Pub Date : 2025-02-25DOI: 10.1016/j.actaastro.2025.02.043
Haochen Ma , Tiance Liang , He Zheng , Jiapeng Li , Liqiu Wei , Liang Han , Hong Li , Yongjie Ding
It is necessary to increase the voltage and reduce the anode volume flow rate to improve the specific Hall thruster impulse under power constraints. This leads to a low density of neutral gas flow in the channel and results in insufficient ionization. This study proposes pulse power technology to improve the specific Hall thruster impulse. The influence of pulsed discharge on the discharge and plasma plume characteristics of a Hall thruster was investigated. The experimental results show that the high voltage provided by the pulsed mode was beneficial to the acceleration of ions at constant power and anode flow. As a result, the specific impulse, efficiency, and thrust of Hall thruster improved. The specific impulse of the Hall thruster at constant power is 1770 s in the pulsed mode and 1570 s in the direct current (DC) mode. This represents an increase of about 12.7 %, which significantly raises the upper limit of the Hall thruster's specific impulse. The results of this study are significant for the design of high-specific-impulse Hall thrusters.
{"title":"Improving specific impulse of Hall thruster by pulse power technology","authors":"Haochen Ma , Tiance Liang , He Zheng , Jiapeng Li , Liqiu Wei , Liang Han , Hong Li , Yongjie Ding","doi":"10.1016/j.actaastro.2025.02.043","DOIUrl":"10.1016/j.actaastro.2025.02.043","url":null,"abstract":"<div><div>It is necessary to increase the voltage and reduce the anode volume flow rate to improve the specific Hall thruster impulse under power constraints. This leads to a low density of neutral gas flow in the channel and results in insufficient ionization. This study proposes pulse power technology to improve the specific Hall thruster impulse. The influence of pulsed discharge on the discharge and plasma plume characteristics of a Hall thruster was investigated. The experimental results show that the high voltage provided by the pulsed mode was beneficial to the acceleration of ions at constant power and anode flow. As a result, the specific impulse, efficiency, and thrust of Hall thruster improved. The specific impulse of the Hall thruster at constant power is 1770 s in the pulsed mode and 1570 s in the direct current (DC) mode. This represents an increase of about 12.7 %, which significantly raises the upper limit of the Hall thruster's specific impulse. The results of this study are significant for the design of high-specific-impulse Hall thrusters.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 127-133"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143527320","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 : 2025-02-25DOI: 10.1016/j.actaastro.2025.02.041
C.-S. Chang , S.-S. Wei , Zu Puayen Tan , Y.-X. Chang , Jong-Shinn Wu
To improve the ignition system of a hybrid rocket engine, this paper reports the experimental study of the performance of the hypergolic solid fuel grain (HSF) consisting of a mixture of NaBH4/KNO3 with paraffin for a hybrid rocket engine using 90 % HTP as the oxidizer. Drop tests were conducted to examine the ignition delay time (IDT) of HSF compositions with varying ratios of sodium borohydride (NaBH4) and potassium nitrate (KNO3) mixing with paraffin. The results showed that IDT decreased with increasing amount of NaBH4, and decreased further with KNO3 addition. For comparison purpose, two formulations were selected for the tests: HSF01 (80 wt% paraffin, 20 wt% NaBH4) and HSF02 (65 wt% paraffin, 20 wt% NaBH4, 15 wt% KNO3). A series of image visualizations using high-resolution and high-speed cameras, and event cameras revealed similar ignition mechanisms for both tests, in which flamelets were formed upon the contact of HTP droplet, leading to explosive combustion. However, KNO3 in HSF02 consumed the smoke-like mixture produced during the explosion, in which behavior was absent in HSF01. In addition, atmospheric combustion tests (ACT) were conducted in a PMMA tube (10 mm in diameter and 100 mm in length) and the results showed that only HSF02 was successfully ignited, with flamelets forming ∼4 ms after HTP injection and full combustion was established at ∼0.7 s. The test results indicated that the KNO3 as an oxidant additive added to the hypergolic solid fuel grain (HSF) plays an important role in the HSF ignition mechanism. It decreases not only the IDT of the fuel grain, but also increases the flammability of the HSF.
{"title":"Hypergolic solid propellant using NaBH4/KNO3 with paraffin for HTP-based hybrid rockets","authors":"C.-S. Chang , S.-S. Wei , Zu Puayen Tan , Y.-X. Chang , Jong-Shinn Wu","doi":"10.1016/j.actaastro.2025.02.041","DOIUrl":"10.1016/j.actaastro.2025.02.041","url":null,"abstract":"<div><div>To improve the ignition system of a hybrid rocket engine, this paper reports the experimental study of the performance of the hypergolic solid fuel grain (HSF) consisting of a mixture of NaBH<sub>4</sub>/KNO<sub>3</sub> with paraffin for a hybrid rocket engine using 90 % HTP as the oxidizer. Drop tests were conducted to examine the ignition delay time (IDT) of HSF compositions with varying ratios of sodium borohydride (NaBH<sub>4</sub>) and potassium nitrate (KNO<sub>3</sub>) mixing with paraffin. The results showed that IDT decreased with increasing amount of NaBH<sub>4</sub>, and decreased further with KNO<sub>3</sub> addition. For comparison purpose, two formulations were selected for the tests: HSF01 (80 wt% paraffin, 20 wt% NaBH<sub>4</sub>) and HSF02 (65 wt% paraffin, 20 wt% NaBH<sub>4</sub>, 15 wt% KNO<sub>3</sub>). A series of image visualizations using high-resolution and high-speed cameras, and event cameras revealed similar ignition mechanisms for both tests, in which flamelets were formed upon the contact of HTP droplet, leading to explosive combustion. However, KNO<sub>3</sub> in HSF02 consumed the smoke-like mixture produced during the explosion, in which behavior was absent in HSF01. In addition, atmospheric combustion tests (ACT) were conducted in a PMMA tube (10 mm in diameter and 100 mm in length) and the results showed that only HSF02 was successfully ignited, with flamelets forming ∼4 ms after HTP injection and full combustion was established at ∼0.7 s. The test results indicated that the KNO<sub>3</sub> as an oxidant additive added to the hypergolic solid fuel grain (HSF) plays an important role in the HSF ignition mechanism. It decreases not only the IDT of the fuel grain, but also increases the flammability of the HSF.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 103-112"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143519578","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 : 2025-02-25DOI: 10.1016/j.actaastro.2025.02.040
Xianda Liu , Yunhe Meng
This paper studies the configuration acquisition problem of the TianQin space gravitational wave detector. For the characteristics of the TianQin gravitational wave detector configuration, such as large scale, high precision requirements, and small upper limit of thrust, firstly, the large-scale configuration acquisition problem is transformed into a small-scale rendezvous problem using the virtual formation idea. Then, using the differential geometry guidance method, high-precision, and rapid rendezvous is achieved through continuous small thrust, and the process of achieving configuration acquisition through collaborative optimization using genetic algorithms is designed. Finally, the influence of differential geometry guidance law parameters on rendezvous performance is analyzed through simulation, and the feasibility of collaborative optimization to achieve configuration acquisition is verified.
{"title":"Configuration acquisition of gravitational wave detector based on differential geometry guidance","authors":"Xianda Liu , Yunhe Meng","doi":"10.1016/j.actaastro.2025.02.040","DOIUrl":"10.1016/j.actaastro.2025.02.040","url":null,"abstract":"<div><div>This paper studies the configuration acquisition problem of the TianQin space gravitational wave detector. For the characteristics of the TianQin gravitational wave detector configuration, such as large scale, high precision requirements, and small upper limit of thrust, firstly, the large-scale configuration acquisition problem is transformed into a small-scale rendezvous problem using the virtual formation idea. Then, using the differential geometry guidance method, high-precision, and rapid rendezvous is achieved through continuous small thrust, and the process of achieving configuration acquisition through collaborative optimization using genetic algorithms is designed. Finally, the influence of differential geometry guidance law parameters on rendezvous performance is analyzed through simulation, and the feasibility of collaborative optimization to achieve configuration acquisition is verified.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 134-147"},"PeriodicalIF":3.1,"publicationDate":"2025-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143527317","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 : 2025-02-22DOI: 10.1016/j.actaastro.2025.02.017
Eyoas E. Areda , Masui Hirokazu , Mengu Cho
Advancements in CubeSat technologies are revolutionizing space research and commercial satellite applications, enabling CubeSats to conduct advanced, complex missions. A key development is the deployment of CubeSat constellations for continuous monitoring, driven by private space firms due to low costs and scalability. As demand for CubeSat constellations grows, standardized design and development processes are crucial for mass production. Traditional CubeSat interfaces, using a stacking arrangement, increase assembly time and costs due to a lack of standardization. Customizing interfaces for specific missions complicates testing and repairs, reducing reliability and flexibility. System complexity in satellite development causes inefficiency, yet the impact on mass CubeSat production remains unassessed, with no established methods to evaluate satellite assembly complexity. To address these issues, this study investigates CubeSat platform interfaces using industrial design tools like design for manufacturing and assembly and advanced complexity analysis. The goal is to develop a modular, flexible platform with a standardized interface to enhance compatibility and reduce costs. This study describes the development and interface standardization process of a 1U structure platform using a slot-type mechanical interface and a backplane-board-type electrical interface for efficient mass production. The concept, previously demonstrated on a 3U CubeSat, employs a unique method for mounting internal subsystems onto the main structural frame, facilitating integration while minimizing structural parts. Important design parameters influencing efficiency are evaluated against conventional designs for suitability in high-demand applications. Evaluation methods are validated with assembly and disassembly tests, resulting in reduced integration time, lower costs, and improved reliability. Assembly tests and environmental testing under launch conditions have shown promising results, ensuring the design can withstand launch loads.
{"title":"Improving efficiency in CubeSat mass production: A modular and standardized approach","authors":"Eyoas E. Areda , Masui Hirokazu , Mengu Cho","doi":"10.1016/j.actaastro.2025.02.017","DOIUrl":"10.1016/j.actaastro.2025.02.017","url":null,"abstract":"<div><div>Advancements in CubeSat technologies are revolutionizing space research and commercial satellite applications, enabling CubeSats to conduct advanced, complex missions. A key development is the deployment of CubeSat constellations for continuous monitoring, driven by private space firms due to low costs and scalability. As demand for CubeSat constellations grows, standardized design and development processes are crucial for mass production. Traditional CubeSat interfaces, using a stacking arrangement, increase assembly time and costs due to a lack of standardization. Customizing interfaces for specific missions complicates testing and repairs, reducing reliability and flexibility. System complexity in satellite development causes inefficiency, yet the impact on mass CubeSat production remains unassessed, with no established methods to evaluate satellite assembly complexity. To address these issues, this study investigates CubeSat platform interfaces using industrial design tools like design for manufacturing and assembly and advanced complexity analysis. The goal is to develop a modular, flexible platform with a standardized interface to enhance compatibility and reduce costs. This study describes the development and interface standardization process of a 1U structure platform using a slot-type mechanical interface and a backplane-board-type electrical interface for efficient mass production. The concept, previously demonstrated on a 3U CubeSat, employs a unique method for mounting internal subsystems onto the main structural frame, facilitating integration while minimizing structural parts. Important design parameters influencing efficiency are evaluated against conventional designs for suitability in high-demand applications. Evaluation methods are validated with assembly and disassembly tests, resulting in reduced integration time, lower costs, and improved reliability. Assembly tests and environmental testing under launch conditions have shown promising results, ensuring the design can withstand launch loads.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"232 ","pages":"Pages 51-67"},"PeriodicalIF":3.1,"publicationDate":"2025-02-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143580590","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 : 2025-02-21DOI: 10.1016/j.actaastro.2025.02.022
Jucheng Lu, Haibin Shang, Xuefen Zhang
This paper proposes the application of a physics-informed neural network (PINN) to the propagation of heterogeneous binary asteroid systems. The accuracy and efficiency of such propagation are important in the study of celestial mechanics and mission analysis, where we devote to achieving a reasonable balance. The gravitational interactions, which are necessary quantities for this integration, are formulated in Taylor expansion representation that incorporates the derivatives of the primary’s gravitational potential, the secondary’s generalized inertia integrals, and the relative geometry. To represent the gravity field of the primary with heterogeneous mass distribution, a hybrid model combining a quadrature-based polyhedron model and a PINN-based model is developed. The derivatives of the resultant gravitational potential are obtained by superposing those from the polyhedron and PINN-based models, with calculations performed using analytical formulas and automatic differentiation, respectively. For the gravitational potential evaluations, the hybrid model offers faster computation speed and comparable precision compared to the benchmark model. Its application to binary asteroid system propagation demonstrates that the PINN component can effectively capture the effects of non-uniform mass distribution of the body. Furthermore, our mutual dynamics simulations suggest that the heterogeneous mass distribution of the primary may significantly influence the orbital period of the system.
{"title":"Speeding up heterogeneous binary asteroid system propagation through the physics-informed neural network","authors":"Jucheng Lu, Haibin Shang, Xuefen Zhang","doi":"10.1016/j.actaastro.2025.02.022","DOIUrl":"10.1016/j.actaastro.2025.02.022","url":null,"abstract":"<div><div>This paper proposes the application of a physics-informed neural network (PINN) to the propagation of heterogeneous binary asteroid systems. The accuracy and efficiency of such propagation are important in the study of celestial mechanics and mission analysis, where we devote to achieving a reasonable balance. The gravitational interactions, which are necessary quantities for this integration, are formulated in Taylor expansion representation that incorporates the derivatives of the primary’s gravitational potential, the secondary’s generalized inertia integrals, and the relative geometry. To represent the gravity field of the primary with heterogeneous mass distribution, a hybrid model combining a quadrature-based polyhedron model and a PINN-based model is developed. The derivatives of the resultant gravitational potential are obtained by superposing those from the polyhedron and PINN-based models, with calculations performed using analytical formulas and automatic differentiation, respectively. For the gravitational potential evaluations, the hybrid model offers faster computation speed and comparable precision compared to the benchmark model. Its application to binary asteroid system propagation demonstrates that the PINN component can effectively capture the effects of non-uniform mass distribution of the body. Furthermore, our mutual dynamics simulations suggest that the heterogeneous mass distribution of the primary may significantly influence the orbital period of the system.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 64-79"},"PeriodicalIF":3.1,"publicationDate":"2025-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143508768","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 : 2025-02-21DOI: 10.1016/j.actaastro.2025.02.019
A. D’Anniballe, L. Felicetti, S. Hobbs
Accurately tracking space debris and operational satellites is the foundation of the long-term sustainability of space operations. To improve upon some of the inherent limitations of ground radars, a constellation of satellites carrying optical sensors for the surveillance of the Low Earth Orbit (LEO) region is analysed. This analysis aims to understand the performance drivers of such a system in terms of constellation geometry and provide a general methodology for the preliminary design of the system. First, a method for decoupling the design of the optical payload and the constellation geometry while retaining statistically significant results is shown. Using the resulting estimate for the maximum observable distance, an approximate method for computing the coverage of the system is proposed. The expected daily and yearly variation of coverage depending on its own dynamics and the position of the Sun is analysed, showing that it has a small impact on the design process. The dependence of the coverage on constellation parameters such as altitude, inclination and distribution of satellites is investigated through parametric analysis, retrieving an estimate for the Pareto front of the system. Building upon the previous results, a random search method is shown to be effective in finding a design point lying on the Pareto front that is robust to both random satellite loss and deployment strategy. Finally, a reduced budget architecture is proposed to achieve acceptable performance while using only a few tens of satellites. The resulting work answers the problems of estimating and optimising the performance of a distributed system for space-based surveillance of the LEO region, a stepping stone for future cost–benefit analyses for the enhancement of space surveillance networks.
{"title":"Preliminary analysis and design of an optical space surveillance and tracking constellation for LEO coverage","authors":"A. D’Anniballe, L. Felicetti, S. Hobbs","doi":"10.1016/j.actaastro.2025.02.019","DOIUrl":"10.1016/j.actaastro.2025.02.019","url":null,"abstract":"<div><div>Accurately tracking space debris and operational satellites is the foundation of the long-term sustainability of space operations. To improve upon some of the inherent limitations of ground radars, a constellation of satellites carrying optical sensors for the surveillance of the Low Earth Orbit (LEO) region is analysed. This analysis aims to understand the performance drivers of such a system in terms of constellation geometry and provide a general methodology for the preliminary design of the system. First, a method for decoupling the design of the optical payload and the constellation geometry while retaining statistically significant results is shown. Using the resulting estimate for the maximum observable distance, an approximate method for computing the coverage of the system is proposed. The expected daily and yearly variation of coverage depending on its own dynamics and the position of the Sun is analysed, showing that it has a small impact on the design process. The dependence of the coverage on constellation parameters such as altitude, inclination and distribution of satellites is investigated through parametric analysis, retrieving an estimate for the Pareto front of the system. Building upon the previous results, a random search method is shown to be effective in finding a design point lying on the Pareto front that is robust to both random satellite loss and deployment strategy. Finally, a reduced budget architecture is proposed to achieve acceptable performance while using only a few tens of satellites. The resulting work answers the problems of estimating and optimising the performance of a distributed system for space-based surveillance of the LEO region, a stepping stone for future cost–benefit analyses for the enhancement of space surveillance networks.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 47-63"},"PeriodicalIF":3.1,"publicationDate":"2025-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143478586","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 : 2025-02-20DOI: 10.1016/j.actaastro.2025.02.032
Zizhou Wu , Xiaolei Liu , Hong Liu , Dawei Hu , Andrey Degermendzhi , Sergey Bartsev , Yuming Fu
The development of bioregenerative life support systems is essential for sustainable space exploration, reducing Earth-reliant resupply and ensuring human survival in extreme extraterrestrial conditions. A key research focus is the microgravity assessment of Biological Life Support Systems (BLSS), with a focus on gas exchange, critical for habitability. This study introduces a two-loop miniature closed artificial ecosystem (BMCAE) to analyze gas balance within plant-microbe systems under simulated microgravity. The BMCAE, featuring wheat for photosynthesis and microbes for waste management and nutrient cycling, is designed to accommodate spatial constraints while maintaining system stability. A 3D clinostat simulates microgravity to evaluate the BMCAE's capacity to support plant growth and microbial activity. Gas chromatography and next-generation sequencing assess the effects of simulated microgravity on plant and microbial dynamics. Results show that wheat growth responds positively to light intensity but is less robust under simulated microgravity, suggesting a negative impact on growth. Microbial community composition and diversity are significantly altered by simulated microgravity, particularly at lower temperatures, with an enrichment of Firmicutes and Bacillus, indicating microbial adaptation to microgravity. This research provides a theoretical and methodological basis for BMCAE application in space, aiding in the development of miniature ecosystems for BLSS, crucial for sustainable human life support in space.
{"title":"Microgravity's grip: Transforming plant-microbe interactions for space sustainability","authors":"Zizhou Wu , Xiaolei Liu , Hong Liu , Dawei Hu , Andrey Degermendzhi , Sergey Bartsev , Yuming Fu","doi":"10.1016/j.actaastro.2025.02.032","DOIUrl":"10.1016/j.actaastro.2025.02.032","url":null,"abstract":"<div><div>The development of bioregenerative life support systems is essential for sustainable space exploration, reducing Earth-reliant resupply and ensuring human survival in extreme extraterrestrial conditions. A key research focus is the microgravity assessment of Biological Life Support Systems (BLSS), with a focus on gas exchange, critical for habitability. This study introduces a two-loop miniature closed artificial ecosystem (BMCAE) to analyze gas balance within plant-microbe systems under simulated microgravity. The BMCAE, featuring wheat for photosynthesis and microbes for waste management and nutrient cycling, is designed to accommodate spatial constraints while maintaining system stability. A 3D clinostat simulates microgravity to evaluate the BMCAE's capacity to support plant growth and microbial activity. Gas chromatography and next-generation sequencing assess the effects of simulated microgravity on plant and microbial dynamics. Results show that wheat growth responds positively to light intensity but is less robust under simulated microgravity, suggesting a negative impact on growth. Microbial community composition and diversity are significantly altered by simulated microgravity, particularly at lower temperatures, with an enrichment of <em>Firmicutes</em> and <em>Bacillus</em>, indicating microbial adaptation to microgravity. This research provides a theoretical and methodological basis for BMCAE application in space, aiding in the development of miniature ecosystems for BLSS, crucial for sustainable human life support in space.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 80-92"},"PeriodicalIF":3.1,"publicationDate":"2025-02-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511614","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 : 2025-02-19DOI: 10.1016/j.actaastro.2025.02.029
Zhehong Wang , Weizong Wang , Jiaqi Yan , Zihan Wang
Rotating Magnetic Field (RMF) driven Field Reversed Configuration (FRC) plasmoid, originating from magnetic confined fusion research, has been developed as a novel propulsion method for high-power electric thrusters, namely the electrodeless Lorentz force (ELF) thruster. To address the dilemma between the high potential in theory and the low performance in the experiment, this paper numerically investigates the acceleration processes of FRC plasmoid in ELF thruster through a two-dimensional Hall Magnetohydrodynamics method. Direct comparisons with experiments have been made to verify the model. The correlation between the plasma behavior and the thruster performance has been obtained, providing insight into the experimental phenomena. The power scaling rule of thruster performance is obtained by investigating the influence of magnetic field strength and thruster geometry on the exhaust velocity and momentum of the FRC plasmoid. The simulation revealed that the low thruster performance in recent experiments is due to the low power input. High performance is expected to be achievable by scaling up the input power to hundreds kW or MW levels. Increasing the bias field to more than 1000 G, RMF frequency to 1 MHz, and RMF strength to hundreds Gausses, enables a per-shot momentum of mNs level of and specific impulse to be more than 5000 s. Additionally, the contribution of gas pressure force and Lorentz body force to the plasmoid acceleration has been analyzed, showing that the magnetic forces are dominant in high power regime, whereas gas forces being dominant in low power regime. The power scaling rule and geometry design principle formed in this work can help improve the ELF thruster performance, highlighting the necessity of testing prototypes under high-power conditions.
{"title":"Investigation on acceleration process of field reversed configuration plasmoid in an electrodeless Lorentz force thruster using Magnetohydrodynamics simulation","authors":"Zhehong Wang , Weizong Wang , Jiaqi Yan , Zihan Wang","doi":"10.1016/j.actaastro.2025.02.029","DOIUrl":"10.1016/j.actaastro.2025.02.029","url":null,"abstract":"<div><div>Rotating Magnetic Field (RMF) driven Field Reversed Configuration (FRC) plasmoid, originating from magnetic confined fusion research, has been developed as a novel propulsion method for high-power electric thrusters, namely the electrodeless Lorentz force (ELF) thruster. To address the dilemma between the high potential in theory and the low performance in the experiment, this paper numerically investigates the acceleration processes of FRC plasmoid in ELF thruster through a two-dimensional Hall Magnetohydrodynamics method. Direct comparisons with experiments have been made to verify the model. The correlation between the plasma behavior and the thruster performance has been obtained, providing insight into the experimental phenomena. The power scaling rule of thruster performance is obtained by investigating the influence of magnetic field strength and thruster geometry on the exhaust velocity and momentum of the FRC plasmoid. The simulation revealed that the low thruster performance in recent experiments is due to the low power input. High performance is expected to be achievable by scaling up the input power to hundreds kW or MW levels. Increasing the bias field to more than 1000 G, RMF frequency to 1 MHz, and RMF strength to hundreds Gausses, enables a per-shot momentum of mNs level of and specific impulse to be more than 5000 s. Additionally, the contribution of gas pressure force and Lorentz body force to the plasmoid acceleration has been analyzed, showing that the magnetic forces are dominant in high power regime, whereas gas forces being dominant in low power regime. The power scaling rule and geometry design principle formed in this work can help improve the ELF thruster performance, highlighting the necessity of testing prototypes under high-power conditions.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 1-14"},"PeriodicalIF":3.1,"publicationDate":"2025-02-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143464114","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 : 2025-02-19DOI: 10.1016/j.actaastro.2025.02.016
Xuan Xie, Fanghua Jiang, Junfeng Li
Space-based gravitational wave detectors have attracted considerable attention for their ability to detect low frequency gravitational waves generated by the universe’s most various sources. However, the high-precision detection requires extremely strict orbital insertion to maintain the configuration throughout the mission period. This paper presents an optimization method to correct orbital insertion errors using a low-frequency control strategy for long-duration, large-baseline spacecraft constellations. With active control, space-based gravitational wave detectors can mitigate initial orbit uncertainties. By presenting an evaluation algorithm and an estimating equation for fuel consumption and geometric indices, the segmented optimization method offers high computational efficiency. To adapt the control strategy to high-fidelity dynamics, an initial solution selection skill is proposed, and local refinements are employed. The application to the TianQin mission demonstrates the efficiency of the proposed method. The active control not only corrects the orbital insertion error but also reduces the geometric changes of the configuration by nearly 30% compared to an ideal deployment. The configuration maintenance strategy balances fuel efficiency and geometric stability, with a fuel consumption of only 421.57 m/s over the five-year mission period.
{"title":"Insertion error correction and configuration maintenance optimization for geocentric gravitational wave detectors","authors":"Xuan Xie, Fanghua Jiang, Junfeng Li","doi":"10.1016/j.actaastro.2025.02.016","DOIUrl":"10.1016/j.actaastro.2025.02.016","url":null,"abstract":"<div><div>Space-based gravitational wave detectors have attracted considerable attention for their ability to detect low frequency gravitational waves generated by the universe’s most various sources. However, the high-precision detection requires extremely strict orbital insertion to maintain the configuration throughout the mission period. This paper presents an optimization method to correct orbital insertion errors using a low-frequency control strategy for long-duration, large-baseline spacecraft constellations. With active control, space-based gravitational wave detectors can mitigate initial orbit uncertainties. By presenting an evaluation algorithm and an estimating equation for fuel consumption and geometric indices, the segmented optimization method offers high computational efficiency. To adapt the control strategy to high-fidelity dynamics, an initial solution selection skill is proposed, and local refinements are employed. The application to the TianQin mission demonstrates the efficiency of the proposed method. The active control not only corrects the orbital insertion error but also reduces the geometric changes of the configuration by nearly 30% compared to an ideal deployment. The configuration maintenance strategy balances fuel efficiency and geometric stability, with a fuel consumption of only 421.57 m/s over the five-year mission period.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 15-24"},"PeriodicalIF":3.1,"publicationDate":"2025-02-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143471185","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}
The purpose of this paper is to investigate the sustainability of space point-to-point transport and tourism based on its current development status and referring to the development history of aviation tourism. This study focuses on the following major points: (1) futuristic (suborbital and orbital) travel vs. traditional (aviation) travel, (2) infrastructure in suborbital and orbital tourisms vs. aviation tourism, (3) market demand vs. supply availability, (4) technology maturity vs. risk assessment, (5) development cost vs. ticket price (affordability), and (6) impact on the environment. In suborbital space tourism, the Virgin Galactic has completed seven commercial spaceflights (Galactic 1 to 7) from June 29, 2023 to June 8, 2024. Also, the Blue Origin has completed seven commercial spaceflights (NS-16, NS-18 to −22, NS-25 to −26 and NS-28) from July 20, 2021 to November 22, 2024. On the other hand, in the orbital space tourism, seven space passengers travelled eight times to the International Space Station (ISS) from 2001 to 2009 through the arrangements of Space Adventures along with Russian Roscosmos and Energia Corporation. On June 7, 2019, NASA announced a plan to open the ISS to space tourism. From September 16, 2021 to May 21, 2023, four commercial spaceflight missions have been made: all-civilian crew Inspiration4 mission, Ax-1, Ax-2 and Ax-3. Referring to the aviation tourism development history, the current space tourism status is mostly like its status at late 1950s. The creation of jet aircraft and the airline deregulation in 1978 can be considered as the two major watersheds from “adventure” to “prosperity” to “complete popularization” of the commercial airline industry, the passenger experience and the aviation tourism. At the civil aviation “adventure” stage in early 1940s, flying was very expensive and discomforts. Only business and wealthy travellers, a tiny fraction of the traveling public, could afford to fly. The current stage of space tourism is “adventure”, might mean it needs 20 more years to enter the “prosperity” stage and then the “popularization” stage. But there are many infrastructures still need be established such as: the space tourism industry chain, the legal and regulatory issues, the criteria for passenger screening and training, the insurance issue, the space port, the space traffic management and control, etc., etc. However, suppose we were standing at 1950s to outlook and prospect the civil aviation industry, the sustainability of space tourism is expectable based on the current development status.
{"title":"A study from aviation to suborbital point-to-point transport and tourism to orbital tourism","authors":"Yi-Wei (Eva) Chang , Chen-Joe Fong , Wen-Pin Wei , Chao-Yi Pan","doi":"10.1016/j.actaastro.2025.02.025","DOIUrl":"10.1016/j.actaastro.2025.02.025","url":null,"abstract":"<div><div>The purpose of this paper is to investigate the sustainability of space point-to-point transport and tourism based on its current development status and referring to the development history of aviation tourism. This study focuses on the following major points: (1) futuristic (suborbital and orbital) travel vs. traditional (aviation) travel, (2) infrastructure in suborbital and orbital tourisms vs. aviation tourism, (3) market demand vs. supply availability, (4) technology maturity vs. risk assessment, (5) development cost vs. ticket price (affordability), and (6) impact on the environment. In suborbital space tourism, the Virgin Galactic has completed seven commercial spaceflights (Galactic 1 to 7) from June 29, 2023 to June 8, 2024. Also, the Blue Origin has completed seven commercial spaceflights (NS-16, NS-18 to −22, NS-25 to −26 and NS-28) from July 20, 2021 to November 22, 2024. On the other hand, in the orbital space tourism, seven space passengers travelled eight times to the International Space Station (ISS) from 2001 to 2009 through the arrangements of Space Adventures along with Russian Roscosmos and Energia Corporation. On June 7, 2019, NASA announced a plan to open the ISS to space tourism. From September 16, 2021 to May 21, 2023, four commercial spaceflight missions have been made: all-civilian crew Inspiration4 mission, Ax-1, Ax-2 and Ax-3. Referring to the aviation tourism development history, the current space tourism status is mostly like its status at late 1950s. The creation of jet aircraft and the airline deregulation in 1978 can be considered as the two major watersheds from “adventure” to “prosperity” to “complete popularization” of the commercial airline industry, the passenger experience and the aviation tourism. At the civil aviation “adventure” stage in early 1940s, flying was very expensive and discomforts. Only business and wealthy travellers, a tiny fraction of the traveling public, could afford to fly. The current stage of space tourism is “adventure”, might mean it needs 20 more years to enter the “prosperity” stage and then the “popularization” stage. But there are many infrastructures still need be established such as: the space tourism industry chain, the legal and regulatory issues, the criteria for passenger screening and training, the insurance issue, the space port, the space traffic management and control, etc., etc. However, suppose we were standing at 1950s to outlook and prospect the civil aviation industry, the sustainability of space tourism is expectable based on the current development status.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"231 ","pages":"Pages 93-102"},"PeriodicalIF":3.1,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511601","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}
扫码关注我们
求助内容：
应助结果提醒方式：
京公网安备 11010802042870号