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Orbit design method of near-lunar space constellation CHEN Shiyu, NI Yanshuo, PENG Jing Chinese Space Science and Technology    2024, 44 (3): 15-29.   DOI: 10.16708/j.cnki.1000-758X.2024.0035 Abstract （2345）      PDF（pc） （9757KB）（2711）       Knowledge map     According to the requirements of relay communication and lunar navigation for future lunar exploration missions，an orbit design method of near-moon space constellation is proposed.First，the indexes of constellation design in relay communication，lunar navigation，cost for deployment and maintenance are sorted out，and analytic hierarchy process is applied to determine the weights of the indexes so that a comprehensive evaluation index can be proposed.The properties of various types of orbits are analyzed with full consideration of orbit resources near the moon，and the orbit types suitable for constellation deployment are initially screened.A construction route of the near-moon space constellation is proposed，where 100% quadruple cover for the whole moon is gradually realized in three stages.The constellation configurations in the three stages are designed successively.For each stage，different configurations are compared and the one with the best comprehensive evaluation index is selected.Based on the above method，the construction scheme of the constellation in near-moon space is obtained.In the first stage，2 satellites are deployed in elliptical lunar frozen orbit（ELFO）to provide full-time earth relay communication for the south pole region of the moon.In the second stage，6 ELFO satellites，2 near rectilinear halo orbit（NRHO）satellites，and 1 L2 halo orbit satellite are deployed to provide full-time navigation for the south pole region and fulltime earth communication for the entire lunar surface.In the third stage，4 ELFO satellites，2 NRHO satellites，1 L1 halo orbit satellite，and 3 distant retrograde orbit satellites are deployed to provide full-time navigation for the entire lunar surface.For any position in the whole lunar surface，the geometric dilution of precision of the designed constellation keeps below 5 in at least 72% of the time，leading to a long-term high-precision navigation for the whole lunar surface.Compared with the existing literature，the proposed design method of the near-lunar space constellation considers more orbit types，more comprehensive constellation performance indexes，and innovatively puts forward a phased construction scheme of the near-lunar space constellation. Related Articles | Metrics

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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 Abstract （2043）      PDF（pc） （7344KB）（2212）       Knowledge map    The construction of cislunar space infrastructure（CLSI）can provide basic and universal services for human activities in the cislunar space，including data communications，position navigation and timing（PNT），and situation monitoring for the development of lunar space，which can meet the needs of follow-up major national lunar exploration projects.At the same time，it has strategic significance for accelerating the development of the space industry into the cislunar space，and promoting China′s strength in science，technology and aerospace.On the basis of clarifying the concept of CLSI and analyzing the state-of-art development status，the top-level system architecture is proposed for the CLSI，addressing to the needs of major projects and the sustainable development of the aerospace industry.Then，the system services，the system composition，the “cloud-domain-end” network architecture as well as the internal and user interfaces architecture are defined and demonstrated.Finally，with the goal of gradually establishing a technologically advanced and reasonably deployed CLSI by phases and providing universal services that are open，safe，reliable，and operate continuously and stably in the long term，development prospects and suggestions are proposed to provide reference for the development and construction planning of CLSI. Reference | Related Articles | Metrics

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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 Abstract （516）      PDF（pc） （2018KB）（1589）       Knowledge map    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. Related Articles | Metrics

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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 Abstract （673）      PDF（pc） （6075KB）（1511）       Knowledge map    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. Related Articles | Metrics

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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 Abstract （1171）      PDF（pc） （8217KB）（1159）       Knowledge map    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. Related Articles | Metrics

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Construction and transfer of space-based spatial-temporal reference in earth-moon space ZHOU Huichao, ZHENG Jinjun, WANG Haihong, BI Shaojun Chinese Space Science and Technology    2024, 44 (3): 51-59.   DOI: 10.16708/j.cnki.1000-758X.2024.0038 Abstract （663）      PDF（pc） （6434KB）（893）       Knowledge map     Cislunar space is gradually becoming a focal area for human space exploration activities.Constructing a high-precision spatial-temporal reference and service is significant for planning and executing cislunar space missions.It is not only a systematic expansion of the spatial-temporal reference in the near-earth region，but also an important approach to enhance the guarantee capability of spatial-temporal information in cislunar space.With the development of GNSS，the infrastructure of spatial-temporal reference in the nearearth region is relatively comprehensive.The navigation system in the lunar region is similar to that of the near-earth region，and various solutions have been proposed.However，cislunar space also includes areas beyond the earth and the moon.Factors such as large airspace and particularity of dynamics should be adequately considered when the spatial-temporal reference is constructed，which can provide spatial-temporal information service with high benefits and connect the spatial-temporal reference of the earth and the moon organically.In this article，the spatial-temporal reference framework in cislunar space was designed based on the current demand of development.With characteristics of cislunar space beyond the earth and the moon considered，the scheme for constructing，tracing and transferring of the space-based earth-moon libration point spatial-temporal reference was researched and proposed.This scheme is anticipated to deliver a spatial-temporal information service with high accuracy and benefits，offering valuable reference for integrative construction and development of spatial-temporal reference in cislunar space. Related Articles | Metrics

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System design and validation of Queqiao-2 lunar relay communication satellite ZHANG Lihua, XIONG Liang, SUN Ji, CHEN Luojing, XIAO Chuan, ZHOU Wenyan, WANG Yong, LIU Wangwang, GUAN Yifeng, CHEN Tao, YU Xiaochuan, XU Jin, CHEN Guohui, CAO Xiaoping Chinese Space Science and Technology    2024, 44 (5): 23-39.   DOI: 10.16708/j.cnki.1000-758X.2024.0071 Abstract （877）      PDF（pc） （8335KB）（865）       Knowledge map    In order to provide relay communication supports for future Chinese lunar exploration program，Queqiao-2 relay communication satellite was developed.Queqiao-2 can perform scientific observations with three kinds of scientific instruments on board.The system design of Queqiao-2，including mission orbit and transfer orbit design，configuration and layout design，housekeeping and information flow design，power supply and distribution design，GNC and propulsion system design，communication links design，etc.，was accomplished through comprehensive tradeoff and evaluation on technical maturity，availability，schedule，cost，and so on.With a view to reducing development risk，both the platform and relay communication payloads were developed based on significant heritage from previous Queqiao relay satellite and other relevant spacecraft.Queqiao-2 features flexible system architecture to support multiple frequencies，modulations，data rates and software reconfigurations to meet new user requirements.Subsequent to a successful launch on March 20，2024，by means of 5 orbit maneuvers，Queqiao-2 was inserted into a highly elliptical frozen mission orbit around the moon with a 24h period on schedule.Following on-orbit tests and calibrations，Queqiao-2 has possessed the capacity to provide reliable relay communication services to multiple lunar exploration missions，as well as the capacity to perform scientific observations.Under the support of Queqiao-2，Chang′e-6 achieved its ambitious mission goal to collect  and return samples from the moon′s mysterious far side.In the meanwhile，Queqiao-2 has also paved the way for the following Chinese lunar exploration missions including Chang′e-7 and Chang′e-8.The design life time of Queqiao-2 is more than 8 years.Benefit from flexibility and extensibility of relay communication system design，it is convenient to provide relay communication services for future lunar exploration missions of both China and other countries.In addition，innovative scientific observations would be performed during the period that no relay communication task is arranged.The system design of Queqiao-2 reflects the development philosophy of technical innovations and inheritance integration.Based on highly flexible and extensible system architecture，multiple and concurrent relay communication mission requirements can be met.It can provide strong supports for future lunar exploration missions.Successful launching，orbit entering and on-orbit tests of Queqiao-2 verified the correct design principle and versatility.By means of Queqiao-2，more innovative scientific outcomes are anticipated and lunar exploration activities can be facilitated. Related Articles | Metrics

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System architectures and key technologies of lunar surface communication and navigation infrastructure LI Jionghui, WANG Zijie, BAI Fan, GU Zheng, XIN Pengfei, JIA Min, ZHAO Hongbo, PENG Jing Chinese Space Science and Technology    2024, 44 (3): 30-42.   DOI: 10.16708/j.cnki.1000-758X.2024.0036 Abstract （672）      PDF（pc） （6199KB）（788）       Knowledge map    As a significant component of the cislunar space infrastructure（CSI），lunar surface communication and navigation infrastructure（LSCNI） provides more convenient communication networking services for the surface local users within hotspot areas，and also provides reference of surface local positioning and navigation as well as certain positioning，navigation and timing（PNT） capacities.On the basis of trend analysis，overall architectures of lunar surface communication and navigation infrastructure are proposed focusing on the medium and long-term strategic development of current major projects as well as future large-scale lunar activities.The architectures contain the network architecture and the lunar surface-space interfaces.Then，the solutions to some core issues such as lunar frequency planning，radio wave channel modeling，network access，high-speed transmissions，positioning and navigation methods are analyzed.Finally，suggestions for phased construction and technological development roadmap are proposed，providing reference for the planning and construction of communication and navigation systems for future lunar exploration missions. Related Articles | Metrics

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International rules and utilization status of frequency and orbit resources for cislunar space exploration SUN Qian, LIU Huiliang, WANG Jilian Chinese Space Science and Technology    2024, 44 (3): 80-88.   DOI: 10.16708/j.cnki.1000-758X.2024.0041 Abstract （402）      PDF（pc） （3908KB）（741）       Knowledge map     Cislunar resources，such as radio spectrum，have attracted close attention among global major participants in space.However，the international rules in force centered on the earth cannot meet the upcoming practical requirements of cislunar resource utilization.The ambiguity of international rules intensifies resources competition and increases the risk of frequency interference between different spacecraft.Amending the international rules on space resources is in an important period of strategic opportunities.Aiming at the gap between international policies and exploration requirements of cislunar space，the existing international rules for frequency and orbit resources were comprehensively investigated.Regulations and mechanisms of international organizations such as the International Telecommunication Union（ITU）and Space Frequency Coordination Group（SFCG），both inter-governmental and nongovernmental，were sorted out.Taking Artemis as an example，a typical lunar exploration program was studied.In addition，the global status and trend of cislunar resources acquisition and utilization were analyzed in detail.Finally，considering the implementation objectives of international lunar research stations and manned lunar landing programs，suggestions for compliant submission following the rules in force were carried out.And proposals for international cooperation on resource utilization，matching the construction procedure，were put forward. Related Articles | Metrics

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Equilibrium of orbital pursuit-evasion-defense three-sided game LI Zhenyu, LIN Kunpeng, HOU Yuzhuo, LUO Yazhong Chinese Space Science and Technology    2024, 44 (4): 90-101.   DOI: 10.16708/j.cnki.1000-758X.2024.0060 Abstract （487）      PDF（pc） （7093KB）（718）       Knowledge map    To improve the defense ability of the spacecraft in orbit，an orbital pursuit-evasion-defense（PED）linear-quadratic game is investigated.Three players are called the pursuer，evader，and defender，respectively.The pursuer aims to intercept the evader，while the evader tries to escape from the pursuer，accompanied by a defender who attempts to protect the evader by intercepting the pursuer actively.Due to the existence of the defender，the pursuer has to evade the defender when chasing the evader.Meanwhile，cooperation between the evader and the defender may decrease the difficulty of escape.For such a three-sided game，a linear-quadratic differential game model is established with a performance index combining three players′ energy consumption and the distance.Then the necessary conditions for the Nash equilibrium of the three players are derived and the optimal pursuit guidance law and evasion-defense guidance law are obtained.Furthermore，the equilibrium solution is extended to a more general PED scenario with multiple defenders.Simulation results show that a defender can improve the survivability of the evader.Even with inferiority in maneuverability，they can win the pursuer cooperatively.Besides，an initial position close to the pursuer or evader is not the best choice for the defender who flies around the evader.The defender has favorable positions. Related Articles | Metrics

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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 Abstract （633）      PDF（pc） （9223KB）（716）       Knowledge map    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. Related Articles | Metrics

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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 Abstract （334）      PDF（pc） （7542KB）（716）       Knowledge map    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. Related Articles | Metrics

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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 Abstract （330）      PDF（pc） （2366KB）（710）       Knowledge map    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. Related Articles | Metrics

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Analysis and key design of lunar far-side robotic sampling and return misson SHENG Ruiqing, MENG Zhanfeng, ZHAO Yang, TAN Zhiyun, ZHANG Hong, HUANG Hao, ZHANG Wu Chinese Space Science and Technology    2024, 44 (5): 1-14.   DOI: 10.16708/j.cnki.1000-758X.2024.0069 Abstract （863）      PDF（pc） （17095KB）（665）       Knowledge map    The Chang′e-6 lunar probe is designed to achieve the first robotic sampling and return mission from the far side of the Moon.The lunar far side has rugged terrain overall and lacks flat areas suitable for sampling.Two areas in Apollo basin within south pole Atiken basin （SPA）are selected as primary and backup targeted landing sites，the safety and reliability of landing，lift-off and surface operation process are ensured.In order to achieve new mission objectives within the establis hed technical configuration，an optimal system design solution is put forward to reduce system changes.The risks associated with alterations of technical status are avoided.Through comparative analysis，a retrograde orbit around the Moon is selected，ensuring minimal system modifications and optimal system design.In consideration of the reduced and discontinuous duration of relay telemetry and control on the far side of the Moon for Chang′e-6，a phased，highly autonomous，and cooperative relay-assisted lunar surface operation timeline design is proposed to ensure the implementation during landing，lift-off and surface operation process.For payload carried by Chang′e-6，a system design is proposed by using data processing units as the central exchange hub to ensure electrical interface safety isolation；customized detection modes are also developed for different payloads to maximize detection benefits without affecting the completion of the main mission.These methods are applied in the Chang′e-6 mission，ensuring the success of the world′s first robotic sampling and return mission from the far side of the Moon，valuable reference and experience are provided for follow-up lunar exploration and deep space exploration missions. Related Articles | Metrics

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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 Abstract （494）      PDF（pc） （5812KB）（643）       Knowledge map    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. Related Articles | Metrics

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Multi-impulse pursuit-evasion game in GEO based on improved dung beetle optimization GUO Yanning, LI Gaojian, YU Yongbin Chinese Space Science and Technology    2024, 44 (4): 1-10.   DOI: 10.16708/j.cnki.1000-758X.2024.0052 Abstract （725）      PDF（pc） （4364KB）（629）       Knowledge map    This paper investigates the pursuit-evasion game of GEO with J2 perturbation and impulsive thrust considering perception delay.An optimization model of orbital pursuit strategy is established，considering fuel consumption，single impulse velocity increment，impulse interval time，mission duration，impulse quantity，and terminal distance.The design variables include the number of impulses，the sequence of maneuver moments，and the sequence of impulse increments.The pursuing spacecraft pursues the target spacecraft through multiple impulses.To enhance problem-solving efficiency，an improved Bernoulli dung beetle optimization algorithm（IBDBO）utilizing Bernoulli chaotic mapping and optimal value guidance is proposed.Additionally，Lambert maneuver correction is introduced to address terminal constraint satisfaction issues.The comparison experiments with other intelligent algorithms verify the superiority of this algorithm in terms of convergence speed，convergence stability and optimization efficiency.Furthermore，simulations in real scenarios with perceptual delay demonstrate the effectiveness of this algorithm for planning pursuit strategies.Finally，the causal relation between terminal distance of both sides in the game and the target spacecraft′s maneuvering capabilities，perception delay time is explored. Related Articles | Metrics

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Design and analysis of radiating rib space deployable antenna mechanism TIAN Dake, SONG Yuqun, JIN Lu, GAO Haiming, LIU Rongqiang, ZHAO Bingfeng Chinese Space Science and Technology    2024, 44 (2): 40-50.   DOI: 10.16708/j.cnki.1000-758X.2024.0020 Abstract （384）      PDF（pc） （9457KB）（624）       Knowledge map    The deployable antenna mechanism is a key component of the mesh deployable antenna，which has a significant influence on the stability and stiffness of the structure after deployment.A new configuration of radiating rib space deployable antenna mechanism was designed to address the development trend of large scale，high storage rate，and high accuracy of space deployable antennas.Firstly，the overall structural design of the antenna was designed，and a three-dimensional model of the structure was established based on the dimensional calculation of the structural composition.Then，the kinematic simulation study of the mechanism was carried out by using numerical simulation software，and the variation law of the motion was analyzed.Finally，a finite element model was established，and the structural modal analysis was carried out.The results show that the proposed mechanism can realize the motion change from folded state to deployed state，and that the mechanism has good synchronization during the deployment process without interference between the components，which verifies the correctness and feasibility of the structural scheme and principle.The research results can provide a reference for research on the basic theory of a deployable antenna mechanism and related engineering applications. Related Articles | Metrics

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Cislunar cloud network：the cross-domain integrated cislunar-spatial network QIAO Liang, LI Chenghao, WANG Shanpeng, LI Jionghui, LIU Lei, XU Yong, YAN Hongcheng, SUN Zhelei Chinese Space Science and Technology    2024, 44 (3): 43-50.   DOI: 10.16708/j.cnki.1000-758X.2024.0037 Abstract （529）      PDF（pc） （5073KB）（597）       Knowledge map    To enhance the service efficiency of cislunar-spatial infrastructure for diverse users and to establish a cross-domain，integrated cislunar-spatial network，the concept of cislunar cloud network is introduced.Interconnecting various constellations and facilities through wireless links，the cislunar cloud network employed the integrated network protocols to facilitate cislunar-spatial networking.The operational deployment of the cislunar-spatial network promised a transformative change for traditional deep-space exploration missions，enabling continuous telemetry，efficient data transmission，and collaborative inter-probe tasks.However，the cislunar cloud network，characterized by high dynamics，significant latency，and strong heterogeneity，poses challenges to cislunar-spatial networking.The development and features of cislunarspatial networks are analyzed，a cislunar cloud network protocol stack is constructed adaptable to cislunar-spatial characteristics and meeting the interconnection needs of future deepspace exploration network nodes.The protocol stack is characterized by integration，universality，layering，intelligence，and internationalization.The design of its data plane and control plane is elaborated on.Additionally，a forward-looking perspective is provided on the future development of the cislunar cloud network protocols. Related Articles | Metrics

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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 Abstract （723）      PDF（pc） （7961KB）（588）       Knowledge map    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. Related Articles | Metrics

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Dynamics of asteroid probe orbit calculation WANG Hong, YAN Jianguo, FAN Min, LI Haitao Chinese Space Science and Technology    2024, 44 (4): 111-118.   DOI: 10.16708/j.cnki.1000-758X.2024.0062 Abstract （373）      PDF（pc） （1959KB）（584）       Knowledge map    The problem of orbit calculation dynamics in the upcoming asteroid exploration missions of China is studied.The demand of asteroid probe orbit calculation is analyzed，and the space-time reference system involved in asteroid orbit calculation is described，then the dynamical models to be considered in orbit calculation are discussed.The calculation formulas of various types of perturbation acceleration are given.The largest force model is the gravitational acceleration of the Sun，with magnitude about 10-6km/s2，and the smallest is the asteroid body perturbation acceleration which is about 10-12-10-13km/s2.The difference between ephemeris of Rosetta provided by ESA and that integrated from the dynamical model in this paper shows that the four-day arc segment position error is about 15m，velocity error is about 0.44mm/s，so the accuracy of the dynamical model is reliable.The above study can provide a reference for the orbit calculation of China′s asteroid exploration missions. Related Articles | Metrics