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Research on distributed energy system of lunar surface research station YUAN Yong, ZHAO Chen, CAO Yan, LIU Zhiqiang, HU Zhenyu Chinese Space Science and Technology    2023, 43 (6): 32-42.   DOI: 10.16708/j.cnki.1000-758X.2023.0081 Abstract （566）      PDF（pc） （3965KB）（1151）       Knowledge map    The lunar surface research station is an exploration cluster，which is composed of several exploration units，including lunar surface command and control center，local / lunar to earth communication system，energy system and various exploration units.The energy system is an important part of the lunar research station.In order to efficiently configure，dispatch and operate the energy system，a distributed energy system concept was proposed.Photovoltaic power is mainly used to provide energy during the day，and nuclear power is used at night.The distributed energy system was studied.The power generation capacity，electricity demand，and payload power-using characteristics of each exploration units were fully analyzed.The architecture of lunar power grid was compared and analyzed，and the scheme of star shaped distributed energy system was selected.The concept of 10kW level long-term power supply was proposed，and the system composition was designed.The key technologies and construction methods of the energy system of lunar research station were analyzed，which can be used for the lunar surface research station in the future. Related Articles | Metrics

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A proposal of lunar standard time and its three progressive stages LIU Min, PING Jinsong, WANG Qianjuan, YU Hezhen Chinese Space Science and Technology    2026, 46 (5): 16-25.   DOI: 10.16708/j.cnki.1000-758X.2026.0073 Abstract （95）      PDF（pc） （1105KB）（74）       Knowledge map    This paper introduces the development of the lunar standard time and its definition based on general relativity and the simultaneity principle in four-dimensional spacetime. A three-step progressive approach is proposed to realize a coordinated lunar time. The primary step, with standard time on the earth ground adopted for traceability, applies to those without clocks deployed on lunar ground or in orbit thus unable to represent time unit on the moon. The intermediate step, with proper time of local clocks converted into coordinated time and an independent lunar standard time provided for time service, applies to those with at least 1 clock on the lunar ground representing SI second and are authorized as lunar local time reference by metrological administration. The advanced step, with time standard traced to an agreed convention by decentralized time keeping and broadcasting, time reference is not directly authorized anymore but replaced with different time keeping apparatus ID. This step applies to those with at least 4 time keeping devices deployed in lunar space or on the lunar ground. Users could obtain local time and position information from broadcast timestamps, and this mechanism is basically consistent with the existing Global Navigation Satellite System (GNSS) theories. Lunar standard time operates independently of Earth standard time. To meet the demand of users on both celestial bodies, timekeeping devices shall continuously monitor and release coordinate time comparison tables as well as terrestrial and lunar calendars. Those timekeeping methods in the three steps mentioned above provide theoretical reference for metrological specifications concerning the “Definition of Lunar Standard Time”. Related Articles | Metrics

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Lunar reference frame: realization, development and future perspectives HUANG Yong, ZHENG Jinjun, QU Weijing, CHANG Xinuo, GENG Renfang Chinese Space Science and Technology    2026, 46 (5): 1-15.   DOI: 10.16708/j.cnki.1000-758X.2026.0082 Abstract （154）      PDF（pc） （3151KB）（117）       Knowledge map    The lunar reference frame provides a fundamental infrastructure for high-precision lunar navigation, mapping, and scientific exploration. This paper presents a systematic review of its definition, realization, maintenance, and future development. Firstly, the fundamental concepts of the lunar reference frame are introduced, with a clear distinction between the lunar reference system and the lunar reference frame. Particular emphasis is placed on the two principal realizations currently adopted for lunar geodetic applications, namely the principal axes (PA) frame and the mean Earth/rotation axis (ME) frame, including their defining principles and transformation relationships. Secondly, the techniques used for the maintenance and refinement of the lunar reference frame are reviewed, including lunar laser ranging (LLR), very long baseline interferometry (VLBI), and photogrammetry. Finally, the contribution of the Earth-Moon navigation system to the establishment of the lunar reference frame is discussed. As a key infrastructure for cislunar space activities, such a navigation system provides essential technical support for the realization and long-term maintenance of the lunar reference frame. Future development is expected to focus on enhancing high-precision observation capabilities, improving multi-source data fusion, accelerating standardization, and strengthening international collaboration, thereby advancing the international lunar reference frame as a unified spatiotemporal reference for future lunar exploration.  Related Articles | Metrics

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RoMa-TRN:employing vision measurements to enable autonomous terrain relative navigation without maps for deep space missions TIAN Qihang, YANG Wei, LIN Dayong, XU Yunfei Chinese Space Science and Technology    2026, 46 (5): 38-47.   DOI: 10.16708/j.cnki.1000-758X.2026.0075 Abstract （80）      PDF（pc） （9278KB）（82）       Knowledge map    Autonomous terrain relative navigation (TRN) is expected to play a crucial role of upcoming planetary missions. Conventional TRN methods typically rely on landmark detection and image registration, which achieve relative pose estimation of the spacecraft by establishing data association between navigation images and onboard maps. The association problem between measurements and maps is a complex and computationally intensive task, and requires high accuracy in the prior knowledge onboard. Feature matching is a critical task in computer vision, aiming to achieve stable and accurate image registration under real-world varying conditions through robust visual models. This paper addresses the challenge of autonomous optical navigation for future deep space missions and for the first time, RoMa-TRN, an autonomous TRN method based on RoMa feature matching without maps is proposed. For sequential images captured by a monocular camera, the method employs the pre-trained visual model for front-end feature matching and constructs visual odometry. By solving a least-squares problem, it estimates the inter-frame direction of motion of the spacecraft. This measurement can be incorporated into an onboard navigation filter to update the state of spacecraft. Experimental results demonstrate that, compared with other feature matching methods, the proposed approach achieves accurate and robust image registration under varying illumination and viewpoint conditions. Under extreme scenarios with solar elevation angles of 1° and 89°, no significant performance degradation is observed. At an orbital altitude of 10 km, the method achieves a motion direction estimation accuracy of approximately 0.03°, enabling precise direction-of-motion for navigation filter. Related Articles | Metrics

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Space microgravity combination and its control YU Shao-Hua Chinese Space Science and Technology    2019, 39 (5): 49-.   DOI: 10.16708/j.cnki.1000-758X.2019.0039 Abstract （1174）      PDF（pc） （1448KB）（978）       Knowledge map    Space microgravity combination is an upgraded version of the tethered satellite system, a more powerful and prospective version for future applications. However, both the systems are beset with the same problem: if there is no preset control，the system′s motion is unstable. Therefore, an effective control algorithm has to be developed to make the system stable. Based on a simplified dynamic model of tethered satellite，the relationship between microgravity and dynamic inertia forces was used to deduce a very unique range rate control algorithm to stabilize the system concisely and productively. This algorithm can be applied to massdistributed, elastic and other more complex cases of tethered satellite control. It can also be successfully adopted to control inorbit rendezvous and docking missions of the space microgravity combination. 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 （1061）            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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Systematic bias self-calibration method for stellar aberration navigation system XIONG Kai, XU Chao, HUANG Xiangyu Chinese Space Science and Technology    2026, 46 (5): 26-37.   DOI: 10.16708/j.cnki.1000-758X.2026.0074 Abstract （93）      PDF（pc） （5541KB）（50）       Knowledge map    In order to reduce the effect of systematic bias on the performance of stellar aberration navigation system, a systematic bias estimation and compensation method based on a parametric model and an extended Kalman filter (EKF) is proposed. The systematic bias is described uniformly as relative installation errors of sensors. A stellar aberration navigation system model is established where spacecraft motion state, measurement noise and systematic bias are taken into consideration. Then a navigation filter is designed based on the model to estimate the systematic bias parameters together with the position and velocity of the spacecraft. The feasibility of the systematic bias self-calibration method is analyzed through the calculation of the Cramer-Rao lower bound (CRLB). The numerical simulation is implemented for an Earth satellite. It shows that the unfavorable effect of the system is suppressed evidently by using the proposed method. With an inter-star angle measurement accuracy of 0.1″, after the systematic bias self-calibration, the positioning accuracy of the stellar aberration navigation system is improved from about 50km to less than 3km. In comparison with the existing approach where the systematic bias is modeled as the inter-star angle measurement bias, the main advantage of the proposed method is that the dimension of the state vector to be estimated is independent of the number of the measurement, which facilitates the design of the onboard navigation algorithms. Related Articles | Metrics

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System design and validation of Queqiao-2 lunar relay communication satellite ZHANG Lihua, XIONG Liang, SUN Ji, CHEN Luojing, XIAO Chuan, ZHOU Wenyan, WANG Yong, LIU Wangwang, GUAN Yifeng, CHEN Tao, YU Xiaochuan, XU Jin, CHEN Guohui, CAO Xiaoping Chinese Space Science and Technology    2024, 44 (5): 23-39.   DOI: 10.16708/j.cnki.1000-758X.2024.0071 Abstract （1135）      PDF（pc） （8335KB）（1011）       Knowledge map    In order to provide relay communication supports for future Chinese lunar exploration program，Queqiao-2 relay communication satellite was developed.Queqiao-2 can perform scientific observations with three kinds of scientific instruments on board.The system design of Queqiao-2，including mission orbit and transfer orbit design，configuration and layout design，housekeeping and information flow design，power supply and distribution design，GNC and propulsion system design，communication links design，etc.，was accomplished through comprehensive tradeoff and evaluation on technical maturity，availability，schedule，cost，and so on.With a view to reducing development risk，both the platform and relay communication payloads were developed based on significant heritage from previous Queqiao relay satellite and other relevant spacecraft.Queqiao-2 features flexible system architecture to support multiple frequencies，modulations，data rates and software reconfigurations to meet new user requirements.Subsequent to a successful launch on March 20，2024，by means of 5 orbit maneuvers，Queqiao-2 was inserted into a highly elliptical frozen mission orbit around the moon with a 24h period on schedule.Following on-orbit tests and calibrations，Queqiao-2 has possessed the capacity to provide reliable relay communication services to multiple lunar exploration missions，as well as the capacity to perform scientific observations.Under the support of Queqiao-2，Chang′e-6 achieved its ambitious mission goal to collect  and return samples from the moon′s mysterious far side.In the meanwhile，Queqiao-2 has also paved the way for the following Chinese lunar exploration missions including Chang′e-7 and Chang′e-8.The design life time of Queqiao-2 is more than 8 years.Benefit from flexibility and extensibility of relay communication system design，it is convenient to provide relay communication services for future lunar exploration missions of both China and other countries.In addition，innovative scientific observations would be performed during the period that no relay communication task is arranged.The system design of Queqiao-2 reflects the development philosophy of technical innovations and inheritance integration.Based on highly flexible and extensible system architecture，multiple and concurrent relay communication mission requirements can be met.It can provide strong supports for future lunar exploration missions.Successful launching，orbit entering and on-orbit tests of Queqiao-2 verified the correct design principle and versatility.By means of Queqiao-2，more innovative scientific outcomes are anticipated and lunar exploration activities can be facilitated. Related Articles | Metrics

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Preparation of silicon oxide nanofluids via microfluidic for enhanced flow boiling heat transfer CHEN Hongqiang, GAO Quan, MA Xiang, ZHANG Yonghai, WEI Jinjia Chinese Space Science and Technology    2024, 44 (5): 66-74.   DOI: 10.16708/j.cnki.1000-758X.2024.0074 Abstract （422）      PDF（pc） （8788KB）（265）       Knowledge map    Enhanced microchannel flow boiling heat transfer using nanofluids is an effective method to improve the heat transfer performance of high-power electronic devices.However，conventional nanofluids face the challenges of complex fabrication processes，poor stability，and the inability to control nanoparticle size，which negatively affect the overall heat transfer efficiency.A simple microfluidic synthesis strategy is developed to prepare highly stable and size-controlled silica nanofluids in a continuous，efficient and high-throughput manner.A specially designed helical microchannel reactor enables continuous flow one-step synthesis of stable nanofluids with controllable particle sizes ranging from 30nm to 110nm simply by flow rate adjustment.The results of flow-boiling heat transfer experiments show that at higher flow rates（0.4m/s），the heat transfer performance of smaller-sized nanoparticles（≤55nm） is better than that of larger-sized nanoparticles（110nm），and the enhancement for critical heat flux（CHF） and heat transfer coefficient（HTC） reaches 90.9% and 68% respectively.The enhanced wettability of the boiling surface，efficient surface nucleation，and improved bubble dynamics provide theoretical explanations for the enhanced heat transfer performance.These findings provide not only a new method for controllable preparation of nanofluids，but also new ideas for efficient two-phase chip cooling of power devices in aerospace and power electronics. Related Articles | Metrics

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Experimental research on discharge characteristics of LHT40 low power Hall thruster CHEN Xinwei, GU Zuo, GAO Jun, GUO Ning, WANG Shangmin, ZHAO Yong, FENG Jie, SHI Kai, PU Yangxu, LI He Chinese Space Science and Technology    2021, 41 (5): 65-74.   DOI: 10.16708/j.cnki.1000-758X.2021.0068 Abstract （428）      PDF（pc） （6187KB）（498）       Knowledge map    In order to obtain the discharge characteristics of the 300W class hybrid-excited low-power Hall thruster, a high-precision micro-thrust laser measurement device and an integrated ion current density diagnostic device were used to access the characteristics of thrust, specific impulse, efficiency, beam divergence angle and mass utilization efficiency of the thruster for different operating conditions. There is a maximum for thrust, specific impulse and anode efficiency under discharge voltages from 200V to 300V. The discharge current and voltage exhibit damping-free harmonic oscillation, and the first-order frequency is about 4.05kHz. Under constant electric field and magnetic field, the beam ion current density presents a bipolar diffusion characteristics. When the anode flow rate is increased to 0.95 mg/s, the ion current density shows a typical doublepeak structure, and the mass utilization efficiency is positively correlated with anode mass flow rate. Related Articles | Metrics

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Research of dynamic beam resource scheduling of LEO constellation based on A2C algorithm LIU Wei, ZHENG Runze, ZHANG Lei, GAO Zihe, TAO Ying, CUI Kaixin Chinese Space Science and Technology    2023, 43 (3): 123-133.   DOI: 10.16708/j.cnki.1000-758X.2023.0045 Abstract （473）      PDF（pc） （3071KB）（422）       Knowledge map    The giant low-orbit constellation provides low-latency，large-capacity communication channels for user spacecraft such as manned spacecraft，space stations and remote sensing satellites，and there is a resource allocation optimizing problem of satellite beams.The intelligent optimization framework of A2C（advanced actor-critic）using discrete-time deep reinforcement learning was studied，and the beam resource scheduling algorithm that could effectively meet the needs of multi-users，dynamic and concurrent access was formed by combining the concepts of individuals and genes in genetic algorithms.Based on simulation and analysis，the proposed algorithm could be applicable in a variety of typical scenarios.The method could provide effective scheduling results for more than 3000 tasks in 20s，and the task success rate was not less than 91%.The complexity was reduced by algorithm optimization，which could save more than 45% of the time compared with traditional genetic algorithms.At the same time，the convergence problem in the traditional A2C algorithm framework was optimized，which solved the non-convergence problem in the traditional fully connected A2C algorithm.Meanwhile，the convergence speed was increased by more than 38% compared with the DQN（deep q-network）algorithm. Related Articles | Metrics

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Analysis and key design of lunar far-side robotic sampling and return misson SHENG Ruiqing, MENG Zhanfeng, ZHAO Yang, TAN Zhiyun, ZHANG Hong, HUANG Hao, ZHANG Wu Chinese Space Science and Technology    2024, 44 (5): 1-14.   DOI: 10.16708/j.cnki.1000-758X.2024.0069 Abstract （999）      PDF（pc） （17095KB）（744）       Knowledge map    The Chang′e-6 lunar probe is designed to achieve the first robotic sampling and return mission from the far side of the Moon.The lunar far side has rugged terrain overall and lacks flat areas suitable for sampling.Two areas in Apollo basin within south pole Atiken basin （SPA）are selected as primary and backup targeted landing sites，the safety and reliability of landing，lift-off and surface operation process are ensured.In order to achieve new mission objectives within the establis hed technical configuration，an optimal system design solution is put forward to reduce system changes.The risks associated with alterations of technical status are avoided.Through comparative analysis，a retrograde orbit around the Moon is selected，ensuring minimal system modifications and optimal system design.In consideration of the reduced and discontinuous duration of relay telemetry and control on the far side of the Moon for Chang′e-6，a phased，highly autonomous，and cooperative relay-assisted lunar surface operation timeline design is proposed to ensure the implementation during landing，lift-off and surface operation process.For payload carried by Chang′e-6，a system design is proposed by using data processing units as the central exchange hub to ensure electrical interface safety isolation；customized detection modes are also developed for different payloads to maximize detection benefits without affecting the completion of the main mission.These methods are applied in the Chang′e-6 mission，ensuring the success of the world′s first robotic sampling and return mission from the far side of the Moon，valuable reference and experience are provided for follow-up lunar exploration and deep space exploration missions. Related Articles | Metrics

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Technology and development prospects for lunar critical mineral resources utilization HE Chengdan, LI Zhengwei, WANG Yongjun , LIU Kun , ZHANG Yan , SHI Zhongning, WANG Jin, LI Lixia, YU Ruiyun, FENG Xiating, LI Detian Chinese Space Science and Technology    2026, 46 (3): 19-33.   DOI: 10.16708/j.cnki.1000-758X.2026.0034 Abstract （359）      PDF（pc） （4791KB）（391）       Knowledge map    The Moon harbors abundant critical mineral resources, including water ice,ilmenite and helium-3 (3He). Exploiting these resources holds significant strategic value for sustaining deep-space exploration missions, addressing future resource scarcity, and catalyzing new space-based economic models. This study introduces the reserves and occurrence characteristics of key lunar mineral resources such as water ice, solid minerals, and 3He. It identifies major challenges in lunar resource utilization, including the harsh extreme lunar environment, uncertainty in resource distribution, limitations of energy supply systems, and reliability of robotic equipment. Based on this, the study reviews research progress in the utilization technologies of key lunar mineral resources, summarizes the full-process technological system for lunar resource development and utilization, and puts forward development suggestions in areas such as interdisciplinary talent development, exploitation strategies, technical verification, feasibility studies, policies and regulations, and international cooperation models. Related Articles | Metrics

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Improved U-Net network and its application of road extraction in remote sensing image KONG Jiayuan , ZHANG Hesheng Chinese Space Science and Technology    2022, 42 (3): 105-113.   DOI: 10.16708/j.cnki.1000-758X.2022.0041 Abstract （661）      PDF（pc） （10925KB）（545）       Knowledge map    High resolution remote sensing image segmentation has a good application prospect in the military and civil fields, but due to the complex background conditions and the obstruction of interferences, the existing algorithms can’t extract road details from remote sensing images. Based on the improved U-Net network model, MDAU-Net (multi dimension attention U-Net) network structure model was proposed. The U-Net network structure was deepened to a seven-layer structure to improve the ability of fine segmentation of roads. A new multidimensional attention module,which was called MD-MECA (multi dimension modified efficient channel attention), was proposed to optimize the feature transfer in the coding part. DropBlock and Batch Normalization were used to resolve the overfitting during network training. The experimental results show that the improved algorithm can effectively improve the road extraction effect, and the accuracy rate on the test set reaches 97.04%. Related Articles | Metrics

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ApproachPlanningandControlMethodforRendezvouswithNoncooperativeTargetinanEllipticalOrbit XU Li-Jia, HU Yong Chinese Space Science and Technology    2015, 35 (6): 1-.   DOI: 10.3780/j.issn.1000-758X.2015.06.001 Abstract （911）      PDF（pc） （6937KB）（698）       Knowledge map    Theproblemsofapproachplanningandcontrolmethodforrendezvouswithanuncontrolledtumblingnoncooperativetargetinanellipticalorbitwerestudied.Onthepartofapproachplanning,thechaserandtargetspacecraftrendezvousedfromadistancetoasafeberthpoint,whichwasdesignedbyconsideringthestructureofthetargetspacecraft.Aftertheobservationattheberthpointforaperiodoftime,thegrasppointwasdeterminedandtheattitudemotionofthetargetspacecraftcanbepredicted.Then,asafeapproachtrajectoryfromtheberthpointtotheimplementpointforgraspingwasdesignedfortracking.Onthepartofcontrolmethod,byusingthemeasurementsoftherelativepositionandconsideringtheuncertaintiesoftheactualsystem,adaptivecontrollawsbasedonthecharacteristicmodelwereproposedforthewholerendezvousandapproachprocess.Finally,anexamplewasgiventoshowtheeffectivenessoftheproposedapproachplanningandcontrolmethod. Related Articles | Metrics

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Attitude determination algorithmfor micro-satellite based on Gauss-Newton and UKF KANG Guohua, FAN Kai, ZHOU Qiongfeng, LIANG Ertao Chinese Space Science and Technology    2018, 38 (2): 16-23.   DOI: 10.16708/j.cnki.1000-758X.2018.0017 Abstract （472）      PDF（pc） （11249KB）（218）       Knowledge map    To improve the attitude determination accuracy of miniature low-cost attitude sensor, a micro-satellite attitude determination algorithm combining Gauss-Newton iterative algorithmandunscented Kalman filter (UKF) was designed based on the attitude sensor configuration of magnetometer/solar sensor/gyroscope. Firstly, the Gauss-Newton algorithm was used to fuse the data of magnetometer and solar sensor, and the optimal quaternion was obtained. Secondly, UKF was performed using the optimal quaternion combined with gyrodata as the observed data, using the attitude quaternions and the angularvelocity of theinertial systemas the state variables, and the observed dimension was reduced and the observation equation was transformed into a linear equation by this method. As a result, the computational complexity is significantly reduced and the influence of measurement error on attitude determination accuracy is overcomed. Related Articles | Metrics

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Quality validation of HJ-1B satellite land surface temperature products based on DTW ZHANG Qi, LI Dacheng, LI Hua, DUAN Sibo, ZHANG Xiaoyu, HAN Qijin, GAO Haixia Chinese Space Science and Technology    2022, 42 (3): 93-104.   DOI: 10.16708/j.cnki.1000-758X.2022.0040 Abstract （320）      PDF（pc） （7784KB）（211）       Knowledge map    The HJ-1B satellite thermal infrared data is widely used,but the quality validation of its surface temperature retrieval products is not yet perfect.In response to this problem,part of multiple underlying surfaces in the Heihe River Basin was taken as the research area,HJ-1B data was used as the research data,and universal single-channel algorithm was used to invert the surface temperature of the different underlying surface research areas.The inversion results were verified using the ground observation site data of the Heihe River Basin and MODIS surface temperature data.Dynamic time warping was introduced to evaluate timing similarity.The results show that the relative deviation between the HJ-1B surface temperature inversion product and the ground observation value for desert and desert sites is within 1K,and the root mean square error(RMSE) is about 0.5K.The deviation for vegetation and crop sites is within 2K,and the RMSE is 1.2K.The evaluation result of the time-series mismatched data using DTW is consistent with the performance of existing indicators.The relative deviations between the HJ-1B surface temperature inversion products and the surface stations are lower than those between the HJ-1B surface temperature inversion products and the MODIS surface temperature inversion products. Related Articles | Metrics

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Development of advanced electric propulsion technology for cislunar and deep space exploration WU Chenchen, GENG Hai, WANG Zitong, LI Detian Chinese Space Science and Technology    2023, 43 (5): 13-23.   DOI: 10.16708/j.cnki.1000-758X.2023.0064 Abstract （628）      PDF（pc） （7207KB）（844）       Knowledge map    Space electric propulsion is the key technology of cislunar and deep space exploration.Space electric propulsion technology，one of the key technology of cislunar and deep space exploration,was focused on.The technical connotation of space electric propulsion and its application status in China was introduced，and the typical international cislunar and deep space exploration missions based on electric propulsion was analyzed from the dimensions of mission characteristics，electric propulsion configuration，and application benefits.Aiming at the future development needs of China’s deep space exploration，the optimization application stratrgies of electric propulsion were introduced for five typical scenarios: lunar exploration，asteroid exploration，human Mars exploration，solar system boundary exploration and cislunar space scientific exploration，and the key technical systems and development priorities of advanced electric propulsion for deep space exploration were sorted out.Finally，according to the development idea of “one medium，one super，one micro”，suggestions on space electric propulsion technology development were given，which provide a reference for a wider range of applications of space electric propulsion in the field of cislunar and deep space exploration. Related Articles | Metrics

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Thermospheric density determination and empirical model correction based on TLE data ZHANG Zhongtao, ZHANG Yakun, WANG Bin Chinese Space Science and Technology    2024, 44 (1): 54-64.   DOI: 10.16708/j.cnki.1000-758X.2024.0006 Abstract （485）      PDF（pc） （13519KB）（449）       Knowledge map     The thermosphere density model used for spacecraft orbit prediction generally has an error of about 30%，which affects the precise orbit determination and load control of LEO satellites.Based on the relationship between the change of horizontal motion of the low-orbit spacecraft and the atmospheric density，the TLE data of the GRACE（gravity recovery and climate experiment）satellite were used to invert the atmospheric density along the orbit in 2003 and 2007.After concluding the cause of the error in the relational analysis，the lognormal distribution was used to fit the density ratios.By analyzing the influence of solar radiation and geomagnetic index on atmospheric density changes，a correction and forecasting method of thermospheric density model based on space environment index was proposed.This method was used to correct the calculated density of the MSIS86 model in 2003，2004，2007 and 2008，the average relative error of the model was reduced from 33.33%~59.62% to 11.55%~15.13%，and the improvement in low solar activity years is 1.5~2 times of high solar activity years.The forecast correction was carried out on the empirical model results in 2009，which reduced the forecast error by 3649% and improved the model accuracy. Related Articles | Metrics

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Concept and verification of capture and orient module for Mars sample return LIU Zhi, GAO Jinzhong, YU Maohua, WANG Zhiyi, YANG Wenmiao, HAN Tian, LIU Zhou, YUAN Huiling Chinese Space Science and Technology    2024, 44 (5): 107-114.   DOI: 10.16708/j.cnki.1000-758X.2024.0079 Abstract （374）      PDF（pc） （9961KB）（373）       Knowledge map    An orbiting sample capture and orientation system architecture for the orbiting sample capture retrieve system concept is developed to enable on-orbit capture，orientation，and transfer of a Mars sample container into a containment vessel as part of a potential Mars sample return（MSR） campaign.The concept uses a rotating trap cover for orbiting sample （OS） capture，and four sector devices to form a retractable capture space for constraining and fixing OS container.The conveyor belts on the sector devices drive cooperatively with each other to realize OS container attitude correction and to transfer to a containment vessel with friction force and protruding bars acting on the OS container.In order to accurately realize sample orientation and transfer，a coordinated action strategy between the sector devices and the conveyor belts is formulated based on the sector angle signals.A prototype of OS capture and orientation mechanism is designed and developed，and the functions of OS capture，orientation and transfer are tested and verified.The mechanism has the characteristics of light weight（<12kg），high integration of orientation and transfer functions，strong adaptability of OS container attitude correction，and high transfer reliability，and can be applied to potential Mars sample return mission. Related Articles | Metrics