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01 June 2025, Volume 45 Issue 3 Previous Issue   

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Structure and mechanical properties of lunar glasses CHEN Ziqiang, ZHAO Yong, CHI Xiang, YAN Yuqiang, SHEN Jie, ZOU Minjie, ZHAO Shaofan, LIU Ming, YAO Wei, ZHANG Bo, KE Haibo, MA Xiuliang, BAI Haiyang, YANG Mengfei, ZOU Zhigang, WANG Weihua 2025, 45 (3):  1-8.  doi: 10.16708/j.cnki.1000.758X.2025.0033 Abstract ( 88 )   PDF (18306KB) ( 45 )   Save Glass, a main component of lunar soil, is widely mixed in various forms like particles and agglutinates of small sizes in lunar soil and has good spatial applicability. The good glass-forming ability of lunar soil makes it the preferred raw material for the preparation of space glass materials. However, due to the lack of micro and nano sample preparation and detection methods, the mechanical properties of lunar glasses are rarely reported before, which seriously restricts the service evaluation of such glassy materials. In this study, the microstructures and mechanical properties of five typical Chang'e-5 lunar glassy particles are systematically studied by means of micro and nano sample preparation and mechanical testing combined with transmission electron microscopy (TEM) characterization. The results show that the lunar glasses have flexible and changeable (homogeneous to nano scaled inhomogeneous) amorphous structures and broad controllable mechanical properties (hardness ranges from (6.1±0.4)GPa to (8.4±0.2)GPa, modulus ranges from (48.5±1.9)GPa to (88.4±2.4)GPa). In addition, there is a marvelous decoupling phenomenon between the hardness and modulus of the lunar glasses, i.e., the rejuvenation process (heating them up to the supercooled liquid region and then cooling down to room temperature at fast cooling rates) greatly reduces the modulus while has much weaker effects on the hardness, which is attributed to the deformation mode changed from densification to shear flow. The rejuvenation process will induce volume expansion and inhomogeneous structure in the lunar glasses, which will facilitate such deformation change, leading to hardening effects. The results can provide guidance for the research and development of high-performance glassy materials for space application. 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 2025, 45 (3):  9-18.  doi: 10.16708/j.cnki.1000.758X.2025.0034 Abstract ( 291 )   PDF (7961KB) ( 294 )   Save 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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Review of surface environmental characteristics and terrain mechanics of Mars Zhen, LI Xiujuan, ZHANG Rui, ZOU Meng 2025, 45 (3):  19-28.  doi: 10.16708/j.cnki.1000.758X.2025.0035 Abstract ( 88 )   PDF (8582KB) ( 76 )   Save To prevent anomalies during lander touchdown and rover exploration on the Martian surface， and to provide parameter references for the subsequent utilization of in-situ Martian resources and the preparation of simulated Martian soil for ground experiments， this study analyzes the topographical features of Mars， with a particular focus on the physical and mechanical properties of Martian soil. By summarizing images and data obtained from successfully landed missions， this study systematically examines the Martian surface terrain and soil parameters， identifies key environmental characteristics， and compiles the mechanical parameter ranges of Martian soil in the vicinity of landers and rovers. Additionally， the properties and applicability of various simulated Martian soils developed both domestically and internationally are analyzed， and appropriate parameter ranges and selection criteria for simulated Martian soil tailored to lander and rover experiments are proposed. The results indicate that Martian soil is primarily composed of fine-grained particles， with significant amounts of dust， soil clumps， and small rock fragments scattered across the surface， which is often covered by a fragile weathered layer. The upper soil layer is relatively loose， exhibiting mechanical properties similar to sandy soil， making rovers prone to sinking anomalies during exploration， potentially affecting their normal operation. The measured cohesion of Martian soil ranges from 0.10 to 9.0kPa， while the internal friction angle ranges from 18° to 35°. Further analysis suggests that the optimal simulated Martian soil parameters for lander testing are a cohesion of 0.24kPa， an internal friction angle of 35°， and a bulk density of 1.52g/cm3， whereas for rover testing， the suitable parameters are a cohesion of 0.50kPa， an internal friction angle of 18°， and a bulk density of 1.10g/cm3. These findings provide valuable references for future Mars exploration site selection， the development of simulated Martian soil， ground experiments， and the in-situ utilization of Martian resources. Related Articles | Metrics

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Scheme design and in-orbit flight validation for relay communication of sampling and return mission from lunar far-side ZHAO Yang, LI Xiaoguang, TAO Zhuo, SHENG Ruiqing, XU Baobi, HUANG Hao 2025, 45 (3):  29-40.  doi: 10.16708/j.cnki.1000.758X.2025.0036 Abstract ( 74 )   PDF (9529KB) ( 80 )   Save Autonomous sample-return lunar probe has made successful achievements on unmanned and autonomous sampling and return mission from far-side of the Moon for the first time of humankind, under the support of lunar relay satellite. To ensure the probe and relay satellite can smoothly and stably establish a relay link to successfully complete the whole mission, a probe-satellite relay communication link was established in advance after these two targets having been sent into space. Therefore， an all-directional TT&C data transmission link for in-orbit relay communication test is indispensable. The scheme design on lunar probe and lunar relay satellite is summarized. First, the relay communication process is introduced while the principles for relay communication link establishment are concluded by introducing the flight orbit characteristics of both lunar probe and relay satellite. Then a data flow chart for modules of probe in communication with satellite is shown. Besides, a scheme design for relay communication link establishment of probe and satellite is presented, including the selection of relay communication link establishment test arc, allocation for ground TT&C stations, flight attitude design for test, test item design in coverage of overall data flow between facilities in single capsule and between different capsules, and flight procedure design for relay communication link establishment. Finally, inorbit test result is demonstrated, and it is indicated that this designed scheme on relay communication link establishment of probe and satellite satisfied the mission requirements. The compatibility of interfaces between the probe and relay satellite is verified and the correctness is testified via in-orbit test process. Comprehensive factors such as allocation of resources on the ground, flight safety, flight attitude design, flight procedure design, relay communication link design, and data flow design have been taken into account within this scheme. Moreover, through modular design method, it can be flexibly adjusted to accommodate various launching windows and orbital phase changes between the probe and relay satellite, providing a stable foundation for technical knowledge and in-orbit flight experience of relay communication link establishment between complex integrated spacecraft and cooperative relay communication target for follow-up missions in the coming future and is of promising application prospects. Related Articles | Metrics

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Mission analysis and design of Queqiao-2 communication relay payload XU Jin, WANG Qiuping, LI Yao, SUN Ji, CHEN Lan, YU Xiaochuan, WANG Hai, TIAN Sen, DANG Xiaokang, WANG Yongta 2025, 45 (3):  41-55.  doi: 10.16708/j.cnki.1000.758X.2025.0037 Abstract ( 120 )   PDF (12008KB) ( 148 )   Save The Queqiao-2 relay satellite supports the fourth phase of China’s lunar exploration mission to land probes on the Moon. Its primary function is to facilitate communication between lunar surface exploration missions (Chang'e-6, Chang'e-7 and Chang'e-8, etc.) and ground stations, particularly for missions to the Moon’s far side and polar regions. The relay communication payload is one of the most critical and core components of Queqiao-2 relay satellite. The mission features, design and key technologies of Queqiao-2 communication relay payload are analyzed and introduced. A full digital modulation and demodulation function is developed for the forward and return links, considering factors like communication techniques, long-distance transmission, compatibility with multiple lunar probes, and engineering feasibility. This, combined with the ability to update software in orbit, makes the communication relay payload highly flexible and innovative. A key challenge is detecting and tracking multiple targets from high-dynamic signals of the return link. This is addressed by creating a dedicated algorithm to ensure stable communication. Since its launch in March 2024, the communication payload has been operating well in orbit with high reliability, which establishes a leading role in system technical performance around the world. It has provided stable and reliable relay communication for the Chang’e-6 lunar probe for sampling and return mission, successfully completing the world’s first lunar sample return mission from the far side of the Moon. The Queqiao-2 relay satellite's communication payload has played a significant role in China's deep space exploration, generating substantial economic and social benefits. It has laid a solid foundation for future deep space exploration, human spaceflight programs, lunar exploration projects and international cooperation. Related Articles | Metrics

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Progress in electric heating test technology for nuclear thermal rockets core assembly LI Xiaoliang, SHAO Mingxue, CAI Kaiyuan, LI Xiaoduo, WU Xunliang, FENG Songjiang 2025, 45 (3):  56-66.  doi: 10.16708/j.cnki.1000.758X.2025.0038 Abstract ( 35 )   PDF (10790KB) ( 17 )   Save Nuclear-thermal propulsion has been developed in recent years as a key direction for nuclear power in space. The core assembly，as an important part of the nuclear thermal rocket， is very important for the development of the nuclear thermal rocket motor by testing its heat resistance， hydrogen compatibility， and stability of the material structure at higher temperatures. In comparison with some advanced electric heating test technologies carried out abroad， four types of ground simulation facilities designed for the development and testing of core assemblies， namely， ground induction heating， electric arc heating， radio frequency heating， and direct current direct heating， are introduced. Some specific working parameters of different devices for ground simulation experiments are analyzed， and the advantages and disadvantages of each device are compared and analyzed. It is pointed out that ground-based simulations can be carried out to understand the strengths and weaknesses of sample materials and components in terms of thermal stability， structural strength， resistance to hydrothermal corrosion， and irradiation at low cost， and then to select the best materials. The continuous development and improvement of the ground simulation experiment facility will make the development of nuclear thermal rocket core components more accurate and reliable， which is of great significance in promoting the development of China's nuclear thermal rockets and thus realizing nuclear power propulsion in space. Related Articles | Metrics

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Analysis of engineering challenges and solutions for organ-on-a-chip applications in space WEI Yaming, ZOU Jianfeng, HUANG Xiaotao 2025, 45 (3):  67-76.  doi: 10.16708/j.cnki.1000.758X.2025.0039 Abstract ( 34 )   PDF (2950KB) ( 12 )   Save This study systematically analyzes the engineering challenges associated with the application of organ chips in space and proposes corresponding solutions. It begins by reviewing the development of organ chip technology and its potential applications in space. The paper then examines the effects of the space environment, such as microgravity, radiation, and temperature fluctuations, on organ chips. The difficulties related to functional complexity, power consumption, size limitations, long-term stability, the need for standardization and validation are analyzed. Concluding the analysis, the study offers solutions that encompass surface coating and functional modifications, microenvironment control, automated monitoring and control systems, thereby providing an engineering framework for the deployment of organ chips in space. Related Articles | Metrics

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Sealing method for celestial sample orbit transfer based on shape memory alloy LIU Zhengli, LUO Yichen, LIU Zhou, YU Maohua, ZHOU Xue, HONG Haocen, ZHANG Bin 2025, 45 (3):  77-88.  doi: 10.16708/j.cnki.1000.758X.2025.0040 Abstract ( 47 )   PDF (11380KB) ( 14 )   Save This study addresses the sealing challenges in planetary soil sampling. It aims to design a radial compression sealing device using a shape memory alloy (SMA) triggered by temperature changes. The device ensures sample integrity and reduces the need for high axial force, optimizing the sealing process. A microscopic leakage model, based on Roth’s law, is used to evaluate the impact of structural and external factors on leakage rates. Two SMA sheet configurations are analyzed, with simulations showing that the sharp-angle design enhances sealing reliability. The device uses polyimide heating films for resistive heating, achieving sealing by radially compressing the canister. Theoretical leakage rates are predicted, and the energy consumption is assessed through thermal simulations. When the SMA sheet’s diameter deviation from the inner wall is under 0.20mm, the leakage rate reaches 10-6Pa·m3/s. Tests show an average compression stress of 160MPa, with measured leakage rates consistent with predictions. The total energy consumption is 2137.7J, demonstrating the device's high sealing efficiency for orbital sample transfer. The SMA-based device effectively seals without requiring significant axial force. The sharp-angle configuration particularly enhances performance. This device offers a reliable, energy-efficient solution for planetary sample orbit transfer sealing with broad potential applications. Related Articles | Metrics

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Design of continuum robot for space capture YANG Chengxu, ZHAO Zhijun, WANG Yaobing, WANG Jie, WANG Lihua 2025, 45 (3):  89-99.  doi: 10.16708/j.cnki.1000.758X.2025.0041 Abstract ( 117 )   PDF (7877KB) ( 141 )   Save Aiming at the requirement of reliable acquisition of objects of different sizes and shapes in space, a rope-driven continuum robot with “C” type linkage is designed, which can realize the “form-closed” and reliable capture of objects in the absence of some accurate measurement information. The continuum robot can be applied to the acquisition task of targets of different sizes by flexibly increasing or decreasing the number of joints, and has the characteristics of uniform operation capability in all directions. First the “C” type linkage design scheme of continuum robot is introduced, then the flexibility description index based on the Jacobian matrix condition number for the kinematic model of linkage continuum robot is established, and particle swarm optimization algorithm is adopted to optimize the rod length allocation of continuum robot with flexibility as the optimization objective. The results show that the flexibility index of the continuum robot with optimized rod length is 4.6% higher than that of the continuum robot with average rod length. Finally, the simulation results show that with the increase of the flexibility index, the anisodirectional motion ability of continuum robot becomes more similar. It is proved that the flexibility of continuum robot can be improved by using this index as optimization basis. Related Articles | Metrics

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Staring mode attitude control of Geo-SAR satellite with reflector antenna 2025, 45 (3):  100-109.  doi: 10.16708/j.cnki.1000.758X.2025.0042 Abstract ( 41 )   PDF (11864KB) ( 19 )   Save To improve the repeating cycle of Geo-SAR through prompt attitude control method, the staring mode attitude control property and system parameters’ performance of Geo-SAR with reflector antenna are presented. The approach illuminated in this paper aims to shorten the attitude control time, and to improve the revisiting effect. Firstly, Geo-SAR staring mode model and Doppler history are illustrated and compared with those of low earth orbital SAR (Leo-SAR). Its maximum yaw angle to be compensated for broadside imaging is about ±76° when traditional two-dimensional yaw steering (2D-YS) method is used. A new twodimensional pitch and roll squint control (2D-PRSC) algorithm is advanced, which can make satellite continuously stare at any scene in the whole orbital period. The maximum attitude control angle is about ±7.2°, and the capability of satellite is obviously improved. Finally, Geo-SAR fast BP imaging algorithm is illustrated in this paper. The point target with 25m×25m resolution is simulated, the imaging results are good and meet the theory parameters. The simulation results show that the new method in this paper is correct. As the reference scheme for attitude system design, the method can shorten the Geo-SAR attitude control time to about 1/10 of the original value. Related Articles | Metrics

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An optimal control strategy for spacecraft approaching along a designated straight direction LIU Jianghui, PENG Qibo, WU Xinfeng 2025, 45 (3):  110-119.  doi: 10.16708/j.cnki.1000.758X.2025.0043 Abstract ( 42 )   PDF (4900KB) ( 15 )   Save The technology of spacecraft’s space on-orbit service has received increasing attention. The basis of space on-orbit service is spacecraft rendezvous technology, and the essence of spacecraft rendezvous is the approach of the chaser to the target in close range. During the process of approaching the target, the chaser should avoid collisions with accessories such as the solar panel and antenna of the target. In order to ensure the safety of the approximation process, an optimal control strategy for spacecraft approaching along a designated straight direction is proposed. The relative motion model between the two spacecraft with arbitrary eccentricity orbit described by nonlinear TH (Tschauner-Hempel) equation is established. The coordinate system of linear approximation motion is introduced, and the optimal control acceleration of the chaser is derived according to the Hamiltonian equation and the characteristics of linear direction approximation motion. The chaser spacecraft can not only approach the target along a designated straight direction according to the mission requirements, but also ensure the optimal energy. In order to eliminate the interference factors that affect the linear approximation, the proportional differential control law is used to correct the derived control acceleration in the non-linear direction. In order to verify the effectiveness of the proposed control strategy, two sets of scenarios are set up for numerical simulation, which are the linear approximation of the chaser along the velocity direction of the target and the linear approximation along the radial direction of the target. The simulation results show that the proposed control strategy can realize the chaser approaching the target along the designated straight direction, which has good engineering applicability and provides a new idea for improving the success rate and safety of spacecraft space on-orbit service. Related Articles | Metrics

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Identification of center of mass for gravitational wave detection spacecraft based on periodical micro incentives WANG Ziming, LI Ming, YAO Jinming, QI Chaoqun, ZHANG Huibo, ZHANG Hao 2025, 45 (3):  120-130.  doi: 10.16708/j.cnki.1000.758X.2025.0044 Abstract ( 72 )   PDF (6770KB) ( 11 )   Save  Due to the influence of factors such as fuel consumption and structural thermal deformation, the mass distribution of the space-based gravitational wave detection spacecraft will change, and the position of the center of mass will be offset, which will seriously affect the accuracy of gravitational wave detection. Aiming at the demand of high-precision measurement of center of mass for the space-based gravitational wave detection spacecraft, a spacecraft center of mass identification method based on periodical micro incentives is proposed. First, a spacecraft dynamics model that takes into account the effects of nonconservative forces in space, gravity gradient forces and thruster noise is constructed. Then, the research on inertia tensor identification method based on space inertial sensor and star sensor measurement data, and the input method of periodic micro incentives based on thrusters are conducted. A center of mass identification method based on periodical micro incentives and Kalman filter theory is proposed. Finally, simulations under different waves of incentives are carried out. The results show that under the moment of the triangular waveform, the present method is able to achieve high-precision centroid identification with a resolution of 2.14×10-6m during an extremely small angular maneuver of 2.2×10-5rad. This research can reduce the cost of interplanetary link reconstruction and provide a technical approach to maintain the accuracy of spacecraft detection. Related Articles | Metrics

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Aerodynamic function fitting and control matrix computation for atmospheric sail based on GA-BP LIN Ru, LIU Xiaowen, DING Jixin, XU Ming 2025, 45 (3):  131-142.  doi: 10.16708/j.cnki.1000.758X.2025.0045 Abstract ( 29 )   PDF (14367KB) ( 6 )   Save Aiming at the need of low-cost and special formation requirements for space missions, the research focuses on the sailcraft utilizing low orbit aerodynamic drag. The practicability of atmospheric sail technology is ascertained via the model based on towing the imitation kite sailcraft to simulate the low orbit environment. And the aerodynamic torque, generated by the rotation of the distributed sub-sails, is applied to complete the position and attitude control of the sailcraft. The dataset is obtained by aerodynamic simulation of sailcraft with different rotation angles of sub-sails and attitudes of sailcraft, which is subsequently used to train an intelligent model based on Genetic Algorithm-optimized Back Propagation Neural Network (GA-BP). The aerodynamic function network model is derived from the dataset, where the predicted correlation coefficient R2 of each parameter is greater than 0.98 (except for the rolling moment of 0.91). The resulting network model is employed in the mechanical equilibrium equations of the sailcraft, leading to the inverse calculation of the control matrix corresponding to the sub-sail rotation angles and the sailcraft relative positions. The control matrix and the boundaries of the sub-sail angles regulate the safe operation range of the sailcraft, which can provide a reference for the actual control of the atmospheric sailcraft. Related Articles | Metrics

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Blind parameter estimation of hybrid asynchronous frequency hopping signals based on neural networks WANG Ya, YUAN Shuai, LIU Naijin 2025, 45 (3):  143-153.  doi: 10.16708/j.cnki.1000.758X.2025.0046 Abstract ( 21 )   PDF (3927KB) ( 8 )   Save Due to its superior anti-interception and inherent security, the wide application of frequency hopping (FH) signals in satellite communications, satellite measurement and control radio frequency links, satellite navigation systems and Link 16 data link has brought great challenges to space-based electronic reconnaissance. In non-cooperative scenarios, wideband FH communication reconnaissance including FH signal detection, parameter estimation, and network sorting under single-channel reception is challenging. The FH pattern contains the most information about FH signals. So it is the core of FH parameter estimation. Based on the task analysis, this paper proposed a blind prediction framework combining time and power domain features to improve the accuracy and efficiency of FH pattern estimation for mixed signals in the wideband spectrum. First, the spectrogram generated by the short-time Fourier transform (STFT) was used as the input of the signal detection network. The signals were detected on the multi-scale feature maps and then the time-equency (TF) characteristics of FH signals were predicted. After signal detection and localization, the relative power density characteristics were estimated based on the pixels in the signal area. Then the TF and power features were used to identify signal categories and predict the corresponding FH patterns. The unique advantage of this framework is that it requires no prior signal information and anchors but exploits the inherent TF and power properties of asynchronous FH signals. It has a strong generalization ability and can adapt to signals of any shape. The proposed framework can achieve a recognition accuracy of 98.77% for mixed signals with 2 FH signal radiation sources. Experimental results demonstrate the superiority of the proposed framework in fully blind detection, identification, sorting, and parameter estimation of hybrid FH signals. Related Articles | Metrics

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Cooperative tracking of hypersonic vehicle with square root information filter WANG Chenyang, LI Chaoyong, SONG Xun, WANG Linbo 2025, 45 (3):  154-163.  doi: 10.16708/j.cnki.1000.758X.2025.0047 Abstract ( 25 )   PDF (5522KB) ( 8 )   Save In the cooperative hypersonic vehicle (HV) tracking problem,traditional nonlinear filtering algorithms may encounter numerical errors and collapse due to the accumulation of round-off errors when running on embedded systems with limited precision.To track HV more stable and faster,square root filtering was introduced in cubature rule-embedded information consensus filter (Cub-ICF),and the equivalent square root form was derived.This ensured the positive definiteness and symmetry of the covariance during the filtering process.On the basis of finite-time consensus algorithm,a finite-time consensus square root cubature information filter (FC-SRCIF) which combined the numerical robustness and convergence rate was designed.Simulation results demonstrate that FC-SRCIF outperforms existing cooperative tracking algorithms for both non-maneuvering and maneuvering targets.Particularly,for maneuvering target tracking,FC-SRCIF exhibits a 41.9% and 37.1% higher tracking accuracy in position and velocity compared to Cub-ICF,respectively,while also improving the convergence rate.These findings validate the unique advantages of FC-SRCIF in addressing the cooperative tracking problem of HV. Related Articles | Metrics

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SS-Minnaert: an improved vegetation topographic correction method LYU Yue, LI Dacheng, XU Zhaopeng, YANG Yi, HU Zhiheng 2025, 45 (3):  164-174.  doi: 10.16708/j.cnki.1000.758X.2025.0048 Abstract ( 22 )   PDF (9078KB) ( 6 )   Save Terrain effects cause significant deviations to the surface reflectance of remote sensing data, especially in the scenario of large solar zenith angle and significant surface heterogeneity. The traditional terrain correction methods frequently fall short in fully compensating for the scattering effects induced by uneven terrain. To address the inadequacy of terrain correction methods in instances of intense surface scattering, the SS-Minnaert model, a terrain correction approach that accounts for solar zenith angle and surface heterogeneity, is developed in response to a detailed analysis of terrain-induced errors in vegetated regions. The model's accuracy is validated using reflectance simulations from the three-dimensional discrete anisotropic radiative transfer (DART) model. The results indicate that the SS-Minnaert model reduces RMSE by 0.036 to 0.092 in the green, red, and near-infrared bands for solar zenith angles greater than 40°, and by 0.004 to 0.031 for angles less than 40°. Further quantitative analysis demonstrates the SS-Minnaert model's superior performance in terrain correction over mainstream models at solar zenith angles beyond 40°. For solar zenith angles below 40°, the SS-Minnaert model exhibits comparable topographic correction proficiency to established VECA and Teillet models in the near-infrared band. In the red and green bands, the performance is even better. In summary, the SS-Minnaert model markedly enhances the Minnaert model by integrating the dual influences of solar zenith angle and surface heterogeneity, demonstrating a terrain correction effect superior across multiple bands, particularly at high solar zenith angles where the improvement is notably significant.  Related Articles | Metrics

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Conception on the habitability exploration mission of the icy moon CHEN Xiao, LI Kui, HAO Jihua, CHEN Gang, DU Yang, PANG Fuchuan, LI Dongyu, LI Haiyang 2025, 45 (3):  175-184.  doi: 10.16708/j.cnki.1000.758X.2025.0049 Abstract ( 149 )   PDF (3615KB) ( 142 )   Save The exploration of liquid oceans beneath the icy crusts of icy moons and the investigation of their habitability provide critical clues for understanding the origin and evolution of the solar system， the emergence of life， and the search for extraterrestrial life. This field has become one of the most prominent frontiers in international deep space exploration. Based on a comprehensive review of domestic and international icy moon exploration missions and their key achievements， current development trends are analyzed， the scientific objectives and detection methodologies for icy moon exploration are summarized， and a novel multi-mode exploration concept is proposed combining orbital reconnaissance， surface landing， and deep drilling. Focusing on Enceladus as a primary target， the mission aims to investigate its gravitational field， thermal profile， magnetic environment， potential seismic activity， and geochemical characteristics through mass spectrometry， chromatography， spectroscopy， and biological detection. Concurrently， it will collect natural samples to analyze elemental and isotopic compositions， thereby advancing our understanding of Enceladus' habitability.  Critical technologies requiring breakthroughs are further identified， including next-generation detection payloads and high-precision analysis of biogenic elements. The implementation of such icy moon exploration missions will significantly enhance China's technological capabilities in deep space exploration and strengthen its leadership in planetary science. Related Articles | Metrics

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New thermal control technology for jovian mission LI Jinyue, SU Ruobin, YANG Jin, DUAN Xiaowen, HE Chunli, LU Xi, NIU Junpo 2025, 45 (3):  185-191.  doi: 10.16708/j.cnki.1000.758X.2025.0050 Abstract ( 40 )   PDF (7091KB) ( 16 )   Save Usually the Jovian probe uses Venus-Earth-Earth gravity-assist mission sequences to achieve Earth-Jupiter transfer. due to a wide range of changes in the daily distance caused by large-scale changes in solar light intensity， which in turn leads to the drastic temperature variation of the probe's external thermal control components， which not only needs to adapt to the high solar heat flow of up to about 2，938W/m2 near Venus， but also needs to adapt to the low solar heat flow of 50W/m2 near Jupiter， which poses a challenge to the extreme high and low temperature adaptability of the thermal control design. Currently， the traditional approach mainly adopts thermal control measures such as fluid loops， shutters and multi-layer components to control temperature， which increases the complexity and design difficulty of the thermal control system. In this paper， we proposed a new type of thermal control design method We used a three-dimensional heat-insulating solar panel to orbstruct the sunlight， and adopted a closed-loop decoupling control algorithm to regulate the positional relationship between the solar wing and the star body. By deminishing the solar thermal radiation to the detector's external surface of the stand-alone device and maintaining a fixed heat-sinking surface， the temperature fluctuation of the detector is reduced. Through simulation analysis， it has been shown that when the solar panel is positioned 1.5 meters away from the star body， the heat dissipation capacity at the shaded area can reach 170W/m2， suitable for blocking high solar heat flux near Venus. When the solar panel is positioned 0.5 meters away from the star body， the heat dissipation capacity decreases to 50W/m2， providing insulation and reducing heat loss at the heat-sinking surface near Jupiter. Our design has the advantages of simple thermal control design and high adaptability， and provides a new idea for the thermal control design of the subsequent deep space detectors. Related Articles | Metrics