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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 （556）      PDF（pc） （2018KB）（1994）       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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Research on system design and key technologies for crewed lunar landing and ascent WANG Xiang, ZHU Enyong, LIU Yang, HOU Zhendong Chinese Space Science and Technology    2026, 46 (2): 1-11.   DOI: 10.16708/j.cnki.1000-758X.2026.0019 Abstract （774）      PDF（pc） （8772KB）（1056）       Knowledge map    Lunar landing and ascent represents one of the riskiest and most challenging phases in crewed lunar exploration missions, exerting a direct impact on mission success and astronaut safety. Mastering and breaking through the key technologies for crewed lunar landing and ascent formed the core of developing a safe and reliable crewed lunar lander, and further drove the overall advancement of China’s crewed spaceflight technology. First, mission requirements for crewed lunar landing and ascent were analyzed, followed by the proposal of a system scheme for China's crewed lunar lander. Based on this scheme, an in-depth analysis was conducted on the key landing and ascent technologies specific to typical crewed mission demands, including emergency rescue design, ultra-soft landing design, lunar surface stable ascent, and autonomous rapid circumlunar rendezvous. Corresponding technical approaches and solutions were put forward accordingly. A circumlunar orbit design method optimizing fuel consumption for both nominal and emergency ascent, as well as an integrated planning method for emergency ascent and rendezvous-docking adapting to multi-constraint and variable-target scenarios were proposed, effectively enabling the crew to return safely at any stage during the landing and ascent process. A multidisciplinary optimization method for descent velocity was developed, taking into account plume heating, landing impact and landing stability, which provided a design reference for achieving ultra-soft lunar landing. A thrust coordinated control method for parallel orbit control engines and a rapid engine fault diagnosis method were established, enhancing the lander’s control capability and safety during lunar ascent. Additionally, a scheme design method for autonomous rapid circumlunar rendezvous under complex scenarios and multi-constraint conditions was presented, addressing the challenges in rendezvous scheme design under resource and time limitations. This analysis of key technologies for lunar landing and ascent provides a reference for the design of crewed lunar landers, and also helps deepen the understanding of the development difficulties and risks associated with such landers. Related Articles | Metrics

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Performance analysis of on-orbit testing of mechanically pumped two-phase loop for spacecraft MENG Qingliang, WEI Guanglang, YU Feng, YANG Tao, ZHAO Zhenming, ZHU Xu Chinese Space Science and Technology    2025, 45 (4): 70-78.   DOI: 10.16708/j.cnki.1000-758X.2025.0059 Abstract （456）      PDF（pc） （7542KB）（787）       Knowledge map    Mechanistically pumped two-phase loop (MPTL) is a two-phase heat transfer device, which possesses the strong heat transfer ability through the release of latent heat of liquid and vapor phase change during flow boiling process. MPTL shows a promising prospect in thermal control of spacecraft.The objective of the present study is to focus on the working characteristics and stability of MPTL under the microgravtiy environment on orbit. One MPTL, which included one shield centrifugal pump, one two-phase temperature controlling accumulator and one micro channel evaporator, was designed and constructed to investigate the characteristics of start-up, phase-changing heat transfer, and temperature-controlling for MPTL aboard one satellite. Test results shows that MPTL shows good working performance and stable operating behavior in microgravity environment. The two-phase accumulator presents good heat transfer performance under microgravity condition. Its temperature control accuracy reaches to ±0.1K. The passive cooling function of accumulator is validated, and its cooling rate reaches to 1℃/min. The temperature difference between the measuring points of vapor and liquid phase for the accumulator are in the range of 0.3～1.0K when the pump is working. The temperature control accuracy of the evaporator is in the range of ±0.1～±0.3K at the two rotation speeds. Superheating phenomenon takes place during the phase changing process of the loop and it leads to a higher 7～8K temperature at the evaporator’s outlet than the temperature control point. By comparing the results under the two rotation speeds, the superheat time and superheat temperature are related with the rotation speeds. The two-phase temperature controlling accumulator using the capillary structures can assure the function of high-precision temperature control and high-efficiency two-phase fluid management and control for MPTL under the microgravity condition. The phase transition characteristic for vapor-liquid is related to the mass flowrate of the loop. The stability of temperature on the evaporator is related to the fluid quality of its interior fluid. The study would contribute to the engineering design basis for the technology of two-phase flow and heat transfer, and would promote the development of active two-phase thermal control technology for space. Related Articles | Metrics

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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 （564）      PDF（pc） （5812KB）（769）       Knowledge map    In order to meet the requirement of high revisit and wide coverage of SAR system for national disaster prevention and reduction, the world’s first geosynchronous orbit SAR named Land Exploration 4rd(LT-4) was designed and developed. The satellite uses a ring-shaped reflector antenna and combined with phased array feed system, operating at L-band. The particularity of the orbit makes the satellite naturally have the characteristics of high revisit and wide coverage. In order to give a comprehensive description of the SAR payload system of LT-4, the characteristics of high orbit SAR which are different from low orbit SAR are described, and the key performance parameters of SAR payload are given. Then the working process of SAR payload is introduced, and the main functions and performance of the key equipment of SAR payload are expounded. At last, the history of load development for more than ten years is briefly described, and the load integration test items and test verification are given. The world's first high-orbit SAR image is obtained when the SAR payload works for the first time on orbit. The image information is rich and the payload’s on-orbit state is stable. The imaging results show that the SAR payload design is reasonable and the ground test and verification are sufficient, which can provide favorable information support for national disaster prevention and reduction. Related Articles | Metrics

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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 （371）      PDF（pc） （2366KB）（897）       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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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 （782）      PDF（pc） （7961KB）（616）       Knowledge map    The relevant policies， plans and specific projects of cave lunar bases at home and abroad were investigated systematically， with a focus on the comparative analysis of the existing gaps in research achievements. Based on the image information of lunar exploration at home and abroad and the research results of cave lunar base concept， the feasibility concept of cave lunar construction has been sorted out. Based on the unique advantages of the cave (such as suitable temperature， low radiation， less lunar dust， etc.) and the objective conditions of the difficulty of building a lunar base， a qualitative analysis was conducted on various concepts of cavebased lunar bases. Each type of lunar base configuration shows unique advantages： the cavebased lunar base based on the transformation of craters makes full use of the natural terrain on the lunar surface， combines the natural structural characteristics and artificial transformation requirements， and has significant advantages insitu resource utilization. Whether it is an unmanned or manned cave lunar base， it will go through four key strategic stages： lunar exploration， lunar address selection， lunar base construction and lunar base application. Although a large number of lunar images have been obtained through the launched lunar orbit probe， lunar surface probe and other exploration means， the current lunar surface exploration capabilities still need to be further improved to provide stronger support for the "site selection" work of the construction of the cave lunar base. At the same time， it is urgent to accelerate the development of key equipment for the construction of lunar bases as soon as possible， provide implementation tools for the construction of unmanned lunar bases， implement the "foundation" task of the cave lunar base， and realize the strategic goal of "cave utilization" of the cave lunar base as soon as possible. Related Articles | Metrics

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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 （493）      PDF（pc） （10574KB）（568）       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

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System design and key technologies of No.4 land exploration satellite 01 ZHANG Qingjun, NI Chong, DAI Chao, LIU Liping, TANG Zhihua, SHU Weiping Chinese Space Science and Technology    2025, 45 (1): 1-11.   DOI: 10.16708/j.cnki.1000-758X.2025.0001 Abstract （1254）      PDF（pc） （8217KB）（1224）       Knowledge map    In order to solve the problem of small imaging width and long revisiting time of low orbit SAR,China developed the No.4 land exploration satellite 01,which is a scientific satellite in the medium and long term development plan of national civil space infrastructure (2015-2025),and is the world′s first geosynchronous SAR satellite.Using the advantages of the geosynchronous orbit,the revisiting time of the same place can be reduced from the day level of low orbit satellite to the hour level,and the width can be increased from the hundred-kilometer level of low orbit satellite to the thousand-kilometer level,which can provide strong support for the effective implementation of disaster emergency response.For the new system of geosynchronous SAR microwave imaging,a series of key technologies are developed,such as microwave imaging for geosynchronous SAR,ultra-large power space-borne microwave transmission,ultra-large aperture space-borne antenna,large-flexibility and high-precision attitude stability control,intense pulse high-quality large power supply,integrated efficient thermal management for payload and platform,and integrated satellite-ground high-precision orbit determination.The satellite has the capability of quick revisit,large width,all-day and all-weather observation.The overall design of the satellite is introduced,and the technical innovation is summarized.Through the evaluation of the preliminary test results for the satellite in orbit,the geosynchronous SAR images have clear texture and good quality,which can meet the requirements of disaster prevention and reduction,land resource exploration and other tasks. Related Articles | Metrics

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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 （400）      PDF（pc） （6453KB）（530）       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

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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 （327）      PDF（pc） （3370KB）（689）       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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Manned lunar landing GNC technology and verification CHEN Shangshang, LI Ji, YANG Wei, WANG Xiaolei, ZHANG Yi, ZHANG Xiaowen, WANG Pengji, GUO Chaoli, LI Yuxin, JIA Feida, XI Kun, WEN Yi Chinese Space Science and Technology    2026, 46 (2): 71-81.   DOI: 10.16708/j.cnki.1000-758X.2026.0025 Abstract （372）      PDF（pc） （11885KB）（522）       Knowledge map    The guidance, navigation, and control (GNC) technology is most critical for achieving a soft landing on the lunar surface, and its design correctness critically relies on comprehensive ground verification. Compared with unmanned missions, manned lunar landings impose higher requirements on the reliability and autonomy of the GNC system. To address these challenges, several novel methods were proposed in guidance, including predictive descent orbit strategy, range-controlled powered explicit guidance law, and optimal constant-altitude hazard avoidance. For navigation, an integrated navigation scheme was designed based on signal consistency checking technology, which combined data from inertial measurement unit, microwave radar, and optical navigation sensors. For attitude control, technologies such as rapid disturbance estimation, high-precision torque allocation, and multi-engine fault detection were developed. To verify the developed GNC technology, the Attitude and Orbit Control System (AOCS) general platform models were adopted in mathematical simulations, and model parameters for newly developed individual units were obtained through experiments. For hardware-in-the-loop simulations, a new verification system was designed, featuring capabilities such as environment simulation and manual control simulation. For full-system comprehensive verification tests, additional scenarios such as emergency ascent and main engine failure were included. The mathematical simulations achieved a landing point accuracy better than 100m, the hardware-in-the-loop simulations demonstrated a navigation error of less than 1m in 1 minute, and the emergency handling procedures in the full-system comprehensive verification tests met expectations. Guidance and control results across all three verification methods were normal. The research methodology fully inherits China's existing landing GNC technologies, develops necessary new technologies tailored to the new mission characteristics, and has been validated through simulations and testing. The research results can provide valuable references for subsequent work. Related Articles | Metrics

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Accuracy analysis of GNSS real-time kinematic timing DONG Xiaosong, SUN Baoqi, YANG Haiyan, HAN Baomin, WU Meifang, MENG Lingda, YANG Xuhai Chinese Space Science and Technology    2021, 41 (6): 34-41.   DOI: 10.16708/j.cnki.1000-758X.2021.0079 Abstract （385）      PDF（pc） （3464KB）（840）       Knowledge map    Compared with PPP timing, real-time kinematic timing based on GNSS carrier phase observations can effectively avoid dependence on real-time precise orbit and clock products, and is of great significance to short-distance kinematic and static high-precision time users. In order to verify the performance of GNSS realtime kinematic timing, a timing experiment was carried out with the GPS system as an example based on the time and frequency resources as well as the observation data of three GNSS tracking stations for up to 2 months of the National Time Service Center of the Chinese Academy of Sciences. Compared with the PPP time transfer, the standard deviation of differences from realtime kinematic timing result is better than 0.15ns; compared with the result of optical fiber two-way time transfer, the standard deviation of differences from real-time kinematic timing result is better than 0.5ns. The experiments show that GNSS realtime kinematic timing accuracy can reach the sub-nanosecond level, which can provide an important reference for the future application of this timing technique. Related Articles | Metrics

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Propulsion technology of the lunar module for manned lunar exploration GU Shuaihua, WANG Jianhai, HU Yuzhou, ZHU Yinjuan Chinese Space Science and Technology    2026, 46 (2): 99-107.   DOI: 10.16708/j.cnki.1000-758X.2026.0028 Abstract （350）      PDF（pc） （4898KB）（508）       Knowledge map    A series of key technical issues, such as the design of high-performance and highly reliable propulsion systems for manned lunar exploration spacecraft, lightweight high-load-bearing large-volume tanks, and throttleable engine, have been addressed. A number of concerns and systematic control measures have been proposed to solve these technical problems. The pressure and pressure difference of the storage tank are ensured by differentiating the oxygen-fuel pressure reducing valve under large system flow and by compensating for pressure drop under small flow. The thrust consistency of the four variable-thrust engines is guaranteed by balancing the upstream flow resistance of the system and the thermal calibration of individual units. The above-mentioned methods were verified through technical verification by conducting single-machine tests and system-level tests. The results show that the proposed solutions in this paper can reduce or eliminate the risks faced by various key technologies. The technical problems of pressure difference stability control of common bottom tanks under large and small flow rates and thrust consistency control of four variable-thrust engines have been solved. The pressure difference of the common bottom tank can be controlled within a small range of 0 to 0.3MPa, and the thrust deviation of the four variable-thrust engines is controlled within 100N. These researches indicate that manned lunar exploration has overcome the key technical challenges of the propulsion system, and can reliably provide power for manned lunar spacecraft, as well as offer new ideas for the design of subsequent spacecraft. 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 （1050）      PDF（pc） （1373KB）（1745）       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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Aerialrelativemeasurementbasedonmonocularreconstructionfornoncooperationtarget LI Yong-Fei, WANG Shi-Cheng, YANG Dong-Fang, SUN Da-Wei Chinese Space Science and Technology    2016, 36 (5): 48-.   DOI: 10.16708/j.cnki.1000-758X.2016.0057 Abstract （1005）            Knowledge map    Amonocularvisionbasedrelativepositionandattitudemeasurementalgorithmwaspresented，whichcombinedthereconstructionoftargetswiththemeasurementofrelativepositionsandattitudefornoncooperationtargets.Firstly，aseriesofpointsonthetargetswerereconstructedusingtheimagesobtainedintheearliermeasurementwithafastandgloballyconvergentstructureandmotionestimation.Secondly，therelativepositionandattitudewerecalculatedbyusingaKalmanfilterbasedonrecursivedepthparametrization，inwhichnewpointsobservedfromnewimageswererecoveredandaddedtothe3Dpointsettoimprovetheaccuracyandrobustnessofthemeasurement.Experimentresultshowsthattheattitudemeasurementcanachieveanaccuracyhigherthan1°,andthepositionmeasurementcanachieveanaccuracyhigherthan2cm，whichindicatesthehighprecisionoftheproposedalgorithm. Related Articles | Metrics

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Error source analysis and compensation in test chain for dualaxial analog sun sensor XU Xiaodan, WANG Jianfu, CHONG Huixuan, GAO Changshan, LIANG He, HONG Shuai, Chinese Space Science and Technology    2019, 39 (1): 19-.   DOI: 10.16708/j.cnki.1000-758X.2018.0072 Abstract （651）      PDF（pc） （8157KB）（699）       Knowledge map    Based on 4quadrant silicon cell, a dualaxial analog sun sensor can get the sun incident angle about two axes simultaneously. The acquisition accuracy of the four quadrant photocurrents determines the sensor performance directly. But the inconformity arisen from the test chain brings measurement deviation to the sensor. Therefore, based on numerical simulation, the influence model of the inconformity in the responsivity of each cell quadrant and then the C/V transformer, amplifier, A/D conversion and dark current for each quadrant photocurrent was established and analyzed. Then the calibration and compensation of such error sources were proposed. As a result, the requirement for the uniformity in the test chain can be lowered with the precondition of the sensor measurement accuracy. Test result shows that without changing the test chain parameters, the measuring accuracy of the sun sensor is improved from 2.05° (αaxis, 3σ) and 1.94° (βaxis, 3σ) to 0.28° (αaxis, 3σ) and 0.26° (βaxis, 3σ). Related Articles | Metrics

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Numerical study of electromagnetic acceleration mechanism for pulsed plasma thruster YANG Sanxiang, LIU Chao, WANG Shangmin, FENG Jie, CHEN Juanjuan, WU Chenchen, JIA Yanhui, GUO Ning, GENG Hai Chinese Space Science and Technology    2020, 40 (4): 11-21.   DOI: 10.16708/j.cnki.1000-758X.2020.0040 Abstract （731）      PDF（pc） （12440KB）（866）       Knowledge map    In order to get a clear understanding of electromagnetic acceleration mechanism for pulsed plasma thrusters, and offer a theoretical foundation for the performance optimization and minification of the thruster，numerical simulation of the pulsed plasma thruster characteristic is necessarily to be researched. In this paper, a onedimensional integrated circuit model that includes the capacitance, inductance, electrodes and plasma is used to numerically study pulsed plasma thrusters. The electromagnetic acceleration mechanism of pulsed plasma thrusters is systematically investigated by varying the initial discharge voltage and separation distance of the electrodes. The results show that the thrust, specific impulse, impulse bit of pulsed plasma thrusters, and temperature and density of plasma increase with initial discharge voltage. Similarly, the thrust and specific impulse of thrusters also increase with the separation distance of electrodes. However, the igniting difficulty of thruster increases since the resistance between electrodes increases with the electrodes spacing. Therefore, there is an optimal value of distance between electrodes of the pulsed plasma thruster.  Related Articles | Metrics

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Aerodynamic and structural simulation of space reentry inflatable aeroshell at high angle of attack ZHANG Zhang, WU Jie, WANG Liwu, HOU Anping, CAO Xu, WANG Qi Chinese Space Science and Technology    2019, 39 (6): 80-.   DOI: 10.16708/j.cnki.1000-758X.2019.0053 Abstract （344）      PDF（pc） （5588KB）（696）       Knowledge map    For the description of the aerodynamic and structural characteristics of the space reentry inflatable aeroshell at high angle of attack, the CFD model was used to calculate the flow field distribution and aerodynamic coefficients at different angles of attack. At the same time, the finite element model considering the internal pressure was established. Using the hypersonic flow field as the input, the influence of aerodynamic force on the static characteristics of structure at different angles of attack was analyzed by the one way fluidstructure interaction method. The results show that with the increase of angle of attack, the axial force coefficient decreases as a whole, while the normal force coefficient and pitching moment coefficient show Mtype and Wtype trends. Furthermore, the maximum stress of the structure increases with angles of attack increment, and the maximum increase is near 45° angle of attack. 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 （613）      PDF（pc） （2682KB）（472）       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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Cutting-edge scientific issues in ice giant exploration WANG Chi, LI Hui, KONG Dali, WANG Yuxian, YANG Zhongwei Chinese Space Science and Technology    2025, 45 (4): 1-11.   DOI: 10.16708/j.cnki.1000-758X.2025.0053 Abstract （536）      PDF（pc） （9196KB）（444）       Knowledge map    Exploring ice giants and their moons stands as one of the frontiers in deep space exploration and space science research. Current international planetary exploration plans all include missions to ice giants. Focusing on China’s future ice giant exploration missions, the current status of ice giant exploration is investigated, and seven key scientific questions are identified and summarized. By comparing and analyzing the characteristics of ice giant systems, and combining with the development trends in planetary exploration, the prospects and recommendations for future ice giant missions are proposed. Neptune-Triton exploration as a priority for ice giant missions is highlighted. Future exploration can be broadly divided into three subjects: exploring extraterrestrial oceans and life, understanding Kuiper belt objects and solar system evolution, and investigating ice giant systems to understand planetary origins and evolution. Analyzing the scientific objectives for ice giant exploration provides a scientific reference for China’s future deep space missions. Related Articles | Metrics