov , N.N. Smirnov , E.V. Mikhalchenko , E.I. Skryleva , F. Chen , Y. Meng","doi":"10.1016/j.actaastro.2025.02.002","DOIUrl":"10.1016/j.actaastro.2025.02.002","url":null,"abstract":"<div><div>Droplet-laser interaction is a process being encountered in many Space applications: igniting fuel-oxidant mixtures in engines of different types, removing small debris fragments from low Earth orbits, etc. The present paper describes the results of ground-based research of the process of droplet breakup under the effect of a laser pulse. The laser pulse effect is simulated as momentum applied to the boundary having Gaussian distribution both in space and time. The results of simulations testify that fragmentation of a droplet begins first in the rarefaction wave following the converging compression wave caused by the pulse. The second stage of fragmentation begins on compression wave coming to the opposite border of the droplet and reflecting from the free surface of the droplet in the form of a strong rarefaction wave.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 772-778"},"PeriodicalIF":3.1,"publicationDate":"2025-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143209659","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 : 2025-01-31DOI: 10.1016/j.actaastro.2025.01.057
Carlos Rubio, Adrián Delgado, Adrián García-Gutiérrez, Alberto Escapa
A new highly parallelizable procedure to integrate perturbed Keplerian motions numerically is presented in this study. It is based on a waveform relaxation method combined with the classic fourth-order Runge–Kutta integrator. Other parallelizable algorithms are already known in the literature, being one of the most widespread the Picard–Chebyshev method. When formulated in Cartesian variables, however, the Picard–Chebyshev method exhibits a limited convergence interval. This limitation requires sequential integration over small segments, reducing the level of parallelization. Alternatively, the equations of motion can be transformed into modified equinoctial elements. The waveform relaxation method proposed here extends both the convergence interval and rate when using Cartesian variables, carrying them to the same level as the modified equinoctial elements. Hence, this method offers an effective parallel algorithm that can be applied directly in Cartesian variables, what simplifies the formulation of the dynamical equations, the integrator structure, and the perturbation force expressions. The convergence and performance of the new waveform relaxation method was validated by performing low-Earth orbit propagations subjected to both conservative and non-conservative perturbations. The evaluation revealed a substantial enhancement with respect to a Picard–Chebyshev method, with a reduction in the Cartesian variables parallel evaluation of the perturbations of approximately 20 times, spanning from 10 to 30 orbit periods and with no significant loss of precision.
{"title":"Waveform relaxation method for parallel orbital propagation","authors":"Carlos Rubio, Adrián Delgado, Adrián García-Gutiérrez, Alberto Escapa","doi":"10.1016/j.actaastro.2025.01.057","DOIUrl":"10.1016/j.actaastro.2025.01.057","url":null,"abstract":"<div><div>A new highly parallelizable procedure to integrate perturbed Keplerian motions numerically is presented in this study. It is based on a waveform relaxation method combined with the classic fourth-order Runge–Kutta integrator. Other parallelizable algorithms are already known in the literature, being one of the most widespread the Picard–Chebyshev method. When formulated in Cartesian variables, however, the Picard–Chebyshev method exhibits a limited convergence interval. This limitation requires sequential integration over small segments, reducing the level of parallelization. Alternatively, the equations of motion can be transformed into modified equinoctial elements. The waveform relaxation method proposed here extends both the convergence interval and rate when using Cartesian variables, carrying them to the same level as the modified equinoctial elements. Hence, this method offers an effective parallel algorithm that can be applied directly in Cartesian variables, what simplifies the formulation of the dynamical equations, the integrator structure, and the perturbation force expressions. The convergence and performance of the new waveform relaxation method was validated by performing low-Earth orbit propagations subjected to both conservative and non-conservative perturbations. The evaluation revealed a substantial enhancement with respect to a Picard–Chebyshev method, with a reduction in the Cartesian variables parallel evaluation of the perturbations of approximately 20 times, spanning from 10 to 30 orbit periods and with no significant loss of precision.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 672-683"},"PeriodicalIF":3.1,"publicationDate":"2025-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143077724","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 : 2025-01-31DOI: 10.1016/j.actaastro.2025.01.048
Jacob Haqq-Misra , Clément Vidal , George Profitiliotis
Earth remains the only known example of a planet with technology, and future projections of Earth’s trajectory provide a basis and motivation for approaching the search for extraterrestrial technospheres. Conventional approaches toward projecting Earth’s technosphere include applications of the Kardashev scale, which suggest the possibility that energy-intensive civilizations may expand to harness the entire energy output available to their planet, host star, or even the entire galaxy. In this study, we argue that the Kardashev scale is better understood as a “luminosity limit” that describes the maximum capacity for a civilization to harvest luminous stellar energy across a given spatial domain, and we note that thermodynamic efficiency will always keep a luminosity-limited technosphere from actually reaching this theoretical limit. We suggest the possibility that an advanced technosphere might evolve beyond this luminosity limit to draw its energy directly from harvesting stellar mass, and we also discuss possible trajectories that could exist between Earth today and such hypothetical “stellivores.” We develop a framework to describe trajectories for long-lived technospheres that optimize their growth strategies between exploration and exploitation, unlike Earth today. We note that analyses of compact accreting stars could provide ways to test the stellivore hypothesis, and we more broadly suggest an expansion of technosignature search strategies beyond those that reside exactly at the luminosity limit.
{"title":"Projections of Earth’s technosphere: Luminosity and mass as limits to growth","authors":"Jacob Haqq-Misra , Clément Vidal , George Profitiliotis","doi":"10.1016/j.actaastro.2025.01.048","DOIUrl":"10.1016/j.actaastro.2025.01.048","url":null,"abstract":"<div><div>Earth remains the only known example of a planet with technology, and future projections of Earth’s trajectory provide a basis and motivation for approaching the search for extraterrestrial technospheres. Conventional approaches toward projecting Earth’s technosphere include applications of the Kardashev scale, which suggest the possibility that energy-intensive civilizations may expand to harness the entire energy output available to their planet, host star, or even the entire galaxy. In this study, we argue that the Kardashev scale is better understood as a “luminosity limit” that describes the maximum capacity for a civilization to harvest luminous stellar energy across a given spatial domain, and we note that thermodynamic efficiency will always keep a luminosity-limited technosphere from actually reaching this theoretical limit. We suggest the possibility that an advanced technosphere might evolve beyond this luminosity limit to draw its energy directly from harvesting stellar mass, and we also discuss possible trajectories that could exist between Earth today and such hypothetical “stellivores.” We develop a framework to describe trajectories for long-lived technospheres that optimize their growth strategies between exploration and exploitation, unlike Earth today. We note that analyses of compact accreting stars could provide ways to test the stellivore hypothesis, and we more broadly suggest an expansion of technosignature search strategies beyond those that reside exactly at the luminosity limit.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 831-838"},"PeriodicalIF":3.1,"publicationDate":"2025-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143360668","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 : 2025-01-30DOI: 10.1016/j.actaastro.2025.01.062
Sergey S. Popovich, Andrey G. Zditovets, Nickolai A. Kiselev, Urii A. Vinogradov
The effect of an incident shock wave on the thermal and dynamic parameters of a supersonic flow on a flat plate is experimentally studied. The shock wave was initiated by a wedge with an opening angle of 12°. The oncoming flow Mach number was 2.48, the total pressure was 530 kPa, the total temperature was 295 K. The Reynolds number based on the boundary layer length from the nozzle throat to the beginning of the test section was at least 2∙107. The static pressure distributions along the flat plate length are presented for two flow patterns with a shock wave and without any disturbances. The 2D2C-PIV method was used to obtain the velocity field in the wind tunnel test section and in the boundary layer separation region on the flat plate. Applying PIV method allowed to register the main characteristics of the interaction region including mean velocity field, incident and reflected shock wave patterns, as well as the boundary layer distortion. The cooling rates of the flat plate were obtained using an infrared camera, which made it possible to calculate the distributions of the temperature recovery factor and the heat transfer coefficient along the flat plate surface. An increase in the temperature recovery factor was noted for flow with an induced shock wave in comparison with an undisturbed flow. At the same time, an uneven distribution of temperature recovery factor and heat transfer coefficient was observed in the separation region. The results of the study can be useful in calculating high-speed channel flows with heat exchange in air- and spacecrafts propulsion systems.
{"title":"Experimental study of aerodynamic heating in the region of an incident shock wave boundary layer interaction","authors":"Sergey S. Popovich, Andrey G. Zditovets, Nickolai A. Kiselev, Urii A. Vinogradov","doi":"10.1016/j.actaastro.2025.01.062","DOIUrl":"10.1016/j.actaastro.2025.01.062","url":null,"abstract":"<div><div>The effect of an incident shock wave on the thermal and dynamic parameters of a supersonic flow on a flat plate is experimentally studied. The shock wave was initiated by a wedge with an opening angle of 12°. The oncoming flow Mach number was 2.48, the total pressure was 530 kPa, the total temperature was 295 K. The Reynolds number based on the boundary layer length from the nozzle throat to the beginning of the test section was at least 2∙10<sup>7</sup>. The static pressure distributions along the flat plate length are presented for two flow patterns with a shock wave and without any disturbances. The 2D2C-PIV method was used to obtain the velocity field in the wind tunnel test section and in the boundary layer separation region on the flat plate. Applying PIV method allowed to register the main characteristics of the interaction region including mean velocity field, incident and reflected shock wave patterns, as well as the boundary layer distortion. The cooling rates of the flat plate were obtained using an infrared camera, which made it possible to calculate the distributions of the temperature recovery factor and the heat transfer coefficient along the flat plate surface. An increase in the temperature recovery factor was noted for flow with an induced shock wave in comparison with an undisturbed flow. At the same time, an uneven distribution of temperature recovery factor and heat transfer coefficient was observed in the separation region. The results of the study can be useful in calculating high-speed channel flows with heat exchange in air- and spacecrafts propulsion systems.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 804-813"},"PeriodicalIF":3.1,"publicationDate":"2025-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143368335","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 : 2025-01-30DOI: 10.1016/j.actaastro.2025.01.055
Zichen Fan , Weiqin Ke , Mingying Huo , Ji Qi , Wenyu Feng , Naiming Qi
The large amount of space debris in Earth’s orbit has seriously affected the operational safety of spacecraft. Therefore, this paper proposes a fast optimization algorithm for multi-target detection trajectories based on Bezier-shaped method, targeting non-cooperative targets such as space debris in key areas of the high orbit. This method considers non-spherical gravity perturbation models with different accuracies to achieve rapid design of transfer trajectories; according to different detection missions, this method is also applied under different conditions of free and fixed flight time to achieve a multi-target detection. Compared with the Gauss pseudospectral method, the method proposed in this paper achieved excellent optimization results using an extremely short computation time, significantly improving the efficiency of trajectory optimization under complex gravitational perturbations. This is of great significance for the initial mission analysis of detecting a large amount of space debris in Earth’s orbit in the near future.
{"title":"Rapid optimization of low-thrust trajectories for multi-target detection under complex gravitational perturbation","authors":"Zichen Fan , Weiqin Ke , Mingying Huo , Ji Qi , Wenyu Feng , Naiming Qi","doi":"10.1016/j.actaastro.2025.01.055","DOIUrl":"10.1016/j.actaastro.2025.01.055","url":null,"abstract":"<div><div>The large amount of space debris in Earth’s orbit has seriously affected the operational safety of spacecraft. Therefore, this paper proposes a fast optimization algorithm for multi-target detection trajectories based on Bezier-shaped method, targeting non-cooperative targets such as space debris in key areas of the high orbit. This method considers non-spherical gravity perturbation models with different accuracies to achieve rapid design of transfer trajectories; according to different detection missions, this method is also applied under different conditions of free and fixed flight time to achieve a multi-target detection. Compared with the Gauss pseudospectral method, the method proposed in this paper achieved excellent optimization results using an extremely short computation time, significantly improving the efficiency of trajectory optimization under complex gravitational perturbations. This is of great significance for the initial mission analysis of detecting a large amount of space debris in Earth’s orbit in the near future.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 736-748"},"PeriodicalIF":3.1,"publicationDate":"2025-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143173860","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 : 2025-01-30DOI: 10.1016/j.actaastro.2025.01.058
Qin Huang , Ying Zhang
In this paper, a predefined-time fault-tolerant control scheme is proposed for rigid spacecraft attitude tracking systems with full-state performance constraints. By employing the asymmetrical time-varying integral barrier Lyapunov function, an attitude controller is developed to ensure both attitude and angular velocity tracking errors are stabilized under preset performance constraints within a predefined time. Unlike existing prescribed performance methods, the designed controller allows for direct and arbitrary presetting of the performance boundary for angular velocity tracking error, making it suitable for scenarios where the angular velocity tracking error boundary is stricter than that of the attitude tracking error. To address the lumped perturbation arising from external disturbances, inertia uncertainties and actuator faults, a predefined-time disturbance observer based on a tracking differentiator is firstly proposed. Notably, the commonly used boundedness assumption for the lumped perturbation is sidestepped by using the designed disturbance observer. Comparative numerical simulations are given to substantiate the effectiveness and superiority of the proposed control scheme.
{"title":"Predefined-time fault-tolerant control for rigid spacecraft attitude tracking maneuver with asymmetrical full-state performance constraints","authors":"Qin Huang , Ying Zhang","doi":"10.1016/j.actaastro.2025.01.058","DOIUrl":"10.1016/j.actaastro.2025.01.058","url":null,"abstract":"<div><div>In this paper, a predefined-time fault-tolerant control scheme is proposed for rigid spacecraft attitude tracking systems with full-state performance constraints. By employing the asymmetrical time-varying integral barrier Lyapunov function, an attitude controller is developed to ensure both attitude and angular velocity tracking errors are stabilized under preset performance constraints within a predefined time. Unlike existing prescribed performance methods, the designed controller allows for direct and arbitrary presetting of the performance boundary for angular velocity tracking error, making it suitable for scenarios where the angular velocity tracking error boundary is stricter than that of the attitude tracking error. To address the lumped perturbation arising from external disturbances, inertia uncertainties and actuator faults, a predefined-time disturbance observer based on a tracking differentiator is firstly proposed. Notably, the commonly used boundedness assumption for the lumped perturbation is sidestepped by using the designed disturbance observer. Comparative numerical simulations are given to substantiate the effectiveness and superiority of the proposed control scheme.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 848-860"},"PeriodicalIF":3.1,"publicationDate":"2025-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143349328","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}
This paper introduces an event-triggered control strategy for spacecraft conducting near-asteroid missions, specifically orbiting an asteroid within a defined orbital radius area to enable precise observations and exploration using instruments like ground-penetrating radar. The strategy maintains stable attitude and orbital radius with much lower energy costs. An impulsive orbital control is proposed, in which an intermittent event-triggered mechanism with barrier functions could reduce the energy cost and extend the spacecraft’s lifetime by avoiding unnecessary impulsive thrusts with lower times of impulsive controlled thrusts in an orbital period. For attitude stabilization, a sigmoid-based event-triggered mechanism is employed with a control dead zone to extend control intervals without sacrificing accuracy, thus to reduce most of computation costs. Gravitational orbit-attitude coupling and solar radiation pressure coupling are incorporated into the attitude-orbit dynamics modeling and compensated for in the control design. Stability analysis and numerical simulations validate the strategy’s robustness and effectiveness.
{"title":"Event-triggered orbital and attitude station-keeping control for near-asteroid spacecraft","authors":"Hongyi Xie , Fuqiang Duan , Franco Bernelli-Zazzera","doi":"10.1016/j.actaastro.2025.01.053","DOIUrl":"10.1016/j.actaastro.2025.01.053","url":null,"abstract":"<div><div>This paper introduces an event-triggered control strategy for spacecraft conducting near-asteroid missions, specifically orbiting an asteroid within a defined orbital radius area to enable precise observations and exploration using instruments like ground-penetrating radar. The strategy maintains stable attitude and orbital radius with much lower energy costs. An impulsive orbital control is proposed, in which an intermittent event-triggered mechanism with barrier functions could reduce the energy cost and extend the spacecraft’s lifetime by avoiding unnecessary impulsive thrusts with lower times of impulsive controlled thrusts in an orbital period. For attitude stabilization, a sigmoid-based event-triggered mechanism is employed with a control dead zone to extend control intervals without sacrificing accuracy, thus to reduce most of computation costs. Gravitational orbit-attitude coupling and solar radiation pressure coupling are incorporated into the attitude-orbit dynamics modeling and compensated for in the control design. Stability analysis and numerical simulations validate the strategy’s robustness and effectiveness.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"229 ","pages":"Pages 918-928"},"PeriodicalIF":3.1,"publicationDate":"2025-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143396053","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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