Pub Date : 2025-01-07DOI: 10.1016/j.actaastro.2025.01.004
Shao Nie, Fei Qin, Jinying Ye, Xianggeng Wei, Guoqiang He
One of the principal research subjects within the field of rocket-based combined cycle (RBCC) engines has been the ejector mode, which has been the focus of research for a considerable period of time. The objective of this paper is to present a detailed analysis to the ejector mode of kerosene-fueled RBCC engine. The matching mechanism of the diffusion and afterburning (DAB) mode was obtained through a combination of experiment, theoretical modeling, and numerical simulation. The thrust gain of the sea-level ejector mode was subsequently analyzed. The findings indicate that: (1) In the DAB mode, the requirement of the thermal or geometric throat area ratio is small. The difficulty in organizing the thermal throat has led to the use of a geometric throat to achieve choking on the engine. The results of the model calculation indicate that a thrust gain of 25.2 % for a sea-level ejector mode can be achieved by employing a throat area ratio of 1.83. (2) For the sea-level ejector mode, the mixing requirement can be satisfied when the length of the mixing section reaches 4 times the hydraulic diameter of the rocket nozzle outlet's section. The use of a throat area ratio of 1.8 allows for a thrust gain of 15.9 % in the sea-level ejector mode. The presence of fuel pylons has been observed to reduce thrust gain. (3) The matching mechanism of sea-level ejector mode is revealed. When the rocket flow rate, bypass ratio, combustion organization and throat area ratio match, the maximum thrust gain can be achieved.
{"title":"Investigation on sea-level thrust gain in ejector mode of rocket-based combined cycle engine","authors":"Shao Nie, Fei Qin, Jinying Ye, Xianggeng Wei, Guoqiang He","doi":"10.1016/j.actaastro.2025.01.004","DOIUrl":"https://doi.org/10.1016/j.actaastro.2025.01.004","url":null,"abstract":"One of the principal research subjects within the field of rocket-based combined cycle (RBCC) engines has been the ejector mode, which has been the focus of research for a considerable period of time. The objective of this paper is to present a detailed analysis to the ejector mode of kerosene-fueled RBCC engine. The matching mechanism of the diffusion and afterburning (DAB) mode was obtained through a combination of experiment, theoretical modeling, and numerical simulation. The thrust gain of the sea-level ejector mode was subsequently analyzed. The findings indicate that: (1) In the DAB mode, the requirement of the thermal or geometric throat area ratio is small. The difficulty in organizing the thermal throat has led to the use of a geometric throat to achieve choking on the engine. The results of the model calculation indicate that a thrust gain of 25.2 % for a sea-level ejector mode can be achieved by employing a throat area ratio of 1.83. (2) For the sea-level ejector mode, the mixing requirement can be satisfied when the length of the mixing section reaches 4 times the hydraulic diameter of the rocket nozzle outlet's section. The use of a throat area ratio of 1.8 allows for a thrust gain of 15.9 % in the sea-level ejector mode. The presence of fuel pylons has been observed to reduce thrust gain. (3) The matching mechanism of sea-level ejector mode is revealed. When the rocket flow rate, bypass ratio, combustion organization and throat area ratio match, the maximum thrust gain can be achieved.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"9 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2025-01-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142967737","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 : 2025-01-07DOI: 10.1016/j.actaastro.2025.01.002
Peineng Zhong, Lusi Wang, Guangfei Zhang, Xiayu Li, Jinchang Xu, Qichen Sun, Suping Wang, Suolai Zhang, Chu Wang, Lei Chen, Xu Yang, Kun Xu, Xilun Ding, Tao Zhang
Water ice, extensively detected in the lunar south polar region, represents a valuable resource for future lunar base construction and energy utilization. To gain a comprehensive understanding of the origin, distribution, and properties of water ice in the lunar polar regions, on-site measurement is essential. In alignment with this goal, China’s Chang’E 7 mission, scheduled for launch in 2026, aims to explore water ice within permanently shadowed regions of the lunar south pole through drilling and in-situ measurement of water content. This work presents the design and development of a thermal-vacuum regolith environment simulator, specifically created to test the performance of a robotic drill under conditions simulating the icy lunar regolith of the lunar polar environment. The simulator comprises a vacuum acquisition system, a cryogenic cooling system, and a preparation system for icy lunar regolith simulant. Additionally, the simulator can effectively adjust the position of the lunar regolith container and visually monitor it. The vacuum acquisition system provides a low-pressure environment suitable for drilling tests with icy lunar regolith simulant, while the cryogenic cooling system refrigerates the simulant to a temperature as low as 95 K (−178 °C). The regolith preparation system, moreover, enables controlled mixing and compaction of regolith simulant to specific bulk densities and water contents. To enhance testing efficiency in simulated thermal-vacuum environments, the simulator includes a rotation mechanism that allows multiple drilling tests within a single environmental setup by adjusting the position of the regolith container. Experimental validation confirms the capacity of the simulator to replicate conditions similar to those in lunar polar regions. Specifically, the vacuum acquisition system can pump the chamber to a pressure in the order of 10−1 Pa when loaded with icy lunar regolith simulant, and the cryogenic cooling system can refrigerate the regolith simulant with water contents of 0.5 wt% and 4 wt% to 95 K. This work can provide essential ground-testing support and technical validation for the upcoming drilling and sampling tasks of the Chinese Chang’E 7 mission.
{"title":"Thermal-vacuum regolith environment simulator for drilling tests in lunar polar regions","authors":"Peineng Zhong, Lusi Wang, Guangfei Zhang, Xiayu Li, Jinchang Xu, Qichen Sun, Suping Wang, Suolai Zhang, Chu Wang, Lei Chen, Xu Yang, Kun Xu, Xilun Ding, Tao Zhang","doi":"10.1016/j.actaastro.2025.01.002","DOIUrl":"https://doi.org/10.1016/j.actaastro.2025.01.002","url":null,"abstract":"Water ice, extensively detected in the lunar south polar region, represents a valuable resource for future lunar base construction and energy utilization. To gain a comprehensive understanding of the origin, distribution, and properties of water ice in the lunar polar regions, on-site measurement is essential. In alignment with this goal, China’s Chang’E 7 mission, scheduled for launch in 2026, aims to explore water ice within permanently shadowed regions of the lunar south pole through drilling and <ce:italic>in-situ</ce:italic> measurement of water content. This work presents the design and development of a thermal-vacuum regolith environment simulator, specifically created to test the performance of a robotic drill under conditions simulating the icy lunar regolith of the lunar polar environment. The simulator comprises a vacuum acquisition system, a cryogenic cooling system, and a preparation system for icy lunar regolith simulant. Additionally, the simulator can effectively adjust the position of the lunar regolith container and visually monitor it. The vacuum acquisition system provides a low-pressure environment suitable for drilling tests with icy lunar regolith simulant, while the cryogenic cooling system refrigerates the simulant to a temperature as low as 95 K (<mml:math altimg=\"si22.svg\" display=\"inline\"><mml:mrow><mml:mo>−</mml:mo><mml:mn>178</mml:mn></mml:mrow></mml:math> °C). The regolith preparation system, moreover, enables controlled mixing and compaction of regolith simulant to specific bulk densities and water contents. To enhance testing efficiency in simulated thermal-vacuum environments, the simulator includes a rotation mechanism that allows multiple drilling tests within a single environmental setup by adjusting the position of the regolith container. Experimental validation confirms the capacity of the simulator to replicate conditions similar to those in lunar polar regions. Specifically, the vacuum acquisition system can pump the chamber to a pressure in the order of <mml:math altimg=\"si2.svg\" display=\"inline\"><mml:mrow><mml:mn>1</mml:mn><mml:msup><mml:mrow><mml:mn>0</mml:mn></mml:mrow><mml:mrow><mml:mo>−</mml:mo><mml:mn>1</mml:mn></mml:mrow></mml:msup></mml:mrow></mml:math> Pa when loaded with icy lunar regolith simulant, and the cryogenic cooling system can refrigerate the regolith simulant with water contents of 0.5 wt% and 4 wt% to 95 K. This work can provide essential ground-testing support and technical validation for the upcoming drilling and sampling tasks of the Chinese Chang’E 7 mission.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"128 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2025-01-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142967736","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 : 2025-01-02DOI: 10.1016/j.actaastro.2024.12.062
Liangliang Zhao, Rui Zhang, Yupei Du, Guifen Zhou, Lige Wen, Hua Zhang
As lunar exploration progressed, unmanned lunar rovers encountered harsher and more variable working environments, increasingly complex operating conditions, and greater exploration range requirements. Existing unmanned lunar mesh wheels could not meet the demands of future lunar missions, which required higher traction performance, greater reliability, and lower power consumption. In this study, inspired by the functional characteristics of ostrich toes, we designed a bionic wheel and a comparison wheel. By interchanging the wheel surfaces and lugs (grousers), four types of mesh wheels (Wheels 1–4) were developed and tested. Various loads and slip ratios were applied to investigate how the surface shape of the mesh wheel and the shape of its lugs influenced traction performance and enhanced overall traction. The test results indicated that Wheel 1 outperformed the other wheels in terms of traction performance under the specified conditions and demonstrated greater energy efficiency at lower slip ratios. This led the compacted particles beneath the bionic wheel surface to generate a lateral forward reaction force, thereby propelling the wheel. This caused the compacted particles beneath the bionic wheel surface to generate a lateral forward reaction force, thereby propelling the wheel forward. The bionic lugs operated on a similar principle; however, their contribution to traction was less significant than that of the bionic wheel surface. The innovative design of the wheel surface and lugs effectively addressed the limitations of existing lunar mesh wheel structures.
{"title":"Research in innovative mesh wheel with bionic wheel surfaces and lugs for superior lunar rover performance","authors":"Liangliang Zhao, Rui Zhang, Yupei Du, Guifen Zhou, Lige Wen, Hua Zhang","doi":"10.1016/j.actaastro.2024.12.062","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.062","url":null,"abstract":"As lunar exploration progressed, unmanned lunar rovers encountered harsher and more variable working environments, increasingly complex operating conditions, and greater exploration range requirements. Existing unmanned lunar mesh wheels could not meet the demands of future lunar missions, which required higher traction performance, greater reliability, and lower power consumption. In this study, inspired by the functional characteristics of ostrich toes, we designed a bionic wheel and a comparison wheel. By interchanging the wheel surfaces and lugs (grousers), four types of mesh wheels (Wheels 1–4) were developed and tested. Various loads and slip ratios were applied to investigate how the surface shape of the mesh wheel and the shape of its lugs influenced traction performance and enhanced overall traction. The test results indicated that Wheel 1 outperformed the other wheels in terms of traction performance under the specified conditions and demonstrated greater energy efficiency at lower slip ratios. This led the compacted particles beneath the bionic wheel surface to generate a lateral forward reaction force, thereby propelling the wheel. This caused the compacted particles beneath the bionic wheel surface to generate a lateral forward reaction force, thereby propelling the wheel forward. The bionic lugs operated on a similar principle; however, their contribution to traction was less significant than that of the bionic wheel surface. The innovative design of the wheel surface and lugs effectively addressed the limitations of existing lunar mesh wheel structures.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"74 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2025-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142925310","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 : 2025-01-02DOI: 10.1016/j.actaastro.2024.12.061
Xiaoniu Li, Xinjian Li, Lingfeng Tang, Zheng Yang, Lin Yang
With the diversification and multifunctionality of space missions, micro-nano satellites need to carry more payloads in deep space orbits with harsh lighting conditions. Traditional built-in batteries and fixed deployable solar wings offer limited energy, making it difficult to meet these demands. Although solar wing drive mechanisms powered by stepper motors and harmonic reducers improve power output, their large size, weight, and complexity render them unsuitable for micro-nano satellites. This paper presents a solar array drive assembly driven by an ultrasonic motor, designed for micro-nano satellites operating in the halo orbit at the Lagrange L2 point of the Earth-Moon system. This design addresses the need for miniaturization and lightweight construction while enhancing energy supply. Key components, including the yaw axis pointing mechanism, solar panel assembly, angular displacement detection, energy transmission system, and ultrasonic motor, are optimized for size and weight reduction. To identify the optimal energy-saving drive method, a dynamic model of the SADA system is established, and a novel low-power driving method for the ultrasonic motor-driven solar wing is proposed. A prototype with a volume of less than 0.5U and a mass under 0.2 kg was fabricated. Experimental results show that the output torque of the ultrasonic motor exceeds 0.0581 N m, with the number of driving signal cycles n positively correlated with the total rotation angle θ of the solar wing. When n = 1000 and the interval time Tm = 1.35 h, the mechanism achieves its lowest energy consumption cost, allowing the solar wing to operate at 12.1° per day, saving over 23.8 % of energy compared to continuous drive methods.
随着航天任务的多样化和多功能化，微纳卫星需要在光照条件恶劣的深空轨道上携带更多的有效载荷。传统的内置电池和固定可展开的太阳能机翼提供有限的能量，使其难以满足这些需求。虽然由步进电机和谐波减速器驱动的太阳能翼驱动机构提高了功率输出，但它们的大尺寸、重量和复杂性使它们不适合用于微纳卫星。针对地月系拉格朗日L2点晕轨微纳卫星，设计了一种由超声电机驱动的太阳能电池阵列驱动组件。这种设计解决了小型化和轻量化结构的需要，同时提高了能源供应。关键部件，包括偏航轴指向机构、太阳能电池板组件、角位移检测、能量传输系统和超声波电机，都进行了尺寸和重量的优化。为了确定最优的节能驱动方法，建立了SADA系统的动力学模型，提出了一种新型的超声电机驱动太阳能翼的低功耗驱动方法。制作了体积小于0.5U、质量小于0.2 kg的原型机。实验结果表明，超声电机的输出转矩超过0.0581 N m，驱动信号周期数N与太阳能翼总转角θ呈正相关。当n = 1000，间隔时间Tm = 1.35 h时，该机构达到了最低的能耗成本，允许太阳能翼以每天12.1°的速度运行，与连续驱动方法相比节省了23.8%以上的能量。
{"title":"Development of a compact solar array drive assembly based on ultrasonic motor for deep space micro-nano satellites","authors":"Xiaoniu Li, Xinjian Li, Lingfeng Tang, Zheng Yang, Lin Yang","doi":"10.1016/j.actaastro.2024.12.061","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.061","url":null,"abstract":"With the diversification and multifunctionality of space missions, micro-nano satellites need to carry more payloads in deep space orbits with harsh lighting conditions. Traditional built-in batteries and fixed deployable solar wings offer limited energy, making it difficult to meet these demands. Although solar wing drive mechanisms powered by stepper motors and harmonic reducers improve power output, their large size, weight, and complexity render them unsuitable for micro-nano satellites. This paper presents a solar array drive assembly driven by an ultrasonic motor, designed for micro-nano satellites operating in the halo orbit at the Lagrange L2 point of the Earth-Moon system. This design addresses the need for miniaturization and lightweight construction while enhancing energy supply. Key components, including the yaw axis pointing mechanism, solar panel assembly, angular displacement detection, energy transmission system, and ultrasonic motor, are optimized for size and weight reduction. To identify the optimal energy-saving drive method, a dynamic model of the SADA system is established, and a novel low-power driving method for the ultrasonic motor-driven solar wing is proposed. A prototype with a volume of less than 0.5U and a mass under 0.2 kg was fabricated. Experimental results show that the output torque of the ultrasonic motor exceeds 0.0581 N m, with the number of driving signal cycles <ce:italic>n</ce:italic> positively correlated with the total rotation angle <ce:italic>θ</ce:italic> of the solar wing. When <ce:italic>n</ce:italic> = 1000 and the interval time <ce:italic>T</ce:italic><ce:inf loc=\"post\"><ce:italic>m</ce:italic></ce:inf> = 1.35 h, the mechanism achieves its lowest energy consumption cost, allowing the solar wing to operate at 12.1° per day, saving over 23.8 % of energy compared to continuous drive methods.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"1 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2025-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142925311","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 : 2025-01-01DOI: 10.1016/j.actaastro.2024.12.035
Samuel T. Hart, E. Glenn Lightsey, Álvaro Romero-Calvo
CubeSat propulsion imposes unique propellant management issues. The requisite form factor often necessitates conformal tank geometries and high-density two-phase propellants. Fluid management in these saturated propellant systems cannot generally be accomplished using conventional capillary devices, and current state-of-the-art alternatives are comparatively large. Recently, approaches based on thermal phase change have been proposed. In these phase change propellant management devices (PMDs), the propellant is vaporized in one portion of the tank through the application of heat and condensed in cooler portions due to increased pressure. Experimental results presented here show that ullage bubbles can be repositioned in a thermally insulative nylon tank using less than 5 W of input power. Test data and models indicate that the thermal conductivity of the tank has a significant effect on the efficiency of a phase change PMD when the heat source makes direct contact with the wall. The position of the heater is also shown to have a major impact on performance. Appropriate heater positioning could allow phase change PMDs to be used in tanks constructed of any material in microgravity.
{"title":"Characterization of a Phase Change Propellant Management Device","authors":"Samuel T. Hart, E. Glenn Lightsey, Álvaro Romero-Calvo","doi":"10.1016/j.actaastro.2024.12.035","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.035","url":null,"abstract":"CubeSat propulsion imposes unique propellant management issues. The requisite form factor often necessitates conformal tank geometries and high-density two-phase propellants. Fluid management in these saturated propellant systems cannot generally be accomplished using conventional capillary devices, and current state-of-the-art alternatives are comparatively large. Recently, approaches based on thermal phase change have been proposed. In these phase change propellant management devices (PMDs), the propellant is vaporized in one portion of the tank through the application of heat and condensed in cooler portions due to increased pressure. Experimental results presented here show that ullage bubbles can be repositioned in a thermally insulative nylon tank using less than 5 W of input power. Test data and models indicate that the thermal conductivity of the tank has a significant effect on the efficiency of a phase change PMD when the heat source makes direct contact with the wall. The position of the heater is also shown to have a major impact on performance. Appropriate heater positioning could allow phase change PMDs to be used in tanks constructed of any material in microgravity.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"37 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2025-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142925286","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 : 2024-12-31DOI: 10.1016/j.actaastro.2024.12.042
Renhe Shi, Xinhui Tai, Teng Long, Nianhui Ye, Fuxiang Dong
With the increasing demands for high-speed data transmission and global communication, GEO telecommunication satellites with large-size antenna payload have attracted much attention nowadays. To address the challenge of effective system design, this paper proposes a metamodel assisted multidisciplinary design optimization (MDO) framework for a Large-size Payload Telecommunication Satellite (LSP-TS). In the framework, the LSP-TS MDO problem is formulated to minimize the total system mass subject to several practical engineering constraints. Considering the interconnected relationship between the large-size payload and the satellite platform, the analysis models of satellite geometry configuration, power, attitude control, structure, GEO station-keeping, orbital transfer, and mass disciplines are established. To reduce the computational cost, an adaptive Kriging method using Pareto fitness-based sampling (AKM-PFS) is proposed as the optimizer integrated with the satellite MDO framework. In this approach, the Kriging metamodels of LSP-TS system are constructed and adaptively refined for optimization via exploring the Pareto frontier of objective and constraints, which leads the search to the feasible optimized satellite system design efficiently. After optimization, the total system mass is reduced by 318.53 kg (8.87 %) compared with the initial solution where all constraints being satisfied. Moreover, the optimization solution of the proposed AKM-PFS is further discussed to illustrate the practicality and effectiveness of the proposed method.
{"title":"Multidisciplinary design and metamodel assisted optimization for a telecommunication satellite with large-size payload","authors":"Renhe Shi, Xinhui Tai, Teng Long, Nianhui Ye, Fuxiang Dong","doi":"10.1016/j.actaastro.2024.12.042","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.042","url":null,"abstract":"With the increasing demands for high-speed data transmission and global communication, GEO telecommunication satellites with large-size antenna payload have attracted much attention nowadays. To address the challenge of effective system design, this paper proposes a metamodel assisted multidisciplinary design optimization (MDO) framework for a Large-size Payload Telecommunication Satellite (LSP-TS). In the framework, the LSP-TS MDO problem is formulated to minimize the total system mass subject to several practical engineering constraints. Considering the interconnected relationship between the large-size payload and the satellite platform, the analysis models of satellite geometry configuration, power, attitude control, structure, GEO station-keeping, orbital transfer, and mass disciplines are established. To reduce the computational cost, an adaptive Kriging method using Pareto fitness-based sampling (AKM-PFS) is proposed as the optimizer integrated with the satellite MDO framework. In this approach, the Kriging metamodels of LSP-TS system are constructed and adaptively refined for optimization via exploring the Pareto frontier of objective and constraints, which leads the search to the feasible optimized satellite system design efficiently. After optimization, the total system mass is reduced by 318.53 kg (8.87 %) compared with the initial solution where all constraints being satisfied. Moreover, the optimization solution of the proposed AKM-PFS is further discussed to illustrate the practicality and effectiveness of the proposed method.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"43 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2024-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142929277","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 : 2024-12-31DOI: 10.1016/j.actaastro.2024.12.053
Andrea Muciaccia, Matteo Romano, Mirko Trisolini, Camilla Colombo
The number of uncontrollable objects orbiting around the Earth is constantly growing because of the increased number of new missions and launches and the increased frequency of breakup events. Even with debris mitigation guidelines, some breakup events are difficult to predict or avoid. Consequently, it is extremely important to monitor the appearance of new fragments and study them to have a better knowledge of the events and reduce the risk they pose to other active objects.
{"title":"Reconstruction of in-orbit breakup events over the long term","authors":"Andrea Muciaccia, Matteo Romano, Mirko Trisolini, Camilla Colombo","doi":"10.1016/j.actaastro.2024.12.053","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.053","url":null,"abstract":"The number of uncontrollable objects orbiting around the Earth is constantly growing because of the increased number of new missions and launches and the increased frequency of breakup events. Even with debris mitigation guidelines, some breakup events are difficult to predict or avoid. Consequently, it is extremely important to monitor the appearance of new fragments and study them to have a better knowledge of the events and reduce the risk they pose to other active objects.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"7 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2024-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142925261","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 : 2024-12-25DOI: 10.1016/j.actaastro.2024.12.047
Anna Drobysheva, Stepan Tkachev, Dmitry Roldugin
The one-axis magnetic attitude control problem for a 6U CubeSat is considered. The payload demands high-accuracy pointing and stabilization for short-term periods. A special reference motion is constructed to overcome the constraints of magnetic control and meet the accuracy requirements. To find this motion, the particle swarm optimization (PSO) method is first employed. Subsequently, a three-axis magnetic attitude control law is applied to stabilize the satellite in the vicinity of this motion. Since the performance of the magnetic control is sensitive to disturbances, an extensive numerical study is conducted to demonstrate the fulfillment of the payload requirements. Special attention is given to the uncertainty in the inertia tensor knowledge, which arises due to imperfections in the satellite assembly and the inherent complexity of estimating this parameter.
{"title":"One-axis magnetic attitude control for short-term high-accuracy pointing","authors":"Anna Drobysheva, Stepan Tkachev, Dmitry Roldugin","doi":"10.1016/j.actaastro.2024.12.047","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.047","url":null,"abstract":"The one-axis magnetic attitude control problem for a 6U CubeSat is considered. The payload demands high-accuracy pointing and stabilization for short-term periods. A special reference motion is constructed to overcome the constraints of magnetic control and meet the accuracy requirements. To find this motion, the particle swarm optimization (PSO) method is first employed. Subsequently, a three-axis magnetic attitude control law is applied to stabilize the satellite in the vicinity of this motion. Since the performance of the magnetic control is sensitive to disturbances, an extensive numerical study is conducted to demonstrate the fulfillment of the payload requirements. Special attention is given to the uncertainty in the inertia tensor knowledge, which arises due to imperfections in the satellite assembly and the inherent complexity of estimating this parameter.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"34 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2024-12-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142889304","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 : 2024-12-19DOI: 10.1016/j.actaastro.2024.12.025
Lei Zhang, Hui Ren, TengFei Yuan, Wei Fan
The large inertia and high flexibility of large appendages in the flexible spacecraft pose significant challenges for dynamic modeling and achieving high-precision attitude control. This paper focuses on the attitude-tracking problem of spacecraft equipped with large flexible appendages and novel dynamic modeling and attitude maneuver control methods are developed. An accurate high-order dynamic model is established using the referenced nodal coordinate formulation and an associated model reduction technique is proposed to obtain a low-order model that can capture geometric nonlinearity due to large deformations. A high-precision attitude maneuver controller for flexible spacecraft is designed in SO(3) space by introducing model-based flexible compensation terms, which can be conveniently integrated into traditional attitude control algorithms such as PD and sliding mode controllers. A linear modal observer is designed to reduce difficulty during implementation. Two common flexible spacecraft systems are investigated to demonstrate the performance of the proposed modeling and attitude control approaches. Results indicate that accurate modeling of flexible appendages not only affects their dynamic characteristics but also significantly influences the overall attitude dynamics of the spacecraft. The proposed control approach can significantly improve control accuracy and achieve high-precision attitude tracking even in the presence of large deformations.
{"title":"Dynamic modeling and attitude maneuver control on SO(3) for spacecraft with large flexible appendages","authors":"Lei Zhang, Hui Ren, TengFei Yuan, Wei Fan","doi":"10.1016/j.actaastro.2024.12.025","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.025","url":null,"abstract":"The large inertia and high flexibility of large appendages in the flexible spacecraft pose significant challenges for dynamic modeling and achieving high-precision attitude control. This paper focuses on the attitude-tracking problem of spacecraft equipped with large flexible appendages and novel dynamic modeling and attitude maneuver control methods are developed. An accurate high-order dynamic model is established using the referenced nodal coordinate formulation and an associated model reduction technique is proposed to obtain a low-order model that can capture geometric nonlinearity due to large deformations. A high-precision attitude maneuver controller for flexible spacecraft is designed in SO(3) space by introducing model-based flexible compensation terms, which can be conveniently integrated into traditional attitude control algorithms such as PD and sliding mode controllers. A linear modal observer is designed to reduce difficulty during implementation. Two common flexible spacecraft systems are investigated to demonstrate the performance of the proposed modeling and attitude control approaches. Results indicate that accurate modeling of flexible appendages not only affects their dynamic characteristics but also significantly influences the overall attitude dynamics of the spacecraft. The proposed control approach can significantly improve control accuracy and achieve high-precision attitude tracking even in the presence of large deformations.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"125 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2024-12-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142874790","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 : 2024-12-12DOI: 10.1016/j.actaastro.2024.12.026
Masato Adachi, Ryudai Nitano
Mitigation of lunar regolith particles is one of the challenges for the success of future lunar exploration, and an electrodynamic dust shield (EDS) presents a promising solution. Although a wide range of investigations have been conducted on the cleaning of lunar regolith and its simulants using EDS, the effects of particle size on cleaning performance have not been experimentally investigated in depth. In this study, we conducted EDS cleaning experiments using simulant particles sorted into different size ranges, with the aid of force balance calculations that vary with particle size. The experimental and calculated results reveal a clear trend: the cleaning performance of simulant particles smaller than 25 μm and larger than 250 μm deteriorated owing to the adhesion force of small particles and the dielectrophoresis and gravitational forces of large particles, respectively. In addition, observations of particle motion using a high-speed camera confirmed the role of dielectrophoresis and Coulomb forces on regolith simulants of various sizes during cleaning. In the effects of the dielectrophoresis force on larger particles, the interactions of polarized particles were clearly visible, resulting in the creation of particle chains and the trapping of particles on the substrate surface of EDS.
{"title":"Removal efficiency for size-sorted particles of lunar regolith simulant using an electrodynamic dust shield","authors":"Masato Adachi, Ryudai Nitano","doi":"10.1016/j.actaastro.2024.12.026","DOIUrl":"https://doi.org/10.1016/j.actaastro.2024.12.026","url":null,"abstract":"Mitigation of lunar regolith particles is one of the challenges for the success of future lunar exploration, and an electrodynamic dust shield (EDS) presents a promising solution. Although a wide range of investigations have been conducted on the cleaning of lunar regolith and its simulants using EDS, the effects of particle size on cleaning performance have not been experimentally investigated in depth. In this study, we conducted EDS cleaning experiments using simulant particles sorted into different size ranges, with the aid of force balance calculations that vary with particle size. The experimental and calculated results reveal a clear trend: the cleaning performance of simulant particles smaller than 25 μm and larger than 250 μm deteriorated owing to the adhesion force of small particles and the dielectrophoresis and gravitational forces of large particles, respectively. In addition, observations of particle motion using a high-speed camera confirmed the role of dielectrophoresis and Coulomb forces on regolith simulants of various sizes during cleaning. In the effects of the dielectrophoresis force on larger particles, the interactions of polarized particles were clearly visible, resulting in the creation of particle chains and the trapping of particles on the substrate surface of EDS.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"6 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2024-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142825353","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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