Pub Date : 2025-03-01DOI: 10.1016/j.sspwt.2025.03.005
Shuo Bian , Size Ai , Jianzheng Wei , Zhimin Xie , Guochang Lin , Dongjie Zhang , Huifeng Tan , Qingxiang Ji
With the growing global energy demand and the pursuit of sustainable energy, solar energy has received widespread attention as a clean and renewable energy source. A structural design of an inflatable, large-scale solar concentrating reflector based on in-orbit assembly is proposed in this paper. The axisymmetric inflated reflector surface is inversely designed through membrane mechanics, and the internal pressures to maintain the reflector surface morphology at different orbital positions and the tiny deformation produced by the reflecting surface under the action of the uniform pressure are determined. A inflatable-rigidizable support structure is prepared by using a rigidizable aramid fabric-reinforced composite. The support structure used to the parabolic reflecting surface is designed, and the diameter and spacing distance of the resistance wire of the heating layer are determined by electrothermal simulation; the combination of solar radiation and electric heating is used to rigidize the reflector in orbit, and the corresponding electric heating time at different orbital positions is also analyzed by in orbit simulation. The heating voltage, folding radius and folding method of the rigidizable support structure are determined through the experimental design, and the folding and deployment experiments are carried out by using the heating and internal pressure and the final shape recovery rate of the support tube is approximately 100 %, which verifies the feasibility of its folding and deployment.
{"title":"Structural design and performance analysis of large inflatable solar membrane reflector","authors":"Shuo Bian , Size Ai , Jianzheng Wei , Zhimin Xie , Guochang Lin , Dongjie Zhang , Huifeng Tan , Qingxiang Ji","doi":"10.1016/j.sspwt.2025.03.005","DOIUrl":"10.1016/j.sspwt.2025.03.005","url":null,"abstract":"<div><div>With the growing global energy demand and the pursuit of sustainable energy, solar energy has received widespread attention as a clean and renewable energy source. A structural design of an inflatable, large-scale solar concentrating reflector based on in-orbit assembly is proposed in this paper. The axisymmetric inflated reflector surface is inversely designed through membrane mechanics, and the internal pressures to maintain the reflector surface morphology at different orbital positions and the tiny deformation produced by the reflecting surface under the action of the uniform pressure are determined. A inflatable-rigidizable support structure is prepared by using a rigidizable aramid fabric-reinforced composite. The support structure used to the parabolic reflecting surface is designed, and the diameter and spacing distance of the resistance wire of the heating layer are determined by electrothermal simulation; the combination of solar radiation and electric heating is used to rigidize the reflector in orbit, and the corresponding electric heating time at different orbital positions is also analyzed by in orbit simulation. The heating voltage, folding radius and folding method of the rigidizable support structure are determined through the experimental design, and the folding and deployment experiments are carried out by using the heating and internal pressure and the final shape recovery rate of the support tube is approximately 100 %, which verifies the feasibility of its folding and deployment.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"2 1","pages":"Pages 54-64"},"PeriodicalIF":0.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143800473","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2025-03-01DOI: 10.1016/j.sspwt.2025.02.002
Weiya Zhou , Zhe Ye , Shunan Wu , Yuanyuan Li
The coupling dynamics problem between the walking robot and large space structures during on-orbit assembly is investigated in this paper. The quadruped walking robot is first chosen as the assembly robot, which is equivalent to a spring-mass-damper system with seven degrees of freedom. The primary goal of the robot is to stably walk on a large space structure while carrying an assembly module to a designated location for assembly. Combining with the characteristic of incrementally increasing of the large space structure, a revival dynamic modeling method is then presented. On this basis, the coupled dynamic model of the robot and the space truss structure is developed. To simulate robot walking, the motion gait of the quadruped walking robot is designed as a diagonal alternating gait. The moving load are considered as disturbance inputs associated with the truss, and an active vibration controller is developed to deal with the disturbance. The numerical simulation of a quadruped walking robot moving on a space truss structure is finally presented with different cases. The results demonstrate that the quadruped walking robot movement has a significant influence on the space truss structure, and the mutual disturbances between the two are effectively suppressed by the proposed controller.
{"title":"Coupling dynamic modeling and vibration control of quadruped-robot and large space structure during on-orbit assembly","authors":"Weiya Zhou , Zhe Ye , Shunan Wu , Yuanyuan Li","doi":"10.1016/j.sspwt.2025.02.002","DOIUrl":"10.1016/j.sspwt.2025.02.002","url":null,"abstract":"<div><div>The coupling dynamics problem between the walking robot and large space structures during on-orbit assembly is investigated in this paper. The quadruped walking robot is first chosen as the assembly robot, which is equivalent to a spring-mass-damper system with seven degrees of freedom. The primary goal of the robot is to stably walk on a large space structure while carrying an assembly module to a designated location for assembly. Combining with the characteristic of incrementally increasing of the large space structure, a revival dynamic modeling method is then presented. On this basis, the coupled dynamic model of the robot and the space truss structure is developed. To simulate robot walking, the motion gait of the quadruped walking robot is designed as a diagonal alternating gait. The moving load are considered as disturbance inputs associated with the truss, and an active vibration controller is developed to deal with the disturbance. The numerical simulation of a quadruped walking robot moving on a space truss structure is finally presented with different cases. The results demonstrate that the quadruped walking robot movement has a significant influence on the space truss structure, and the mutual disturbances between the two are effectively suppressed by the proposed controller.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"2 1","pages":"Pages 1-9"},"PeriodicalIF":0.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143800559","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2025-03-01DOI: 10.1016/j.sspwt.2025.02.001
Yanlong Zhang , Pengzhen Guo , Mengfan Tian , Huazhi Chen , Rongqiang Liu , Zongquan Deng , Lifang Li
Deep space exploration missions and the construction of planetary research stations impose strict demands on energy self-sufficiency systems. Solar energy, due to its abundant availability and sustainability, has become the preferred solution. However, extreme environmental conditions in space – including drastic temperature fluctuations, vacuum environments, high-energy particles, and intense radiation – pose significant challenges to the performance and lifespan of solar energy systems. Concentration technology, which enhances photoelectric and photothermal conversion efficiency by focusing sunlight, is crucial for space missions. This review examines the primary environmental factors affecting the performance of solar concentrators, including solar irradiance, thermal cycling, vacuum-induced outgassing, radiation effects, and impacts from micrometeoroids and orbital debris. The analysis focuses on three types of high-temperature concentrators: Fresnel lenses, Scheffler concentrators, and parabolic dish concentrators. Fresnel lenses are characterized by low cost and simple structure but are susceptible to optical degradation at high temperatures. Scheffler concentrators utilize geometric optimization to improve uniformity of light distribution, while parabolic dish concentrators achieve high optical efficiency, making them suitable for high-energy applications though requiring precise solar tracking. Performance comparisons in the thermal power range of 0 to 25 kW reveal that parabolic dish concentrators excel in high-power scenarios with greater efficiency and smaller aperture sizes. Conversely, Fresnel lenses and Scheffler concentrators are more effective in medium to low-temperature applications. Based on these findings, this review emphasizes the need to select concentrators according to mission requirements and outlines future research directions. These include the development of advanced materials, optimized optical designs, and improvements in system integration to enhance the adaptability and reliability of solar concentration technologies in deep space missions.
{"title":"A review of solar concentration technology applications in deep space exploration: Environmental adaptability and performance comparison","authors":"Yanlong Zhang , Pengzhen Guo , Mengfan Tian , Huazhi Chen , Rongqiang Liu , Zongquan Deng , Lifang Li","doi":"10.1016/j.sspwt.2025.02.001","DOIUrl":"10.1016/j.sspwt.2025.02.001","url":null,"abstract":"<div><div>Deep space exploration missions and the construction of planetary research stations impose strict demands on energy self-sufficiency systems. Solar energy, due to its abundant availability and sustainability, has become the preferred solution. However, extreme environmental conditions in space – including drastic temperature fluctuations, vacuum environments, high-energy particles, and intense radiation – pose significant challenges to the performance and lifespan of solar energy systems. Concentration technology, which enhances photoelectric and photothermal conversion efficiency by focusing sunlight, is crucial for space missions. This review examines the primary environmental factors affecting the performance of solar concentrators, including solar irradiance, thermal cycling, vacuum-induced outgassing, radiation effects, and impacts from micrometeoroids and orbital debris. The analysis focuses on three types of high-temperature concentrators: Fresnel lenses, Scheffler concentrators, and parabolic dish concentrators. Fresnel lenses are characterized by low cost and simple structure but are susceptible to optical degradation at high temperatures. Scheffler concentrators utilize geometric optimization to improve uniformity of light distribution, while parabolic dish concentrators achieve high optical efficiency, making them suitable for high-energy applications though requiring precise solar tracking. Performance comparisons in the thermal power range of 0 to 25 kW reveal that parabolic dish concentrators excel in high-power scenarios with greater efficiency and smaller aperture sizes. Conversely, Fresnel lenses and Scheffler concentrators are more effective in medium to low-temperature applications. Based on these findings, this review emphasizes the need to select concentrators according to mission requirements and outlines future research directions. These include the development of advanced materials, optimized optical designs, and improvements in system integration to enhance the adaptability and reliability of solar concentration technologies in deep space missions.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"2 1","pages":"Pages 43-53"},"PeriodicalIF":0.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143800564","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2025-03-01DOI: 10.1016/j.sspwt.2025.03.002
Dongxu Wang, Guanheng Fan, Xintong Li, Yinchun Du, Kunpeng Liu
Among numerous space solar power systems, the concentrator systems is more favored due to the size of the battery array and the emission cost. Space concentrators generally consider using low-quality thin film structures, which, although lightweight, have large deformation errors. When studying the concentration characteristics, slope error is generally used to describe the error, but the surface error of thin film structures is generally measured by the root mean square value (RMS). We found that the deformation of thin film structures has characteristic dimensions, that is, the deformation within a certain size range shows monotonic changes. We can use the quotient of surface error and feature size instead of slope error for optical calculations. In addition, within a certain deviation range of light distribution, we can use a plane instead of a surface to simplify the model when modeling. Based on these theories, we conducted numerical examples to verify and obtained analysis results.
{"title":"Concentration error analysis of space-based thin-film reflectors","authors":"Dongxu Wang, Guanheng Fan, Xintong Li, Yinchun Du, Kunpeng Liu","doi":"10.1016/j.sspwt.2025.03.002","DOIUrl":"10.1016/j.sspwt.2025.03.002","url":null,"abstract":"<div><div>Among numerous space solar power systems, the concentrator systems is more favored due to the size of the battery array and the emission cost. Space concentrators generally consider using low-quality thin film structures, which, although lightweight, have large deformation errors. When studying the concentration characteristics, slope error is generally used to describe the error, but the surface error of thin film structures is generally measured by the root mean square value (RMS). We found that the deformation of thin film structures has characteristic dimensions, that is, the deformation within a certain size range shows monotonic changes. We can use the quotient of surface error and feature size instead of slope error for optical calculations. In addition, within a certain deviation range of light distribution, we can use a plane instead of a surface to simplify the model when modeling. Based on these theories, we conducted numerical examples to verify and obtained analysis results.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"2 1","pages":"Pages 27-32"},"PeriodicalIF":0.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143800562","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2025-03-01DOI: 10.1016/j.sspwt.2025.03.001
Sicheng Wang, Dayu Zhang, Xiaofei Ma, Yongbo Ye, Zexing Yu, Hao Li, Huanxiao Li
Space deployable antennas are extensively utilized in space-based communication, deep space exploration, and earth observation. As the demands for capacity and data transmission rates in human space-based communication continue to rise, the requirement for larger antenna apertures becomes increasingly critical. Traditional single-deployable structures are insufficient to meet these aperture requirements. On-orbit assembled antennas present a viable solution to the challenges associated with folding, transportation, and deployment of large structures, thereby overcoming the aperture limitations inherent in conventional designs. This innovation is particularly pertinent for large aperture space antennas required in space-based communication and related fields. The ability to adjust modules is a foundational aspect of realizing on-orbit assembly antennas. This paper provides a comprehensive review of the current research on module adjustment in space on-orbit assembly antennas. Initially, the existing research landscape of space on-orbit assembly antennas is outlined. Subsequently, the progress made in module adjustment is categorized into two main approaches: inter-module adjustment and self-adjustment of modules. The paper also examines various actuators that can serve as critical components in the design of module adjustment systems. Building upon this analysis, key technologies essential for effective module adjustment are summarized, and future development trends in this area are proposed.
{"title":"A review of module adjustment for space on-orbit assembled antenna","authors":"Sicheng Wang, Dayu Zhang, Xiaofei Ma, Yongbo Ye, Zexing Yu, Hao Li, Huanxiao Li","doi":"10.1016/j.sspwt.2025.03.001","DOIUrl":"10.1016/j.sspwt.2025.03.001","url":null,"abstract":"<div><div>Space deployable antennas are extensively utilized in space-based communication, deep space exploration, and earth observation. As the demands for capacity and data transmission rates in human space-based communication continue to rise, the requirement for larger antenna apertures becomes increasingly critical. Traditional single-deployable structures are insufficient to meet these aperture requirements. On-orbit assembled antennas present a viable solution to the challenges associated with folding, transportation, and deployment of large structures, thereby overcoming the aperture limitations inherent in conventional designs. This innovation is particularly pertinent for large aperture space antennas required in space-based communication and related fields. The ability to adjust modules is a foundational aspect of realizing on-orbit assembly antennas. This paper provides a comprehensive review of the current research on module adjustment in space on-orbit assembly antennas. Initially, the existing research landscape of space on-orbit assembly antennas is outlined. Subsequently, the progress made in module adjustment is categorized into two main approaches: inter-module adjustment and self-adjustment of modules. The paper also examines various actuators that can serve as critical components in the design of module adjustment systems. Building upon this analysis, key technologies essential for effective module adjustment are summarized, and future development trends in this area are proposed.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"2 1","pages":"Pages 10-19"},"PeriodicalIF":0.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143800560","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-12-01DOI: 10.1016/j.sspwt.2024.12.006
Jintai Wu , Qiaowei Yuan , Takayuki Okada , Bo Yang
This paper investigates a novel method for deriving 4-port S-parameters for the E-MIMO approach. In this method, only the self-S-matrices of the transmitting antennas () and receiving antennas () need to be pre-calculated or measured. The coupling matrix ( or ), which depends on the position of the receiving element, can be estimated using the proposed simplified method. Since the receiving antenna is positioned in the far-field, the Friis transmission formula is applied to estimate the amplitude of the elements in the coupling matrix ( or ), while the array factor is used to estimate the phase of these elements. The S-matrices for a 3 × 1 array, obtained through conventional simulation, measurement, and the proposed estimation method, are compared. Furthermore, these matrices are applied to E-MIMO to compare their radiation patterns and power transmission efficiencies. The results demonstrate that the proposed estimation method achieves radiation patterns and power transmission efficiencies that are closely comparable to those obtained using the conventional method, confirming the effectiveness of the proposed method.
{"title":"An estimation method of the 4-port S-parameters used for the E-MIMO approach","authors":"Jintai Wu , Qiaowei Yuan , Takayuki Okada , Bo Yang","doi":"10.1016/j.sspwt.2024.12.006","DOIUrl":"10.1016/j.sspwt.2024.12.006","url":null,"abstract":"<div><div>This paper investigates a novel method for deriving 4-port S-parameters for the E-MIMO approach. In this method, only the self-S-matrices of the transmitting antennas (<span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>T</mi><mi>T</mi></mrow></msub></math></span>) and receiving antennas (<span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>R</mi><mi>R</mi></mrow></msub></math></span>) need to be pre-calculated or measured. The coupling matrix (<span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>R</mi><mi>T</mi></mrow></msub></math></span> or <span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>T</mi><mi>R</mi></mrow></msub></math></span>), which depends on the position of the receiving element, can be estimated using the proposed simplified method. Since the receiving antenna is positioned in the far-field, the Friis transmission formula is applied to estimate the amplitude of the elements in the coupling matrix (<span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>R</mi><mi>T</mi></mrow></msub></math></span> or <span><math><msub><mrow><mi>S</mi></mrow><mrow><mi>T</mi><mi>R</mi></mrow></msub></math></span>), while the array factor is used to estimate the phase of these elements. The S-matrices for a 3 × 1 array, obtained through conventional simulation, measurement, and the proposed estimation method, are compared. Furthermore, these matrices are applied to E-MIMO to compare their radiation patterns and power transmission efficiencies. The results demonstrate that the proposed estimation method achieves radiation patterns and power transmission efficiencies that are closely comparable to those obtained using the conventional method, confirming the effectiveness of the proposed method.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"1 3","pages":"Pages 148-151"},"PeriodicalIF":0.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143216620","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-12-01DOI: 10.1016/j.sspwt.2024.12.005
Xin Xu , Xian-Qi Lin
This paper presents a rectenna with mixing functionality, specifically designed for simultaneous wireless information and power transfer (SWIPT) systems. The antenna uses an electric dipole structure, which not only features a low profile but also provides high gain, significantly enhancing signal reception efficiency in the SWIPT receiver architecture. Simultaneously, the rectifier integrates a mixing function, allowing simultaneous processing of information and energy signals within the receiver, thus achieving highly efficient resource utilization. Compared with traditional architectures, this design greatly increases the integration of SWIPT receivers, reducing both manufacturing cost and design complexity, which aligns well with the growing demands of compact, high-efficiency modern wireless communication systems. To validate the effectiveness of this design, this paper conducts detailed design, fabrication, and testing of the antenna and integrated rectifying-mixer (IRM) circuit and sets up a practical SWIPT system for experimental verification. The results show that this rectenna can effectively meet the requirements of SWIPT applications under various operating conditions, achieving simultaneous reception of information and energy while demonstrating excellent transmission efficiency and interference resistance. These results confirm the high practicality and potential for widespread application of the proposed rectenna in SWIPT systems.
{"title":"A rectenna with mixing functionality for simultaneous wireless information and power transfer (SWIPT)","authors":"Xin Xu , Xian-Qi Lin","doi":"10.1016/j.sspwt.2024.12.005","DOIUrl":"10.1016/j.sspwt.2024.12.005","url":null,"abstract":"<div><div>This paper presents a rectenna with mixing functionality, specifically designed for simultaneous wireless information and power transfer (SWIPT) systems. The antenna uses an electric dipole structure, which not only features a low profile but also provides high gain, significantly enhancing signal reception efficiency in the SWIPT receiver architecture. Simultaneously, the rectifier integrates a mixing function, allowing simultaneous processing of information and energy signals within the receiver, thus achieving highly efficient resource utilization. Compared with traditional architectures, this design greatly increases the integration of SWIPT receivers, reducing both manufacturing cost and design complexity, which aligns well with the growing demands of compact, high-efficiency modern wireless communication systems. To validate the effectiveness of this design, this paper conducts detailed design, fabrication, and testing of the antenna and integrated rectifying-mixer (IRM) circuit and sets up a practical SWIPT system for experimental verification. The results show that this rectenna can effectively meet the requirements of SWIPT applications under various operating conditions, achieving simultaneous reception of information and energy while demonstrating excellent transmission efficiency and interference resistance. These results confirm the high practicality and potential for widespread application of the proposed rectenna in SWIPT systems.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"1 3","pages":"Pages 183-189"},"PeriodicalIF":0.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143216622","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-12-01DOI: 10.1016/j.sspwt.2024.12.004
Yan Liang, XinHua Yu, LuCong Lu, JinJun Mo, YiYing Wang
In the application of the wireless power transfer process for the space solar power station, the continuous exposure to the electromagnetic wave could lead to significant thermal effect on human health. Therefore, this paper investigates the accumulated electromagnetic radiation at 5.8 GHz by the temperature rise on a practical arm model which comes from a Chinese female (26-year-old, 162 cm high, and 50kg weight) and the physiological condition setting is included. By comparing the external electromagnetic distributions on the body surfaces facing and facing away from the illumination source, the corresponding differences of two benchmark lines are obtained for both the simulated and measured situations where the normalized values are close in the whole band. Through this indirect analysis consistency for the surface field distribution, the interior field distributions of three different layers (skin, fat, and muscle) are obtained depending on the simulated results. Then, the temperature rise effects are evaluated of which the fat has the highest temperature rise in a short long time than those of the other two layers, and it is the energy source to make all the layers eventually turn to be relatively steady for the 2-hour period.
{"title":"Temperature rise in a realistic arm model illuminated by plane electromagnetic wave","authors":"Yan Liang, XinHua Yu, LuCong Lu, JinJun Mo, YiYing Wang","doi":"10.1016/j.sspwt.2024.12.004","DOIUrl":"10.1016/j.sspwt.2024.12.004","url":null,"abstract":"<div><div>In the application of the wireless power transfer process for the space solar power station, the continuous exposure to the electromagnetic wave could lead to significant thermal effect on human health. Therefore, this paper investigates the accumulated electromagnetic radiation at 5.8 GHz by the temperature rise on a practical arm model which comes from a Chinese female (26-year-old, 162 cm high, and 50kg weight) and the physiological condition setting is included. By comparing the external electromagnetic distributions on the body surfaces facing and facing away from the illumination source, the corresponding differences of two benchmark lines are obtained for both the simulated and measured situations where the normalized values are close in the whole band. Through this indirect analysis consistency for the surface field distribution, the interior field distributions of three different layers (skin, fat, and muscle) are obtained depending on the simulated results. Then, the temperature rise effects are evaluated of which the fat has the highest temperature rise in a short long time than those of the other two layers, and it is the energy source to make all the layers eventually turn to be relatively steady for the 2-hour period.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"1 3","pages":"Pages 158-164"},"PeriodicalIF":0.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143216624","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-12-01DOI: 10.1016/j.sspwt.2024.12.001
Zhou-Lin Fan, Shuo Cao, Xue-Xia Yang
A high efficient C-band circularly polarized rectenna array with low-profile and lightweight for wireless power transmission of space solar power stations is proposed and designed in this paper. The receiving antenna is an aperture-coupled microstrip quasi-square patch. The patch simultaneously excites two orthogonal modes of TM10 and TM01, which have a phase difference of 90° by the perturbation method, so that the antenna operates in a circularly polarized state. The rectifier circuit is designed by microstrip lines in a parallel topology, and it consists of a stepped impedance matching network, a Schottky diode, two sector-branches as pass-through filter and a load. The input impedance of the rectifier and the characteristic impedance of the antenna feedline are both 50 for being directly integrated into a rectenna. This rectenna has the advantages of low profile and scalability. The rectenna element, 3 × 3 and 4 × 4 subarrays are simulated and tested with good agreement being obtained. The measured results show that the rectification efficiencies of the element and the two subarrays are 73.1%, 72.7%, and 71.3% respectively at the center frequency of 5.76 GHz. Finally, a large rectenna array with 0.7 m aperture is designed to verify the scalability of the design. It will obtain 16.7 W of DC power at an efficiency of 65%. The rectenna has a profile of 1.61 mm and a surface density of less than 1.2 kg/m2.
{"title":"High efficient C-band circularly polarized rectenna array with low-profile and lightweight","authors":"Zhou-Lin Fan, Shuo Cao, Xue-Xia Yang","doi":"10.1016/j.sspwt.2024.12.001","DOIUrl":"10.1016/j.sspwt.2024.12.001","url":null,"abstract":"<div><div>A high efficient C-band circularly polarized rectenna array with low-profile and lightweight for wireless power transmission of space solar power stations is proposed and designed in this paper. The receiving antenna is an aperture-coupled microstrip quasi-square patch. The patch simultaneously excites two orthogonal modes of TM<sub>10</sub> and TM<sub>01</sub>, which have a phase difference of 90° by the perturbation method, so that the antenna operates in a circularly polarized state. The rectifier circuit is designed by microstrip lines in a parallel topology, and it consists of a stepped impedance matching network, a Schottky diode, two sector-branches as pass-through filter and a load. The input impedance of the rectifier and the characteristic impedance of the antenna feedline are both 50 <span><math><mi>Ω</mi></math></span> for being directly integrated into a rectenna. This rectenna has the advantages of low profile and scalability. The rectenna element, 3 × 3 and 4 × 4 subarrays are simulated and tested with good agreement being obtained. The measured results show that the rectification efficiencies of the element and the two subarrays are 73.1%, 72.7%, and 71.3% respectively at the center frequency of 5.76 GHz. Finally, a large rectenna array with 0.7 m aperture is designed to verify the scalability of the design. It will obtain 16.7 W of DC power at an efficiency of 65%. The rectenna has a profile of 1.61 mm and a surface density of less than 1.2 kg/m<sup>2</sup>.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"1 3","pages":"Pages 152-157"},"PeriodicalIF":0.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143216623","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-12-01DOI: 10.1016/j.sspwt.2024.12.002
Qiankun Xu, Fengling Peng, Xing Chen
Microwave wireless power transfer (WPT) technology enables the efficient, contactless transmission of energy through electromagnetic waves, with widespread applications in wireless charging, remote energy transmission, and satellite-based power harvesting, holding significant social, economic, and environmental implications. A ground-to-air WPT system is presented as a sample, this study investigates the impact of antenna polarization modes on the transmission efficiency of WPT systems for moving targets. Numerical simulations of transmission coefficients are conducted under various deflection angles, with transmission distances at both near-field (103 mm) and far-field (350 mm). The three polarization modes are single-line polarization (SL), dual-line polarization (DL), and circular polarization (CP). The results show that the polarization configuration with a single-line polarized transmitting array and a dual-line polarized receiving array (SL–DL) exhibits superior transmission efficiency. In the near field (103 mm), the linear transmission coefficient values of SL–DL are on average 0.08 and 0.06 higher compared to SL–SL and CP–CP at various angles, respectively. In the far field (350 mm), the corresponding transmission coefficient values increase by an average of 0.02 and 0.016.
{"title":"Polarization design of microwave wireless transmission systems for moving targets","authors":"Qiankun Xu, Fengling Peng, Xing Chen","doi":"10.1016/j.sspwt.2024.12.002","DOIUrl":"10.1016/j.sspwt.2024.12.002","url":null,"abstract":"<div><div>Microwave wireless power transfer (WPT) technology enables the efficient, contactless transmission of energy through electromagnetic waves, with widespread applications in wireless charging, remote energy transmission, and satellite-based power harvesting, holding significant social, economic, and environmental implications. A ground-to-air WPT system is presented as a sample, this study investigates the impact of antenna polarization modes on the transmission efficiency of WPT systems for moving targets. Numerical simulations of transmission coefficients are conducted under various deflection angles, with transmission distances at both near-field (103 mm) and far-field (350 mm). The three polarization modes are single-line polarization (SL), dual-line polarization (DL), and circular polarization (CP). The results show that the polarization configuration with a single-line polarized transmitting array and a dual-line polarized receiving array (SL–DL) exhibits superior transmission efficiency. In the near field (103 mm), the linear transmission coefficient values of SL–DL are on average 0.08 and 0.06 higher compared to SL–SL and CP–CP at various angles, respectively. In the far field (350 mm), the corresponding transmission coefficient values increase by an average of 0.02 and 0.016.</div></div>","PeriodicalId":101177,"journal":{"name":"Space Solar Power and Wireless Transmission","volume":"1 3","pages":"Pages 165-170"},"PeriodicalIF":0.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143279104","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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