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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 （2059）      PDF（pc） （9757KB）（2411）       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 （1608）      PDF（pc） （7344KB）（1823）       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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Progress and prospect of lunar resources exploitation and utilization YANG Mengfei, ZOU Zhigang, WANG Weihua, YAO Wei, WANG Qinggong Chinese Space Science and Technology    2024, 44 (1): 1-10.   DOI: 10.16708/j.cnki.1000-758X.2024.0001 Abstract （740）      PDF（pc） （4467KB）（1209）       Knowledge map    With the implementation of the Chang′E-5 mission in 2020，the three phases of China lunar exploration program，namely orbiting，landing and returning，have been completed.Next，the International Lunar Research Station（ILRS）will be established at the lunar south pole by 2030，and a lunar base will be planned later.It is a new era of exploitation and utilization of the Moon，in which a vast tasks should be completed.In this paper，we summarized some important progresses of investigation of lunar resources in the past，including lunar resource exploration，analysis of lunar volatiles，mineral extraction，and material construction by 3D printing of lunar regolith.Then，we proposed future tasks for the exploitation of the lunar resources.The main challenges of the Moon，such as the extreme lunar environment，unique properties of lunar regolith，and autonomous control of the process，were considered.The views in this paper can be referenced for future scientific researches and engineering tasks in the field. 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 （651）      PDF（pc） （17095KB）（508）       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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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 （643）      PDF（pc） （8335KB）（663）       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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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 （599）      PDF（pc） （4364KB）（508）       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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Current status and prospect of multisource remote sensing data in battlefield environment intelligent situational awareness SHAO Zhenfeng, DANG Chaoya, ZHANG Hongping, WU Changzhi, QI Xiaofei, HUANG Jun Chinese Space Science and Technology    2024, 44 (1): 11-22.   DOI: 10.16708/j.cnki.1000-758X.2024.0002 Abstract （578）      PDF（pc） （4641KB）（961）       Knowledge map     In the face of the rapid change of complex battlefield environment information，grasping the situational awareness of complex battlefield environment in a timely，comprehensive and accurate manner is the prerequisite for winning the information war in the future.In order to explore the development direction of multi-source remote sensing data in battlefield environment situational awareness，on the basis of extensive investigation of remote sensing requirements for battlefield environment situational awareness，we firstly expounded the concept and connotation of battlefield environment situational awareness，then gave an overview of multi-source remote sensing data processing and battlefield situational awareness applications.Next，we analyzed the challenges，progress and development trend of remote sensing in battlefield environment situational awareness.In general，remote sensing provides a variety of observation data for battlefield environment situational awareness，and the combination of remote sensing and artificial intelligence algorithm can provide a variety of applications for military battlefield environment situational awareness and offer data assistance to commanders for decision-making.However，there are still a lot of challenges to be solved.Based on the analysis of the current achievements and challenges，we put forward the prospect of remote sensing in the battlefield environment situational awareness，and pointed out that the interpretability of deep learning based on remote sensing and the intelligent battlefield are the difficulties to break through the development of remote sensing in the battlefield environment situational awareness. Related Articles | Metrics

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Matching design of trajectory with Chang′e-6 mission and flighting pratice of Queqiao-2 satellite ZHOU Wenyan, GAO Boyu, DONG Tianshan, LIU Decheng, SUN Ji, ZHANG Lihua Chinese Space Science and Technology    2024, 44 (6): 16-22.   DOI: 10.16708/j.cnki.1000-758X.2024.0087 Abstract （496）      PDF（pc） （2897KB）（238）       Knowledge map    Queqiao-2 provides relay services in its overall life cycle for Chang′e-6, Chang′e-7, Chang′e-8, and Chang′e-4 missions, as well as lunar exploration missions from international cooperation. To meet the different relay needs of multiple launch windows and different flight phases of Chang′e-6 mission, the trajectory design method and process of the Queqiao-2 relay satellite to service the Chang′e-6 mission are introduced from the perspective of mission analysis. The adoption of a lunar elliptical sun-synchronous frozen orbit satisfies the requirements for communication range, coverage, launch windows, and orbital phase for the Chang′e-6 mission. Then the trajectory scheme and the control strategy adopted on each flight phase are optimized with minimum fuel constraint. A four-impulse joint optimization trajectory control strategy is employed to significantly alter the orbital ascending node, inclination and argument of perilune with few velocity increments. Finally, the status of the in-orbit flight and relay support for Chang′e-6 mission are shown respectively. For the first time internationally, Queqiao-2 has achieved a significant change of right ascension of the ascending node in lunar orbit by using a lunar low energy capture orbit, and close range and long arc relay of target on the far side of the moon by using the lunar large elliptical sun-synchronous and frozen orbit. The result shows that the in-orbit flight of Queqiao-2 is consistent with that of the design, which ensures the successful implementation of the Chang′e-6 lunar far-side sampling and return mission. The design method can provide a reference for the orbit design of deep space exploration missions. 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 （484）      PDF（pc） （6199KB）（627）       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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Chang′e-6 mission planning leveraging geometry approach MENG Zhanfeng, GAO Shan, ZHAO Qiao, ZHANG Xiangyu Chinese Space Science and Technology    2024, 44 (6): 1-15.   DOI: 10.16708/j.cnki.1000-758X.2024.0086 Abstract （483）      PDF（pc） （15016KB）（396）       Knowledge map    The Chang′e-6 mission is the first lunar far-side sampling return mission in the world. The mission planning is an important assignment in the spacecraft system design. Mission planning problem is conventionally converted to the numerical constraints optimization problem in the traditional method. However, by using this method, the constraints could not be satisfied directly, and at the same time, the design variables dimension increased, the computing efficiency decreased, and the physical meaning was not apparent. A new mission planning approach using the mission geometry is proposed in this paper. According to the new approach, the periapsis constraints of the Earth-to-Moon and Moon-to-Earth transfer trajectories, the relative geometry constraints on sampling point and lunar orbit plane, and the geometry relationship of the Sun-Earth-Moon are fully considered. The new approach reduced the design variables dimension, improved the computing efficiency. In addition, it also has the advantage of intuitive spatial geometric interpretation, and the result can be verified easily. The new approach has been applied to mission planning and trajectory design in the Chang′e-5 and Chang′e-6 missions successfully, and will be adopted in the future lunar exploration mission. 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 （469）      PDF（pc） （6434KB）（685）       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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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 （461）      PDF（pc） （6075KB）（1122）       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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Research status and prospect of space thermophotovoltaic power generation technology QIU Jiawen, TIAN Dai, HAN Chengzhi, ZHANG Ran, SU Sheng, MA bin, TANG Liangliang, SHAO Jianxiong, ZHU Anwen Chinese Space Science and Technology    2024, 44 (5): 40-56.   DOI: 10.16708/j.cnki.1000-758X.2024.0072 Abstract （397）      PDF（pc） （4668KB）（304）       Knowledge map    Space radioisotope power is a space power device that converts nuclear decay thermal energy into electrical energy through thermoelectric conversion technology，and is widely used in deep space exploration missions.Space isotope power commonly uses plutonium 238 as nuclear sources.The preparation and production of plutonium 238 are difficult and expensive，resulting in worldwide limited production capacity.Meanwhile，long-term deep space exploration missions propose high requirements for the lifespan of isotopic power.Space thermal photovoltaic radioisotope power with high thermoelectric conversion efficiency and long lifespan has become the preferred technical route for deep space exploration missions.NASA has demonstrated a RTPV prototype with a conversion efficiency greater than 20%.In recent years，near-field thermal photovoltaic and spectral-regulation thermal photovoltaic technology have become the hotspot.Significant progress has also been made in the theoretical research and technical verification of critical devices such as emitters，optical filters，and photovoltaic cells.In this paper，the research progress of RTPV system designs and relevant key devices is reviewed.Based on the system level requirements，the development status of each device is stuaied and the future trend is suggested.This paper provides a reference for promoting the engineering development of thermophotovoltaic radioisotope power supply system in the future. Related Articles | Metrics

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A dual-loop fault tolerant attitude control for the Chang′e-6 lunar orbit flight ZHANG Honghua, GUAN Yifeng, LI Ji, YU Jie, CHEN Yao, WANG Zhiwen, ZHANG Xiaowen, ZHANG Luchen, LI Linfeng, SUN Guojian, WANG Zhenhua, GUO Minwen, LI Xiaofeng, GAO Xizhen Chinese Space Science and Technology    2024, 44 (5): 15-22.   DOI: 10.16708/j.cnki.1000-758X.2024.0070 Abstract （385）      PDF（pc） （4634KB）（308）       Knowledge map    During the lunar orbit flight phase of the Chang′e-6 lander and ascender module (LAM), the 10N thruster (could be used in a force-couple method) on the ascender and the 150N thruster on the lander are implemented for the attitude control. However, there exists some fault cases when one 10N thruster failed to fire and the other pair one could work well, the propulsion system could generate opposite control torque due to the installation of thrusters and the attitude could be instable accordingly. To ensure the attitude stability in the 10N thruster fault case, a dual-loop fault tolerant attitude control is proposed with a 10N thruster in the inner loop and a 150N thruster in the outer loop. Numerical simulations illustrate that the LAM attitude in the lunar orbit could still meet the requirements even in the case of the 10N thruster fault. Therefore, the proposed dual-loop attitude control, which implements coupled attitude control thrusters and redundant thrusters, could effectively manage the coupled thruster fault and ensure the stabitlity. 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 （380）      PDF（pc） （5073KB）（452）       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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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 （356）      PDF（pc） （2018KB）（734）       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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A review on recent development of space solar power HOU Xinbin , , MANKINS John, SHINOHARA Naoki , CHOI Joon-Min, SOLTAU Martin Chinese Space Science and Technology    2024, 44 (6): 33-51.   DOI: 10.16708/j.cnki.1000-758X.2024.0089 Abstract （344）      PDF（pc） （16542KB）（285）       Knowledge map    Space solar power (SSP) system, a major type of space-based power-generating equipment, is an important infrastructure providing massive, continuous, and stable green electricity by utilizing solar energy in space. Many countries and organizations consider SSP to be one of the most promising clean energy sources. The historical activities of SSP in the world are summarized. This review focuses on the significant development of SSP during the last 10 years, which is the most important period for SSP. The latest international SSP development programmes in the United States, ESA, Japan, China, UK and Korea are presented. Some significant solar power satellite(SPS) concepts proposed in the decade, including typical SPS-ALPHA, MR-SPS, CASSIOPeiA SPS, et al., are introduced. The technical and non-technical challenges are also listed and several important in-space demonstration missions in recent years and in the near future are introduced. The conclusion is that the next 5 to 10 years will be an important period for rapidly developing the key technologies and conducting on-orbit demonstration and application. Controlling the mutual position relationship between the solar array and the transmitting antenna becomes a core issue to be considered in the innovative design of the SPS. Wireless power transmission technologies would be the demonstration focus for the first step. It is expected that the first commercial SPS would be constructed as early as 2040. Related Articles | Metrics

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An earth-moon space navigation method based on the earth GNSS and navigation augmentation satellite TONG Zhao, ZHU Xiangpeng, CHEN Sufang, XU Lianjun, MENG Yansong Chinese Space Science and Technology    2024, 44 (3): 69-79.   DOI: 10.16708/j.cnki.1000-758X.2024.0040 Abstract （329）      PDF（pc） （11532KB）（384）       Knowledge map    It is of great significance that lunar spacecraft has the ability of GNSS autonomous navigation for the demands of high precision，low cost and autonomous navigation in the following human and unmanned lunar exploration task，which keeps up with the simple and low cost trends of the future lunar mission.However，the direct application of the earth GNSS navigation to the high precision earth-moon navigation scenario has the limited capacity of real-time navigation，which cannot meet the demand of the high precision navigation application for the future lunar exploration mission.Thus，the earth-moon space navigation method based on the GNSS and navigation  augmentation satellite was developed.By adding a moon navigation node which broadcasts navigation signal，the time synchronization link was built between GNSS and moon navigation satellite，and also between lunar users and moon navigation satellite，the clock and position error were decoupled and high precision real-time three-dimensional absolute navigation was realized.At last，the precision of the proposed navigation method was simulated and the results of simulation show that the PDOP of the user was highly improved.The positioning accuracy is better than 50 m and the method has high practicability. 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 （315）      PDF（pc） （7093KB）（479）       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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Fuzzy gain-adapting coupling attitude control for under-actuated spacecraft MENG Zhongjie, LU Junjie Chinese Space Science and Technology    2024, 44 (4): 11-19.   DOI: 10.16708/j.cnki.1000-758X.2024.0053 Abstract （305）      PDF（pc） （3949KB）（308）       Knowledge map    During rapid orbital maneuvers，aiming at the strong attitude disturbance problem caused by thrust misalignment and installation errors under solid propulsion，an underactuated spacecraft intelligent attitude control method based on thrust vector control technology is proposed.Firstly，the dynamic model of spacecraft attitude error is established，and the underactuated characteristic of thrust vector control inputs are analyzed.Then，considering the issues of strong disturbance uncertainty and weak coupling in the roll channel，an underactuated intelligent control law based on enhanced coupling strategy and adaptive fuzzy observer is designed.The fuzzy logic function is used to approximate the strong disturbance uncertainty term and introduced into the control law to achieve underactuated intelligent attitude control of spacecraft.The stability of the system has been proven through Lyapunov theory.Finally，through numerical simulation and comparison with the hierarchical sliding mode control method，the simulation results show that the designed method can shorten the three-axis attitude stability time by 14%，and can effectively eliminate the static error caused by weak roll channel，which provides a foundation for strong disturbance suppression technology during rapid orbital maneuvers. Related Articles | Metrics