Most Down Articles

Published in last 1 year | In last 2 years| In last 3 years| All| Most Downloaded in Recent Month | Most Downloaded in Recent Year|

Most Downloaded in Recent Year

Please wait a minute...


For Selected: Download Citations EndNote Reference Manager ProCite BibTeX RefWorks Toggle Thumbnails

Select

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 （2240）      PDF（pc） （9757KB）（2646）       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

Select

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 （1002）      PDF（pc） （8217KB）（1018）       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

Select

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 （775）      PDF（pc） （8335KB）（812）       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

Select

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 （467）      PDF（pc） （2018KB）（1058）       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

Select

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 （575）      PDF（pc） （6075KB）（1372）       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

Select

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 （551）      PDF（pc） （9223KB）（643）       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

Select

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 （809）      PDF（pc） （17095KB）（632）       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

Select

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 （1837）      PDF（pc） （7344KB）（2098）       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

Select

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 （149）      PDF（pc） （7542KB）（610）       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

Select

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 （625）      PDF（pc） （7961KB）（556）       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

Select

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 （272）      PDF（pc） （5812KB）（546）       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

Select

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 （636）      PDF（pc） （15016KB）（532）       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

Select

Cloud detection methods for remote sensing images：a survey LIU Zili, YANG Jiajun, WANG Wenjing, SHI Zhenwei Chinese Space Science and Technology    2023, 43 (1): 1-17.   DOI: 10.16708/j.cnki.1000-758X.2023.0001 Abstract （1703）      PDF（pc） （2660KB）（2679）       Knowledge map    The cloud cover in the optical remote sensing images will obscure the ground information to varying degrees，which causes the blurring and loss of the surface observation information and greatly affects the imaging quality of remote sensing images.Therefore，the detection and evaluation of cloud cover in remote sensing images are the basis and key to further analyzing and utilizing remote sensing image information.Through sufficient investigation and summary，the development trend and representative work of cloud detection methods based on remote sensing images at home and abroad since the 1990s were reviewed.Cloud detection methods based on remote sensing images were divided into three categories：methods based on band threshold，methods based on classical machine learning and methods based on deep learning.Besides，the public datasets at home and abroad used in the related research on cloud detection were summarized，and the accuracy of some representative cloud detection methods was compared.In addition to the standard cloud detection methods，the cloud and fog（haze）detection，cloud and snow detection，cloud shadow detection and cloud removal methods related to cloud detection were also briefly reviewed.Based on the review and summary of cloud detection work above，the existing problems and future development trends of cloud detection were analyzed and prospected. Related Articles | Metrics

Select

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 Abstract （368）      PDF（pc） （10574KB）（487）       Knowledge map    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. Related Articles | Metrics

Select

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 （502）      PDF（pc） （16542KB）（482）       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

Select

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 Abstract （261）      PDF（pc） （6453KB）（460）       Knowledge map    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. Related Articles | Metrics

Select

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 Abstract （329）      PDF（pc） （5756KB）（456）       Knowledge map    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. Related Articles | Metrics

Select

Micro-vibration suppression method for agile & visible/infrared integrated small satellite YAN Meizhi, WEI Jianguang, ZHAO Zhiming, GUO Linli, HUANG Wei, CHANG Xinya, LIU Peng, LIU Yong, FENG Zhenwei Chinese Space Science and Technology    2024, 44 (5): 115-126.   DOI: 10.16708/j.cnki.1000-758X.2024.0080 Abstract （243）      PDF（pc） （11334KB）（451）       Knowledge map    With increasing demand for high resolution，integration and agility of optical remote sensing small satellites，visible/infrared dual-color common aperture camera as well as CMG（control moment gyroscope） are installed to meet the requirements of miniaturization，all-day and night，multi-target and multi-model imaging.On such satellites there are several kinds of components with micro-vibration，including CMG，infrared camera cryocooler，etc.，which has a great influence on image quality of camera and is difficult to suppress.Therefore，a comprehensive method for suppressing microvibration caused by above-mentioned disturbance sources is proposed，including CMG vibration isolator，isolating installation between cryocooler and camera optical structure，and damping truss is designed and installed to realize isolation between camera optical and satellite platform structure.Using above integrated disturbance source damping and terminal isolation measures，through analysis，calculation，satellite micro-vibration experiment verification and in-orbit test，the effect of micro vibration on image quality can be effectively reduced.Even for visible infrared integrated camera，the in-orbit dynamic MTF（modulation transfer function）of visible channel with sub-meter resolution can reach 0.1，and the influence factor of micro vibration on MTF can be controlled at 0.991. Related Articles | Metrics

Select

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 （788）      PDF（pc） （4641KB）（1096）       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

Select

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 （965）      PDF（pc） （4467KB）（1364）       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