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    System design and key technologies of No.4 land exploration satellite 01
    ZHANG Qingjun, NI Chong, DAI Chao, LIU Liping, TANG Zhihua, SHU Weiping
    Chinese Space Science and Technology    2025, 45 (1): 1-11.   DOI: 10.16708/j.cnki.1000-758X.2025.0001
    Abstract1149)      PDF(pc) (8217KB)(1142)      
    In order to solve the problem of small imaging width and long revisiting time of low orbit SAR,China developed the No.4 land exploration satellite 01,which is a scientific satellite in the medium and long term development plan of national civil space infrastructure (2015-2025),and is the world′s first geosynchronous SAR satellite.Using the advantages of the geosynchronous orbit,the revisiting time of the same place can be reduced from the day level of low orbit satellite to the hour level,and the width can be increased from the hundred-kilometer level of low orbit satellite to the thousand-kilometer level,which can provide strong support for the effective implementation of disaster emergency response.For the new system of geosynchronous SAR microwave imaging,a series of key technologies are developed,such as microwave imaging for geosynchronous SAR,ultra-large power space-borne microwave transmission,ultra-large aperture space-borne antenna,large-flexibility and high-precision attitude stability control,intense pulse high-quality large power supply,integrated efficient thermal management for payload and platform,and integrated satellite-ground high-precision orbit determination.The satellite has the capability of quick revisit,large width,all-day and all-weather observation.The overall design of the satellite is introduced,and the technical innovation is summarized.Through the evaluation of the preliminary test results for the satellite in orbit,the geosynchronous SAR images have clear texture and good quality,which can meet the requirements of disaster prevention and reduction,land resource exploration and other tasks.
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    Performance analysis of on-orbit testing of mechanically pumped two-phase loop for spacecraft
    MENG Qingliang, WEI Guanglang, YU Feng, YANG Tao, ZHAO Zhenming, ZHU Xu
    Chinese Space Science and Technology    2025, 45 (4): 70-78.   DOI: 10.16708/j.cnki.1000-758X.2025.0059
    Abstract305)      PDF(pc) (7542KB)(698)      
    Mechanistically pumped two-phase loop (MPTL) is a two-phase heat transfer device, which possesses the strong heat transfer ability through the release of latent heat of liquid and vapor phase change during flow boiling process. MPTL shows a promising prospect in thermal control of spacecraft.The objective of the present study is to focus on the working characteristics and stability of MPTL under the microgravtiy environment on orbit. One MPTL, which included one shield centrifugal pump, one two-phase temperature controlling accumulator and one micro channel evaporator, was designed and constructed to investigate the characteristics of start-up, phase-changing heat transfer, and temperature-controlling for MPTL aboard one satellite. Test results shows that MPTL shows good working performance and stable operating behavior in microgravity environment. The two-phase accumulator presents good heat transfer performance under microgravity condition. Its temperature control accuracy reaches to ±0.1K. The passive cooling function of accumulator is validated, and its cooling rate reaches to 1℃/min. The temperature difference between the measuring points of vapor and liquid phase for the accumulator are in the range of 0.3~1.0K when the pump is working. The temperature control accuracy of the evaporator is in the range of ±0.1~±0.3K at the two rotation speeds. Superheating phenomenon takes place during the phase changing process of the loop and it leads to a higher 7~8K temperature at the evaporator’s outlet than the temperature control point. By comparing the results under the two rotation speeds, the superheat time and superheat temperature are related with the rotation speeds. The two-phase temperature controlling accumulator using the capillary structures can assure the function of high-precision temperature control and high-efficiency two-phase fluid management and control for MPTL under the microgravity condition. The phase transition characteristic for vapor-liquid is related to the mass flowrate of the loop. The stability of temperature on the evaporator is related to the fluid quality of its interior fluid. The study would contribute to the engineering design basis for the technology of two-phase flow and heat transfer, and would promote the development of active two-phase thermal control technology for space.

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    Review on spacecraft autonomous decision-making and planning for orbital threat avoidance
    GAO Wanying, WU Jianfa, WEI Chunling
    Chinese Space Science and Technology    2024, 44 (4): 71-89.   DOI: 10.16708/j.cnki.1000-758X.2024.0059
    Abstract504)      PDF(pc) (2018KB)(1437)      
    The accumulation of space debris,the deployment of large-scale satellite constellations,and intensified spatial competition have led to a rapid increase in the number of orbital threats,seriously threatening the safety and stability of spacecraft.Research into spacecraft autonomous decision-making and planning for orbital threats is crucial to securing China's space assets.Confronted with complex scenarios characterized by high dynamics,time-varying constraints,incomplete or imperfect information,and multiple concurrent threats,this research faces several practical challenges.This review examines the research status of spacecraft autonomous decision-making and planning,discusses key technologies including problem modeling,decision-making,maneuver planning,intelligent decision-making and planning,and concludes with suggestions for future research.
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    System design of spaceborne large aperture perimeter truss antenna
    FENG Tao, ZAHNG Qingjun, LIN Kunyang, WANG Lipeng, ZHANG Qiao, YANG Jungang, XIAO Yong
    Chinese Space Science and Technology    2025, 45 (1): 24-33.   DOI: 10.16708/j.cnki.1000-758X.2025.0003
    Abstract611)      PDF(pc) (9223KB)(701)      
    The perimeter truss antenna is the ideal structure of the spaceborne deployable antenna with very large aperture, which is the key payload for high-orbit communication and high-orbit remote sensing satellite applications. The spaceborne perimeter truss antenna is a typical prestressed structure composed of the surrounding truss and cable network system. The accuracy of surface and the fundamental frequency of antenna are the main performance indexes of antennas. On-orbit reliable deployment is the premise of on-orbit application, and reliable deployment is the most important part of antenna design. The influence of ring antenna system parameters on on-orbit performance is analyzed. Based on the analysis of the deployable power system and the transmission power system, the influence of system parameters of the ring antenna on the deployable reliability is expounded. The method of evaluating the on-orbit performance design by structural statics and the deployable reliability by dynamic means are proposed. The design flow of spaceborne large aperture perimeter truss antenna system is defined by strength verification and on-board lock-release design by structural dynamics method, and the optimization strategy of each design parameter is proposed. It provides a reference for technical research and engineering development of the larger aperture spaceborne deployable antenna in the future.
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    The load design and implementation of LT-4 space-borne SAR
    LI Guangting, TAN Xiaomin, LI Caipin, NIE Shikang, LIN Chenchen, ZHU Yalin, LIU Bo
    Chinese Space Science and Technology    2025, 45 (4): 123-130.   DOI: 10.16708/j.cnki.1000-758X.2025.0064
    Abstract470)      PDF(pc) (5812KB)(625)      

    In order to meet the requirement of high revisit and wide coverage of SAR system for national disaster prevention and reduction, the world’s first geosynchronous orbit SAR named Land Exploration 4rd(LT-4) was designed and developed. The satellite uses a ring-shaped reflector antenna and combined with phased array feed system, operating at L-band. The particularity of the orbit makes the satellite naturally have the characteristics of high revisit and wide coverage. In order to give a comprehensive description of the SAR payload system of LT-4, the characteristics of high orbit SAR which are different from low orbit SAR are described, and the key performance parameters of SAR payload are given. Then the working process of SAR payload is introduced, and the main functions and performance of the key equipment of SAR payload are expounded. At last, the history of load development for more than ten years is briefly described, and the load integration test items and test verification are given. The world's first high-orbit SAR image is obtained when the SAR payload works for the first time on orbit. The image information is rich and the payload’s on-orbit state is stable. The imaging results show that the SAR payload design is reasonable and the ground test and verification are sufficient, which can provide favorable information support for national disaster prevention and reduction.

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    Research on lunar base based on cave
    LI Linling, LIU Jingang, HOU Yukui, LIU Wei, LI Mingfu, YIN Shuohui, WANG Lei, XU Mengchuan, Peng Jing, SUN Zezhou
    Chinese Space Science and Technology    2025, 45 (3): 9-18.   DOI: 10.16708/j.cnki.1000-758X.2025.0034
    Abstract709)      PDF(pc) (7961KB)(580)      
    The relevant policies, plans and specific projects of cave lunar bases at home and abroad were investigated systematically, with a focus on the comparative analysis of the existing gaps in research achievements. Based on the image information of lunar exploration at home and abroad and the research results of cave lunar base concept, the feasibility concept of cave lunar construction has been sorted out. Based on the unique advantages of the cave (such as suitable temperature, low radiation, less lunar dust, etc.) and the objective conditions of the difficulty of building a lunar base, a qualitative analysis was conducted on various concepts of cavebased lunar bases. Each type of lunar base configuration shows unique advantages: the cavebased lunar base based on the transformation of craters makes full use of the natural terrain on the lunar surface, combines the natural structural characteristics and artificial transformation requirements, and has significant advantages insitu resource utilization. Whether it is an unmanned or manned cave lunar base, it will go through four key strategic stages: lunar exploration, lunar address selection, lunar base construction and lunar base application. Although a large number of lunar images have been obtained through the launched lunar orbit probe, lunar surface probe and other exploration means, the current lunar surface exploration capabilities still need to be further improved to provide stronger support for the "site selection" work of the construction of the cave lunar base. At the same time, it is urgent to accelerate the development of key equipment for the construction of lunar bases as soon as possible, provide implementation tools for the construction of unmanned lunar bases, implement the "foundation" task of the cave lunar base, and realize the strategic goal of "cave utilization" of the cave lunar base as soon as possible.

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    Rigid-flexible coupling design and driving force analysis of modular deployable antenna structure
    TIAN Dake, ZHANG Hao, WANG Yongbin, FANG Jishou, JIN Lu, SHI Zuwei, FAN Xiaodong
    Chinese Space Science and Technology    2025, 45 (4): 144-153.   DOI: 10.16708/j.cnki.1000-758X.2025.0066
    Abstract442)      PDF(pc) (10574KB)(527)      
    Modular deployable antenna has the characteristics of good versatility, strong adaptability and expansion flexibility, and is a configuration form with great development potential to meet the needs of in-orbit assembly and construction of large-scale antenna in the future. In order to better grasp the mechanical characteristics of the antenna structure, the rigid-flexible coupling design and driving force analysis of the antenna structure are developed. Firstly, a scheme design of modular deployable antenna structure is carried out, and the structure composition and deployment/stowed principles are described. Secondly, based on the analytical geometric method, a mathematical model of the equivalent envelope circles is developed, and key parameters such as the angle of the rib unit are obtained, then the three-dimensional model of deployable antenna structure is established. Thirdly, the flexible processing of radial long beams such as upper beam, diagonal beam and lower beam is carried out, and a multi-body dynamic model of rigid-flexible coupling of modular deployable antenna mechanism is established by multi-body dynamics simulation software. Finally, the change laws of the deployable driving force of single module and multi module antennas at different confinement positions are analyzed from the aspects of gravity and no gravity. The results show that if there is gravity in the deploying process, the choice of constraint position has a great influence on the driving force. In the absence of gravity, the antenna constraint position has little effect on deployment. The structural design and multi scheme driving force analysis can provide some reference for the prototype development and engineering application of this antenna.
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    Thermal analysis and verification of flexible solar panels on orbital spacecraft
    HUANG Hongchang, LI Junlan, WANG Cheng, SHEN Xunan, ZHANG Xiaojun, ZHANG Dawei
    Chinese Space Science and Technology    2025, 45 (2): 79-87.   DOI: 10.16708/j.cnki.1000-758X.2025.0025
    Abstract406)      PDF(pc) (5756KB)(526)      
    To predict the working temperature and distribution of flexible solar panels on spacecraft in orbit, an analysis of the thermal environment experienced by the solar wings in outer space was conducted. The variation of heat flow on the front and back of the flexible substrate with the orbital period was calculated. Two typical power generation conditions of the solar cell array-optimal operating point and open circuit state, were considered, and the working temperature of the solar cells and flexible substrate was calculated using the finite element method to study the periodic temperature variations with the orbit. A comparison was made with telemetry data from the space station to validate the accuracy of the model and calculation method. The influence of the thermal-physical performance of various functional areas on the temperature distribution of flexible solar panels was studied by comparing the results under two conditions. The findings indicate that the disparity in absorptivity between the solar cells and substrate could lead to notable temperature gradients at the bonding edges of the flexible substrate, which is a crucial factor that could induce thermal deformation in the flexible substrate.
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    Distributed autonomous scheduling based on event trigger for heterogeneous satellite swarm
    QIN Jiahao, LI Baowei, BAI Xue, RAN Dechao, XU Ming, ZHANG Rui, HU Zhiqiang
    Chinese Space Science and Technology    2025, 45 (4): 88-101.   DOI: 10.16708/j.cnki.1000-758X.2025.0061
    Abstract336)      PDF(pc) (6453KB)(509)      
    The application of earth observation satellite (EOS) is shifting from static to dynamic mission scenario, leading to an increasing demand for real-time observing capabilities. Consequently, an autonomous scheduling method is urgently needed to enable real-time mission responses and overcome the window constraints imposed by satellite telemetry command control (TT&C) systems. An event-triggered distributed autonomous scheduling method is proposed, which enables the autonomous closed-loop of target discovery, evaluation, and imaging. Firstly, an event-triggered distributed multi-satellite task negotiation framework is established utilizing the double layer contract network protocol (DLCNP). Secondly, a dynamic scheduling algorithm considering task priority based on the minimum conflict set is proposed to achieve real-time task assertion and conflict resolving. This algorithm provides an online solution for multi-satellite task negotiation. Finally, an iterative density cluster method is introduced to conduct clustering of high-value point targets. This method ensures the clustered point targets can be covered by a single imaging satellite, which effectively reduced observations required. The superiority of the event-triggered distributed autonomous scheduling method is verified by comparing its task completion rate with global optimization algorithm and communication load with blackboard inter-satellite structure. The pattern of task merging ratio is revealed by varying the size of the spread area and the number of targets. The proposed method can enhance the autonomy and emergency response capability of EOS swarm effectively.
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    Application of wavelet analysis in GPS satellite fault detection
    HE Li-Wen, LI Xin-Guo
    Chinese Space Science and Technology    2017, 37 (6): 56-.   DOI: 10.16708/j.cnki.1000-758X.2017.0084
    Abstract988)      PDF(pc) (1373KB)(1676)      
    At present, the residual chisquare detection method based on extended Kalman filter has been widely used in GPS satellite fault detection independently by the receiver. However, this method has some problems such as dependency on mathematical model and detection delay. A GPS satellite fault detection method based on wavelet analysis was proposed. The wavelet analysis was used to analyze the GPS data in the time and frequency domain, and the data could be processed as multiscale analysis. Abnormal points were used to determine the occurrence of failure. The simulation results show that the proposed method is efficient, sensitive, concise and easy to implement. It′s useful to the reliability and stability of navigation system.
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    Design and on-orbit efficiency analysis of onboard GNSS system for LT4A satellite
    WANG Zhenxing, WANG Yubin, MAO Zhiyi, TIAN Xiaobin, LIU Zhijia, HUANG Yong, SHAO Mingxue
    Chinese Space Science and Technology    2025, 45 (1): 12-23.   DOI: 10.16708/j.cnki.1000-758X.2025.0002
    Abstract717)      PDF(pc) (8610KB)(434)      

    The analysis of the onboard high-orbit GNSS navigation receiver system applied on the LuTan-04A (LT4A), the world′s first Inclined Geosynchronous Orbit (IGSO) Synthetic Aperture Radar (SAR) satellite, is presented. The study investigates the precise orbit determination (POD) performance of the high-orbit GNSS receiver system and reports its engineering application for post-precise orbit determination for the first time. By collecting on-orbit data of BDS and GPS signal anomalies, the quality of onboard observational data and the POD are analyzed and evaluated. Experimental results indicate that the LT4A satellite onboard high-orbit GNSS navigation receiver system can stably capture and track BDS B1I and GPS L1 navigation signals, meeting the requirements for high-orbit real-time positioning, orbit determination, and post-mission precise orbit determination. Utilizing joint orbit determination of onboard BDS+GPS, the in-track accuracy can achieve radial better than 1.87m and three-dimensional better than 3.07m. In response to the characteristics of high-orbit navigation satellite acquisition and the timeliness requirements of applications, the orbit determination system can operate fully automatically throughout the entire process, ensuring the smoothness and continuity of the orbit, and controlling the introduction of high-order Legendre errors. The relevant achievements of this study can be applied to future high-orbit Earth observation satellite missions equipped with GNSS receivers.

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    Cutting-edge scientific issues in ice giant exploration
    WANG Chi, LI Hui, KONG Dali, WANG Yuxian, YANG Zhongwei
    Chinese Space Science and Technology    2025, 45 (4): 1-11.   DOI: 10.16708/j.cnki.1000-758X.2025.0053
    Abstract453)      PDF(pc) (9196KB)(407)      
    Exploring ice giants and their moons stands as one of the frontiers in deep space exploration and space science research. Current international planetary exploration plans all include missions to ice giants. Focusing on China’s future ice giant exploration missions, the current status of ice giant exploration is investigated, and seven key scientific questions are identified and summarized. By comparing and analyzing the characteristics of ice giant systems, and combining with the development trends in planetary exploration, the prospects and recommendations for future ice giant missions are proposed. Neptune-Triton exploration as a priority for ice giant missions is highlighted. Future exploration can be broadly divided into three subjects: exploring extraterrestrial oceans and life, understanding Kuiper belt objects and solar system evolution, and investigating ice giant systems to understand planetary origins and evolution. Analyzing the scientific objectives for ice giant exploration provides a scientific reference for China’s future deep space missions.
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    Improvement and application of MCTS in turn-based orbital games
    ZHENG Xinyu, ZHANG Yi, ZHOU Jie, TANG Peijia, PENG Shengren, DANG Zhaohui
    Chinese Space Science and Technology    2024, 44 (5): 75-82.   DOI: 10.16708/j.cnki.1000-758X.2024.0075
    Abstract264)      PDF(pc) (3370KB)(523)      
     The sensing delay of orbit change in turn-based orbit pursuitevasion game brings difficulties to differential game approaches,and deep reinforcement learning-based algorithms are still risky for engineering applications due to the inexplicability.The predictive-value-accumulate Monte Carlo tree search(PVA-MCTS) algorithm is proposed for the turn-based orbit pursuit-evasion game.Based on the predictability of spacecraft orbital motion,the algorithm predicts and accumulates the decision value in the game.This solves the problem of sparse reward and large time span in the turn-based orbit pursuit-evasion game,and improves the learning efficiency.It is used to solve the turn-based orbit pursuit-evasion game,and compared with the results obtained by Monte Carlo tree search(MCTS) algorithm.The results show that the PVA-MCTS algorithm reduces the pursuit time by about 27.6% and increases the escape time by about 6.8% for pursuer and evader respectively.The PVA-MCTS algorithm is realistic for the application of orbital game in the fields of non-cooperative target approaching and collision avoidance.
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    Review and prospect of intelligent perception for non-cooperative targets
    MU Jinzhen, HAO Xiaolong, ZHU Wenshan, LI Shuang
    Chinese Space Science and Technology    2021, 41 (6): 1-16.   DOI: 10.16708/j.cnki.1000-758X.2021.0076
    Abstract1146)      PDF(pc) (1102KB)(2442)      
    Intelligent perception is the key technology to realizing the fine control process of spacecraft on-orbit, which is one of the major development directions of on-orbit intelligence service. The key technologies of space target intelligent perception include pose measurement, three-dimensional reconstruction and component recognition, which involve the issues such as few-shot, multi-modality, model adaptation and high-dimensional data. From the perspective of engineering application, the latest research progress in the non-cooperative intelligent perception technique was systematically summarized. Firstly, the research status of the representative non-cooperative on-orbit perception systems and optical sensors were reviewed. Secondly, the key technologies involved in the intelligence perception of non-cooperative targets were analyzed. Finally, according to the analysis of the research status and critical techniques, the main issues of non-cooperative target intelligent perception were discussed, and the recommendations for the further development were presented.
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    Key technologies and approaches of intelligent control system for flexible wing structure aircraft
    JIA He, LIU Jinglei, MA Keyao, YAN Yunlong, PEI Xiaoyan, LIU Haiye, WANG Yongbin
    Chinese Space Science and Technology    2024, 44 (4): 59-70.   DOI: 10.16708/j.cnki.1000-758X.2024.0058
    Abstract317)      PDF(pc) (2366KB)(618)      
    With the advantages of lightweight,space integration,re-usability,large drag area and lift coefficient,the flexible wing structure aircraft can achieve functions such as cruise flight,low-speed hovering,re-entry and return,aerodynamic deceleration,fixed point homing and landing buffering,which is currently a research hot spot.Intelligent control system is one of the core technologies of the flight and recovery system of flexible wing structure aircraft.Combined with the application research and engineering practice of intelligent technology in the control system,the intelligent control system and its technical characteristics of the flexible wing structure aircraft are analyzed.The key technologies such as integrated control and simulation of rigid-flexible combination,environmental perception and online health status assessment,trajectory planning and tracking control,cluster flight control,intelligent control of landing and buffering,fault tolerance and reconstruction of intelligent hardware are introduced.The future development of the intelligent control system of flexible wing structure aircraft is considered.Some development suggestions are put forward,such as intelligent and flexible perception of flight environment,online identification of aerodynamic parameters,autonomous execution of multi-task mode and evolutionary learning of the control system.Through continuous research and practice of intelligent control technology,strong support is provided for the development of flexible wing structure aircraft system.
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    Analysisofdesign,simulation&calculationmoduleforMartianatmosphereenvironmentsimulationdevice
    LIU Gao-Tong, SUN Yu, ZHANG Lei
    Chinese Space Science and Technology    2016, 36 (5): 65-.   DOI: 10.16708/j.cnki.1000-758X.2016.0059
    Abstract1378)      PDF(pc) (6530KB)(2358)      
    ThecharacteristicsofMartianatmospherewerestudied. AsimulationcalculationmoduleoftheMartianatmospheresimulationenvironmentboxwassetupbychoosingappropriatecalculationmethodcombinedwithFLUENTfluidfiniteelementcalculationsoftware. ThemodulerealizessteadyandunsteadycalculationsimulationofinteriorflowfieldundermultipleworkingconditionsofthecylindricalMartianatmosphereenvironmentsimulationdevices.ThecalculationresultswasanalyzedsoastoprovidetechnicalsupportandreferencefordesignoftheMartianatmosphereenvironmentsimulationdevice.
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    Architecture and development envision of cislunar space infrastructure
    YANG Mengfei, PENG Jing, LI Jionghui, NI Yanshuo, ZHU Shunjie, DU Ying, XU Baobi, HUANG Xiaofeng, ZHANG Zhengfeng
    Chinese Space Science and Technology    2024, 44 (3): 1-14.   DOI: 10.16708/j.cnki.1000-758X.2024.0034
    Abstract2001)      PDF(pc) (7344KB)(2194)      

    The construction of cislunar space infrastructureCLSIcan provide basic and universal services for human activities in the cislunar spaceincluding data communicationsposition navigation and timingPNT),and situation monitoring for the development of lunar spacewhich can meet the needs of follow-up major national lunar exploration projects.At the same timeit has strategic significance for accelerating the development of the space industry into the cislunar spaceand promoting Chinas strength in sciencetechnology and aerospace.On the basis of clarifying the concept of CLSI and analyzing the state-of-art development statusthe top-level system architecture is proposed for the CLSIaddressing to the needs of major projects and the sustainable development of the aerospace industry.Thenthe system servicesthe system compositionthe cloud-domain-endnetwork architecture as well as the internal and user interfaces architecture are defined and demonstrated.Finallywith the goal of gradually establishing a technologically advanced and reasonably deployed CLSI by phases and providing universal services that are opensafereliableand operate continuously and stably in the long termdevelopment prospects and suggestions are proposed to provide reference for the development and construction planning of CLSI.

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    Review of blackout mitigation methods for vehicles during atmospheric reentry
    YU Minghao, QIU Zeyang
    Chinese Space Science and Technology    2022, 42 (2): 1-12.   DOI: 10.16708/j.cnki.1000-758X.2022.0016
    Abstract581)      PDF(pc) (2375KB)(1750)      
    In order to help researchers better understand the mitigation methods of blackout and its development status, blackout mitigation methods adopted in current aerospace fields were introduced systematically and comprehensively. Firstly, the formation causes and research status of blackout problem were briefly introduced, and then the propagation mechanism of electromagnetic wave in plasma was also expounded. Secondly, the basic principles, advantages and disadvantages of 14 technical methods used to mitigate the blackout were introduced and discussed in detail. Those methods include variation of aerodynamic design of aircrafts, addition of the crossed electric and magnetic fields, standing wave detection, increment of the incident frequency, and terahertz technology, etc. Next, the abovementioned 14 methods were classified and evaluated from six aspects, e.g., power consumption, size quality, communication effect and engineering practicability, etc. Finally, several suggestions are put forward for the future study of the blackout problem.
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    Review of space target positioning algorithms based on space-based optical detection
    LI Yao, CHEN Xin, RAO Peng
    Chinese Space Science and Technology    2024, 44 (2): 1-15.   DOI: 10.16708/j.cnki.1000-758X.2024.0017
    Abstract659)      PDF(pc) (6075KB)(1481)      
    In recent years,the field of space target localization has developed rapidly by integrating detection technologies such as sensor-network collaboration and multi-mode fusion.Positioning methods based on space-based optical detection are widely used in civil and national defense fields with their unique advantages of good concealment and high measurement accuracy.In order to analyze the localization methods suitable for different types of spatial targets in different scenarios,small space target positioning methods based on space-based optical detection were reviewed.Firstly,the development of space-based optical detection technology,the classification and characteristics of space targets,and the concept of space target localization were introduced.Secondly,the positioning methods based on single satellite or multi-satellites suitable for small and weak spatial targets were analyzed.The joint positioning of heterogeneous sensors proposed in recent years was explained.Besides,the error analysis model of spatial target positioning was established according to the imaging process.The proportion of factors influencing positioning accuracy was analyzed.Finally,the summary and outlook were made based on the existing problems.
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    Mission analysis and design of Queqiao-2 communication relay payload
    XU Jin, WANG Qiuping, LI Yao, SUN Ji, CHEN Lan, YU Xiaochuan, WANG Hai, TIAN Sen, DANG Xiaokang, WANG Yongta
    Chinese Space Science and Technology    2025, 45 (3): 41-55.   DOI: 10.16708/j.cnki.1000-758X.2025.0037
    Abstract361)      PDF(pc) (12008KB)(349)      

    The Queqiao-2 relay satellite supports the fourth phase of China’s lunar exploration mission to land probes on the Moon. Its primary function is to facilitate communication between lunar surface exploration missions (Chang'e-6, Chang'e-7 and Chang'e-8, etc.) and ground stations, particularly for missions to the Moon’s far side and polar regions. The relay communication payload is one of the most critical and core components of Queqiao-2 relay satellite. The mission features, design and key technologies of Queqiao-2 communication relay payload are analyzed and introduced. A full digital modulation and demodulation function is developed for the forward and return links, considering factors like communication techniques, long-distance transmission, compatibility with multiple lunar probes, and engineering feasibility. This, combined with the ability to update software in orbit, makes the communication relay payload highly flexible and innovative. A key challenge is detecting and tracking multiple targets from high-dynamic signals of the return link. This is addressed by creating a dedicated algorithm to ensure stable communication. Since its launch in March 2024, the communication payload has been operating well in orbit with high reliability, which establishes a leading role in system technical performance around the world. It has provided stable and reliable relay communication for the Chang’e-6 lunar probe for sampling and return mission, successfully completing the world’s first lunar sample return mission from the far side of the Moon. The Queqiao-2 relay satellite's communication payload has played a significant role in China's deep space exploration, generating substantial economic and social benefits. It has laid a solid foundation for future deep space exploration, human spaceflight programs, lunar exploration projects and international cooperation.

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