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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 （517）      PDF（pc） （2018KB）（1590）       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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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 （331）      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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Comprehensive performance optimized design methodology for LEO heterogeneous constellations LIU Siyang, PAN Ruixue, LI Renfei, MENG Tao Chinese Space Science and Technology    2026, 46 (1): 59-72.   DOI: 10.16708/j.cnki.1000-758X.2026.0009 Abstract （124）      PDF（pc） （8845KB）（102）       Knowledge map    A comprehensive study is conducted on the design methodology for low Earth orbit (LEO) mega-constellations composed of heterogeneous satellites with diverse functions, orbits and payloads. Three critical challenges are addressed, including nonlinear coverage superposition, differentially coupled drift trajectories, and large-parameter optimization. An efficient semi-major axis decay model is developed under the influence of J2 perturbation and atmospheric drag with combined linear and quadratic fitting. Relative drift compensation equations for both the right ascension of the ascending node and the argument of latitude are derived to maintain orbital stability. A complex optimization model is constructed with the objective of minimizing the integrated manufacturing-launch cost, incorporating multi-dimensional coverage constraints such as revisit time, imaging resolution and coverage stability as well as multi-source engineering constraints including limited fuel, selectable satellites, and multiple mission phases. Key variables are reduced through theoretical analysis to improve computational efficiency. A genetic algorithm is employed to determine the cost-optimal nominal configuration parameters. Furthermore, a closed-loop design framework is developed to coordinate nominal configuration, partial correction, fuel planning, and control implementation throughout the constellation lifecycle. For missions targeting coverage between 30°(N) and the equator, with constraints of ≤10min revisit time and ≤1m imaging resolution, the optimized heterogeneous constellation configuration demonstrates a 26%～30% reduction in total cost compared with uniform configurations. Additionally, temporal consistency of revisit time across different latitudes shows improvement. The performance advantage increases with wider latitude coverage. The optimized methodology enables synergistic optimization of coverage performance and cost, supports scalable design of constellations exceeding 1000 satellites for emergency remote sensing and global IoT applications, and contributes to reduced lifecycle cost and design complexity.  Related Articles | Metrics

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Overview of LEO satellite networking communication technology for direct-to-phone connectivity LI Jingling WANG Xianyu, ZHEN Li, MENG Qingzhi, LIANG Wei, MU Tong, CUI Tao, LI Qian, CUI Wanzhao Chinese Space Science and Technology    2026, 46 (1): 1-12.   DOI: 10.16708/j.cnki.1000-758X.2026.0005 Abstract （435）      PDF（pc） （2682KB）（304）       Knowledge map    To overcome the limitations of traditional terrestrial communication coverage and establish seamless, all-time, all-domain connectivity capabilities through direct-to-phone connection of integrated space-ground services, this study conducts a systematic review of communication technologies for direct-to-phone connection to LEO satellite networks. Firstly, the application background, concepts and connotations of direct-to-phone LEO satellite network are elaborated. Subsequently, the network architecture for direct-to-phone LEO satellite network is provided, along with the service characteristics and performance indicator requirements for individual and enterprise users. The development trends, comparative strengths, limitations, and technological evolution of the three main technical routes for direct-to-phone LEO satellite network are specifically analyzed. The key issues and technical challenges faced by LEO satellite network are identified, including severe spectrum resource constraint, link limitation and power imbalance, multi-user concurrent access collision, high dynamic spatio-temporal mismatch, and difficulties in ensuring continuity communication. Based on the foregoing analyses, the critical technologies for direct-to-phone LEO satellite network communication are distilled, such as spectrum resource optimization, the evolution of 5G/6G standardized protocols, ultra-large-scale satellite-borne antenna technology, efficient management and control of satellite network resources. Finally, to address the demands of 6G service applications, novel enabling roles of 6G technologies in direct-to-phone LEO satellite networks are proposed, including integrated space-ground architecture, AI-driven optimization, space-based computing networks, and wireless communication-sensing-computing convergence. This review offers a practical and feasible technical direction for the development of direct-to-phone LEO satellite network communication technology. 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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Agile design of satellite systems for large-scale constellations  JIA Xiaodong, CUI Yufu, LIU Jingyu, LI Chunguang, LIU Pengyu, CAO Lijun, XIN Xu Chinese Space Science and Technology    2026, 46 (1): 48-58.   DOI: 10.16708/j.cnki.1000-758X.2026.0008 Abstract （202）      PDF（pc） （11103KB）（162）       Knowledge map    In the field of mass production of low-orbit large-scale satellite, the traditional document-based systems design method exists many problems such as insufficient systematization, low iteration efficiency, and difficulties in batch testing. This study aims to construct a kind of agile design method of satellite system based on model-based systems engineering (MBSE) to achieve efficient iteration and batch verification of design process, and short the development requirements cycle of large-scale constellations. This paper gives a technical path combining a multi-level model reuse architecture and an incremental development model. Firstly, a three-level model system (system level-subsystem level-unit level) is constructed. Through the multi-level reuse mechanism of the meta-model library, unit library and architecture library, the design experience is solidified by model. Secondly, an incremental development mode based on use cases is proposed. The requirement changes are mapped to scenario iterations, and requirements are dynamically transferred to indices through SysML models. Finally, a batch testing design method based on system verification models is established, and the traceability matrix between test cases and requirements is constructed to achieve full-link closed-loop verification of design and testing. This research takes the mass production project of optical remote sensing satellites as a case. Through the model iterative of input parameters, the trade-off of subsystem schemes and the verification of mission requirements, the method is verified by engineering case. The application verification shows that the design efficiency is improved by approximately 80%. The MBSE agile design method proposed in this study realizes the digital inheritance of design experience by the model reuse mechanism, solves the problem of efficient response of requirement changes by the incremental development mode based on use cases, and improves the batch verification capability of large-scale constellations by the closed-loop mechanism of test. This research results provide a scalable technical framework for the digital transformation of satellite system engineering and expand the application depth of models in the entire life cycle of satellite mass production. Related Articles | Metrics

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Research of technology development for Venus balloon YANG Mei, FU Chenrui, XUE Shuyan, ZHANG Zhengfeng, WEI Yunfei Chinese Space Science and Technology    2026, 46 (1): 97-110.   DOI: 10.16708/j.cnki.1000-758X.2026.0003 Abstract （154）      PDF（pc） （10409KB）（126）       Knowledge map    This paper first defines the composition and types of Venus exploration balloons based on the operational environment of Earth observation balloons, then reviews the characteristics of the Venus atmosphere and its impact on balloon technology. Subsequently, the key technical challenges of adapting balloons to the Venusian atmosphere are addressed. Based on existing Venus and Earth balloon technologies, the study explores crucial aspects of design and technology, including payload design, envelope design, energy systems, temperature control, altitude control, and aerial unfolding and inflation methods. For both high-altitude and low-altitude Venus balloons, the research examines the characteristics of the Venusian atmosphere. Above 50 km altitude, the atmosphere of Venus resembles Earth’s environment, making it easier to adapt Earth-based technologies; however, below 50 km, the atmosphere is characterized by high temperature and pressure with insufficient sunlight. The paper summarizes the technological maturity and engineering feasibility, offering a reference for the development of Venus exploration balloons and the implementation of related scientific missions. 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）（587）       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

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Research on added mass of disk-gap-band parachute JIANG Tian, GE Sicheng, WANG Yihang Chinese Space Science and Technology    2024, 44 (4): 161-172.   DOI: 10.16708/j.cnki.1000-758X.2024.0067 Abstract （174）      PDF（pc） （9480KB）（518）       Knowledge map    The conventional approach to quantifying the added mass of a parachute relies on the premise of an optimal canopy configuration，necessitating the utilization of empirical formulas and coefficients for analysis.Nevertheless，the procedure to identify the added mass is not addressed.A joint simulation scheme is established to facilitate fluid-solid interaction simulation and the calculation of added mass for the disk-gap-band parachute.Correspondingly，a canopy reconstruction strategy is provided for determining the shape of the disk-gap-band parachute and a novel methodology is proposed for the numerical computation of the added mass associated with intricate geometries. The results indicate that through the range of dimensionless inflation time from 0 to 0.6，the increase in added mass of a single disk is equivalent to the aggregate of the parachute.This observation aligns with the mathematical model obtained from established empirical formulas. Following this，a model of a cup with gap is provided that accurately represents the added mass of parachutes at specific time intervals.Correlations are established between the gap structure and other factors such as the height-to-radius ratio，with the aim of deriving a modified empirical formula for predicting the added mass in disk-gap-band parachutes under diverse operational circumstances.The results show that the modified formula is helpful to improve the calculation accuracy of the dynamics simulation in supersonic conditions during the disk-gap-band parachute inflation stage.The research can provide support and reference for the high-precision modeling and analysis for the inflation process of the disk-gap-band parachute. Related Articles | Metrics

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Adaptive teaching-learning-based optimization for multi-satellite collaborative mission planning LIU Yan, LIU Guohua, WEN Zhijiang, HU Haiying Chinese Space Science and Technology    2026, 46 (1): 73-82.   DOI: 10.16708/j.cnki.1000-758X.2026.0010 Abstract （115）      PDF（pc） （5680KB）（64）       Knowledge map    To address the insufficient dynamic adaptability in collaborative observation mission planning for low-earth orbit mega-constellations, an adaptive teaching-learning-based optimization algorithm was proposed. Within the teaching-learning framework, adaptive mechanisms and hybrid learning strategies were incorporated. The teaching phase was enhanced through time-varying teaching factors and an elite-guided mechanism, while the learning phase was improved using hybrid learning strategies to dynamically balance global exploration and local exploitation capabilities. Simulations demonstrated that the proposed algorithm outperformed both the improved genetic algorithm and the improved differential teaching-learning-based optimization algorithm in terms of task completion rate and computational time. In large-scale, high-complexity multi-satellite collaborative mission scenarios, it achieved 6% and 16% higher task completion rates compared to baseline algorithms, proving suitable for high-dimensional discrete optimization problems. The algorithm exhibits advantages in task completion rate, operational efficiency, and robustness, making it applicable to collaborative observation missions in low-earth orbit constellations. Related Articles | Metrics

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Improvement and application of MCTS in turn-based orbital games ZHENG Xinyu, ZHANG Yi, ZHOU Jie, TANG Peijia, PENG Shengren, DANG Zhaohui Chinese Space Science and Technology    2024, 44 (5): 75-82.   DOI: 10.16708/j.cnki.1000-758X.2024.0075 Abstract （275）      PDF（pc） （3370KB）（558）       Knowledge map     The sensing delay of orbit change in turn-based orbit pursuitevasion game brings difficulties to differential game approaches，and deep reinforcement learning-based algorithms are still risky for engineering applications due to the inexplicability.The predictive-value-accumulate Monte Carlo tree search（PVA-MCTS） algorithm is proposed for the turn-based orbit pursuit-evasion game.Based on the predictability of spacecraft orbital motion，the algorithm predicts and accumulates the decision value in the game.This solves the problem of sparse reward and large time span in the turn-based orbit pursuit-evasion game，and improves the learning efficiency.It is used to solve the turn-based orbit pursuit-evasion game，and compared with the results obtained by Monte Carlo tree search（MCTS） algorithm.The results show that the PVA-MCTS algorithm reduces the pursuit time by about 27.6% and increases the escape time by about 6.8% for pursuer and evader respectively.The PVA-MCTS algorithm is realistic for the application of orbital game in the fields of non-cooperative target approaching and collision avoidance. Related Articles | Metrics

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Design and implementation of thermal balance test scheme for Chang'e-5 probe NING Xianwen, JIANG Fan, CHEN Yang, ZHANG Dong, WANG Yuying, XUE Shuyan Chinese Space Science and Technology    2021, 41 (6): 132-137.   DOI: 10.16708/j.cnki.1000-758X.2021.0090 Abstract （346）      PDF（pc） （4036KB）（517）       Knowledge map    Aiming at the problems faced in the thermal balance test of Chang’e-5 probe, a set of thermal balance test scheme was constructed, and a thermal balance test method was proposed based on the analysis of the current situation of thermal balance test technology of spacecraft at home and abroad, as well as the principle of full verification, effectiveness and comprehensiveness. A special infrared absorption space heat flux simulation method was used. The typical test conditions were designed, and the test technical process was optimized. The results of thermal balance test combined with on-orbit flight show that the thermal balance test scheme can effectively verify the correctness of thermal control design, that the temperature impact caused by the deviation of the space heat flux simulation device does not exceed 2℃, and that the setting of test conditions and the technical process is reasonable. The correlation of thermal analysis model can make the thermal analytical model more accurate and reliable. Related Articles | Metrics

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Simulation study on the influence of magnetic screen size on Hall thruster performance XU Zongqi, TIAN Leichao, WANG Pingyang, HUA Zhiwei, HANG Guanrong Chinese Space Science and Technology    2023, 43 (4): 43-51.   DOI: 10.16708/j.cnki.1000-758X.2023.0052 Abstract （239）      PDF（pc） （6134KB）（220）       Knowledge map     Magnetic screen is an important part of magnetic circuit system, and its sizes have an important influence on magnetic flux density distribution.In order to explore the influence law, a low-power Hall thruster was chosen as the research object.First, the finite element software Maxwell was used to simulate the magnetic flux density distributions under different axial and radial sizes of the magnetic screens.The results showed that there was a set of dimensions that could create the best magnetic field configuration for the thruster.Then, PIC method was employed to simulate the distributions of plasma parameters at 200V anode voltage and 0.8mg/s gas flow rate in the discharge channel with the dimensions as the design standard.Finally, according to the ion velocity and ion number density distributions, the calculated thrust, anode specific impulse, and anode efficiency were respectively 6.9mN, 880s, and 41.89%.This simulation study provides a theoretical basis for magnetic field design of Hall thruster and a numerical reference for future experimental research. Related Articles | Metrics

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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 （2346）      PDF（pc） （9757KB）（2714）       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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Application of wavelet analysis in GPS satellite fault detection HE Li-Wen, LI Xin-Guo Chinese Space Science and Technology    2017, 37 (6): 56-.   DOI: 10.16708/j.cnki.1000-758X.2017.0084 Abstract （994）      PDF（pc） （1373KB）（1707）       Knowledge map    At present, the residual chisquare detection method based on extended Kalman filter has been widely used in GPS satellite fault detection independently by the receiver. However, this method has some problems such as dependency on mathematical model and detection delay. A GPS satellite fault detection method based on wavelet analysis was proposed. The wavelet analysis was used to analyze the GPS data in the time and frequency domain, and the data could be processed as multiscale analysis. Abnormal points were used to determine the occurrence of failure. The simulation results show that the proposed method is efficient, sensitive, concise and easy to implement. It′s useful to the reliability and stability of navigation system. Related Articles | Metrics

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Opportunities and challenges of long-distance high-capacity continuous wireless power transmission LI Ming, DONG Shiwei, SHI Dele Chinese Space Science and Technology    2023, 43 (3): 1-13.   DOI: 10.16708/j.cnki.1000-758X.2023.0033 Abstract （506）      PDF（pc） （1058KB）（930）       Knowledge map    Long-distance high-capacity continuous wireless power transmission（WPT）is one of the candidate routes to realize space-based solar power exploitation and carbon neutrality.Firstly，the application demands and development opportunities were introduced with specific technical requirements for practical applications of long-distance high-capacity continuous WPT.Secondly，the international state-of-the-art research progress was reported.Then technical challenges were discussed，with respect to development trend and application needs.And toward these challenges，development suggestions were proposed. 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 （675）      PDF（pc） （6075KB）（1512）       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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Radiometric Calibration and Accuracy Analysis based on Spaceborne SAR TAO Man-Yi, JI Peng, HUANG Yuan-Bao, JIANG Yan Chinese Space Science and Technology    2015, 35 (5): 64-70.   DOI: 10.3780/j.issn.1000-758X.2015.05.009 Abstract （1250）      PDF（pc） （3082KB）（1359）       Knowledge map    With the development of spaceborne synthetic aperture radar(SAR)application,the radiometric calibration technology was used to observe objects′ physical characters.    Because the radiometric calibration technology is very complex,on the study of radiometric calibration and accuracy analysis will be mostly focused in the strip mode with single channel and single polarization.Firstly,the radar equation was derivated,then with the measured calibration constant,the short-term and long-term relative calibrations were studied based on an error model and formula. At the same time,the influence of calibration constant for absolute radiometric precision was analyzed and the system correct was finished.Finally the validated result on TerraSAR-X satellite shows that the difference of the calculated value and the measured one is less than 0.05dB. Related Articles | Metrics

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A novel DOR beacon for deep space navigation and positioning GAN Jiangying, SHU Fengchun, WU Yajun, TONG Fengxian, GUO Shaoguang, WU De Chinese Space Science and Technology    2022, 42 (2): 91-98.   DOI: 10.16708/j.cnki.1000-758X.2022.0026 Abstract （255）      PDF（pc） （5835KB）（316）       Knowledge map    Very long baseline interferometry (VLBI) is one of the important approaches of navigation and positioning of deep space probes. The differential one-way ranging (DOR) beacons and delta differential one-way ranging (Delta-DOR) measurement systems, which accurately determine the angular distance of the deep-space detector with respect to the extraterrestrial radio source, are often used in VLBI observations of deep space probes. Phase dispersion is one of the main sources of error that reduce the accuracy of measurement. A new DOR beacon (PN-DOR) was developed based on the pseudorandom noise modulation method and the design and implementation of the beacon were carried out. Moreover, the optimization methods of the Gold code bandwidth, polynomials, the shaping filters coefficients and the DOR signal modulation index were analyzed in the time and frequency domain. The PN-DOR beacon can effectively reduce the delay error induced by phase dispersion and improve the Delta-DOR measurement accuracy, thus meeting the needs of high-precision navigation and positioning of future deep-space probe missions of China. Related Articles | Metrics

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Mid-to long-wave infrared SNSPD and discussion on its applications in astronomy XU Dingyan, CHEN Qi, ZHANG Labao, WU Peiheng Chinese Space Science and Technology    2026, 46 (1): 83-96.   DOI: 10.16708/j.cnki.1000-758X.2026.0011 Abstract （110）      PDF（pc） （6814KB）（58）       Knowledge map    Superconducting nanowire single-photon detector (SNSPD) is a high-performance single-photon detector that can be extended to the mid-to long-wave infrared range. It is highly suitable for astronomical observation missions with requirements of a wide observation range, weak signal detection, and low dark count rates. This article introduces optical response models of SNSPD, establishes a connection between SNSPD parameters and astronomical measures, and describes the development of SNSPD in the mid-to long-wave infrared band. It analyzes the research directions and difficulties from the perspectives of materials, fabrications, device structures, optical enhancement structures, and large array size. It discusses the feasibility of its applications in astronomical detection fields, such as Lidar and exoplanet spectral detection. Finally, it summarizes and looks forward to the development direction of mid-to long-wave SNSPD, highlighting the issues that still need to be resolved, such as further wavelength extension, infrared optical enhancement structures, and miniaturization. SNSPD has achieved saturated internal quantum efficiency at 29μm, but there is still a far way from realizing megapixel arrays and high-detection efficiency devices. With the advancement of micro-nano processing technology and refrigeration technology, it is accessible to achieve high-efficiency mid-to long-wave SNSPD array devices on satellites. Related Articles | Metrics