The exploration and study of water ice in the lunar polar regions are of great significance for understanding the origin and evolution of water and volatiles on the Moon, as well as for realizing in situ resource utilization for space exploration. In recent years, the detection of water ice in these regions has become a strategic priority in the competition among major countries, including the United States, China, and Russia, in the fields of lunar and deep space exploration. One of the primary scientific tasks for the Chang'E-7 (CE-7) lunar exploration mission is to detect and investigate water ice at the lunar south pole. In this work, the progress in the exploration and study of water ice in the lunar polar regions is summarized. The unresolved key scientific questions related to polar water ice are presented. Furthermore, the basic information and especially the scientific objectives about water ice detection of CE-7 mission are introduced. The remote sensing and in situ detection methods of water ice at the south pole are discussed based on the scientific payloads onboard the orbiter, rover, and mini-flying probe in the CE-7 mission.

The exploration and utilization of lunar water and ice resources have become the core proposition supporting sustainable human extraterrestrial presence. This article analyzes the occurrence characteristics and remote sensing evidence of lunar soil water ice, sorts out the current status of technological development and utilization of lunar soil water ice, and highlights the difficulties and challenges of exploration and utilization technology. Based on the design criteria for the exploitation of lunar soil water and ice resources, this paper elaborates on four fundamental engineering issues related to the utilization of water and ice resources, and provides corresponding conceptual plans and key technologies. The research results of this article can provide reference for the development and utilization of water ice resources in China.

Lunar polar water ice resources are critical for future lunar exploration, serving as essential life-support materials and propellant feedstock. In-situ water ice extraction technologies have become a strategic focus among leading space nations. To address the demand for efficient mining of water ice resources in permanently shadowed regions at lunar poles, this study proposes a multi-needle thermal extraction system design. This paper elaborates on the system architecture and functional characteristics, while numerical simulations investigate the effects of needle parameters and spatial distribution on water ice sublimation rates, validating the proposed approach. These research findings will provide significant technical support for in-situ resource utilization and lunar base construction.

The extraction and utilization of water resources in the permanent shadowed regions of the lunar polar regions is one of the key tasks for future lunar base construction. This study analyzed the formation mechanism and environment of frozen soils on the Moon, compared the preparation methods and tested the characterization of lunar soil simulants with temperatures below −180 ℃, analyzed the advantages and disadvantages of different collection and water extraction methods for frozen soils in the permanent shadow regions, proposed a water resource extraction system and key technologies suitable for future in-orbit verification, so as to provide technical references for future extraterrestrial water resource extraction tasks.

Substantial evidence indicates that the Permanently Shadowed Regions (PSRs) at the lunar poles may harbor considerable water-ice resources mixed with lunar regolith. Understanding the mechanical and thermal properties of icy regolith is a prerequisite for elucidating the evolutionary mechanisms and exploitation strategies of lunar water-ice, and these key properties are closely related to the occurrence forms of water-ice within the porous regolith medium. Specifically, does water-ice exist as dispersed small particles (frost) within the regolith pores, or has it undergone ripening and coarsening, forming large crystals comparable in size to regolith grains? Currently, there is neither direct observational evidence nor theoretical research addressing this question. This knowledge gap also hinders the rational preparation of icy lunar regolith simulants. In this study, we derive a theoretical model of Ostwald ripening under rarefied conditions, demonstrating that clusters of small water-ice particles (frost) within lunar regolith pores will undergo material migration and locally aggregate into large crystals over geological timescales. We quantitatively investigate the ripening rates of water-ice particle clusters under different temperature conditions. The theoretical results indicate that water-ice on the surface of ultra-low temperature PSRs region (<100 K) can retain its initial deposition morphology for extended periods, whereas in warmer non-PSRs or subsurface regions (>120 K), water-ice particle clusters will undergo significant coarsening, forming large crystals comparable in size to regolith grains. Based on these findings, we can prepare lunar regolith simulants with water-ice particle sizes matching those of target icy regolith by adjusting temperature and ripening time. This study not only advances the theoretical understanding of lunar water-ice evolution mechanisms but also provides a critical theoretical foundation for research on the physical properties of icy regolith and the preparation of simulants, offering significant application value for the exploitation and utilization of lunar water-ice resources.

On May 29, 2025, China successfully launched the Tianwen-2 spacecraft to conduct a sample-return mission, targeting the near-Earth asteroid (469219) Kamoʻoalewa. Here, we systematically review early works on Kamoʻoalewa from various research teams, synthesizing reported results on its orbital characteristics, dynamical origin, composition, spectral type, size, rotation period, axis orientation, global regolith particle size distribution, regolith thickness, potential evolutionary history, and key scientific questions. We also predict space weathering features of future returned samples.

Significant water ice deposits are present in the permanently shadowed regions of the lunar poles, and the extraction of these water ice resources holds great scientific and practical value. This paper proposes a water ice extraction method using a thermal drill based on eddy current induction heating. The method involves drilling a high thermal conductivity drill bit into deep lunar regolith, heating the regolith externally via an induction coil, and transferring heat to the subsurface to evaporate water ice for extraction. To verify the feasibility of this approach, simulations were conducted on key parameters affecting the thermal drilling performance. Additionally, an experimental platform for induction heating of the thermal probe was established, and vacuum-environment heating tests with an empty drill bit were performed. The results demonstrate that this method can effectively transfer heat into the lunar regolith interior. This research provides technical groundwork for China's future extraction of water ice resources from lunar regolith.

Under the constraints of the extreme environment in the lunar polar regions and the low thermal conductivity of lunar soil particles, extracting water resources from icy lunar regolith faces significant technical challenges. This study established a microwave heating experimental system to investigate the technical methods for water resource extraction and collection from icy lunar regolith. Low-temperature Lunar Regolith Simulant (LRS) were prepared, and experimental tests were conducted to obtain the fundamental characteristics of water extraction and collection processes from microwave-heated icy LRS. The effects of microwave heating parameters and sample properties on water extraction efficiency were analyzed. Results indicate that microwaves can penetrate the entire LRS, enabling nearly uniform heating. The energy efficiency of microwave heating typically ranges between 2.5~6.0 W·h/g. Water extraction rate shows a positive correlation with total microwave energy input, and optimal ice-water extraction efficiency can be achieved by adjusting microwave power, heating temperature, and constant-temperature heating duration. Increased sample compaction enhances thermal conduction between water molecules and soil particles, reducing total energy input while improving water extraction rate. The average water collection rate in this system ranges from 0.53~1.59 g/min, increasing with the initial water content. This study provides a new route map for water exploitation in the lunar polar regions.

This study aims to address the technical complexity associated with the low collection efficiency of water vapor during the in situ heat extraction of water ice in the lunar polar region. To this end, the study analyzes the influencing factors based on the heat and mass transfer characteristics of the frost layer porous medium. This is achieved through the kinetic model of the phase transition of the water vapor and the growth model of the condensing frost layer. The study's findings provide a theoretical foundation for the optimization of the condenser. A comparison and analysis must be conducted of the relationship between the particle size of aluminum beads and the water vapor flow rate through water vapor flow simulation. A validation platform has been configured to replicate the extreme environment on the Lunar surface. This platform will be utilized to conduct comparative tests on the water vapor condensation collection efficiency of aluminum bead structures with varying particle sizes. The findings indicate that the flow rate of water vapor within the condenser is directly proportional to the diameter of aluminum beads. A decrease in diameter results in a reduction in flow rate, thereby extending the heat exchange time between water vapor and the condenser. The correlation between the internal surface area of the water vapor condenser and its water vapor collection efficiency is positive. The utilization of aluminum beads with a small particle size can lead to a substantial enhancement in the internal surface area. However, the adoption of such aluminum beads is hindered by the potential for pore blockage, which can be caused by the aforementioned small particle size. The study offers a theoretical and experimental foundation for the design of a water vapor collection unit as part of an in-situ Lunar water ice resource extraction device.

Lunar water ice is a critical resource for the construction of future lunar bases. However, constrained by the extreme environment of permanently shadowed regions, traditional drilling methods struggle to achieve low-power, low-drilling-pressure, and fidelity-preserving drilling. In this paper, an ultrasonic sampler suitable for drilling in lunar water ice frozen soil is designed and fabricated. The vibration mode of the ultrasonic horn is designed using finite element simulation software, and the actual output performance of the horn is verified. Simulated lunar regolith permafrost with a 10.0% water content is prepared, and its uniaxial compressive strength is measured to be 41 MPa. The discrete element simulation software PFC is used to simulate the mechanical properties of lunar water ice frozen soil, and the constitutive parameters are established. The drilling performance is evaluated through simulated drilling experiments on lunar regolith permafrost. The results show that under the same feed rate, the average drilling force is reduced by 52.0% when ultrasonic driving is applied, with a deviation of 10.5% from the simulation results.

As deep space exploration missions progress, the extraction and utilization of in-situ lunar water ice resources will be crucial for the establishment of lunar bases and the sustainability of human presence. Microwave heating extraction, as an efficient and rapid extraction technology, has a broad application prospect. In this paper, for the microwave heating extraction process of lunar water ice, an electromagnetics model and a heat transfer model are constructed by decoupling the electromagnetic field from other physical processes. The extraction process under different power inputs is numerically simulated by using the finite element software COMSOL Multiphysics. The results show that: the maximum depth of microwave heating is basically the same as the depth of microwave penetration, and the effective heating range is the area where the modal value of the electric field strength is higher than 1/e times of the surface value; the quality of the extracted water ice is basically positively correlated with the input power of microwave, but the efficiency of the extraction decreases due to the influence of heat conduction in the low-power case; up to 1717.4 g of water ice can be extracted at a power input of 2000 W, which increases the extraction volume by 10 times compared to the conventional heating rod extraction method under the same conditions.

Scientific data and extraterrestrial samples are core outcomes of deep space exploration activities and have irreplaceable research value. International cooperation centered on the sharing of scientific data and extraterrestrial samples has become a common practice in international cooperation for deep space exploration missions. With the rapid growth of deep space exploration missions, relevant technology has been continuously enriched, and related rules are gradually formulated. This paper analyzes existing international space laws and relevant rules, studies the policies and practices of sharing scientific data and samples in deep space exploration of major space faring countries around the world, and puts forward some suggestions for China's related work.

As a unique type of celestial body, asteroids possess significant scientific research value and resource development potential, while also posing potential extraterrestrial impact threats, which have important implications for human civilization and planetary safety. The distribution characteristics of boulders on the surface of asteroids are crucial for understanding their formation, evolution, and physical properties. However, due to the small size, large quantity, and low quality of images of asteroid surface boulders, traditional methods face challenges in accurate statistical analysis. To address these issues, this study introduces an instance segmentation algorithm based on YOLOv8 to improve the detection and segmentation performance for asteroid surface boulders, especially by enhancing the model's ability to detect small-scale boulders through the addition of a small-object detection head. Furthermore, the Slicing Aided Hyper Inference (SAHI) framework is integrated to perform slice-based inference on high-resolution images, thereby enhancing both inference efficiency and segmentation accuracy on large-scale images. Subsequently, geometric analysis techniques, such as ellipse fitting, are employed to extract spatial location, size, and orientation information of boulders from the segmentation results. Finally, the proposed method is applied to the analysis of boulder distribution on the surface of asteroid Bennu. The results indicate that the surface boulders exhibit certain spatial distribution patterns, demonstrating the effectiveness and applicability of the proposed approach in practical planetary image processing tasks.

Three-dimensional (3D) models of small celestial bodies are crucial for revealing their morphology, dimensions, and surface characteristics, providing essential dataset for both exploration tasks and scientific research. Current high-resolution modeling relies on close-range observation by space probes, with traditional techniques such as stereo photogrammetry and photoclinometry (or shape from shading) being widely used. While stereo photogrammetry reconstructs 3D geometry depending on surface texture quality captured on the stereo images, photoclinometric methods exploit pixel-wise brightness to recover fine topographic details. This paper presents a synergistic pixel-wise reconstruction method that integrates stereo photogrammetry and photoclinometric optimization. The method includes three key steps: Firstly, a relatively low-resolution 3D model is constructed using stereo photogrammetry. Secondly, the global model is partitioned into localized regions for iterative photogrammetric refinement. Finally, optimized local regions are merged into a global model of higher resolution and accuracy. Validation experiments conducted using images of a 3D-printed model of asteroid Bennu within an indoor test site revealed that the proposed method can achieve high geometric accuracy and reconstruct subtle terrain features. This integrated method enables high-fidelity modeling of small celestial bodies, supporting the Tianwen-2 mission and related scientific research.

The spin-axis orientation and shape parameters of near-Earth asteroids are critical reference information for studying their formation and evolutionary history, as well as for conducting in-situ space exploration. With the continuous advancements in time-domain astronomy and deep-space exploration technologies in China, an increasing number of universities and research institutions are actively constructing observational facilities which can support near-Earth asteroid observation and research. In this study, a sun-Earth-asteroid physical and dynamical model was established, considering near-Earth asteroids with different triaxial ellipsoid shapes. Simulated light curve data were utilized to investigate the parameter space necessary for inverting the spin-axis orientation and shape of asteroids. Periodograms were extracted from the light curves using the Lomb-Scargle and phase dispersion minimization methods, and a global fitting procedure for asteroid inversion parameters was developed. The results show that with a photometric accuracy of 0.001, 4~6 light curves covering 10° of solar phase angle are sufficient for inversion. For a photometric accuracy of 0.010, 8~10 light curves covering 20° of solar phase angle are required. At a lower photometric accuracy of 0.100, continuous observations covering multiple full rotation periods are recommended initially, followed by sparse observations to extend the solar phase angle for further confirmation of the inversion results. Additionally, for asteroids with nearly equal short axes, the required solar phase angle range can be moderately relaxed. This study provides a reference for the inversion of near-Earth asteroids using light curve data and offers methodological guidance with China’s existing and upcoming ground-based and space telescopes.

Ground-based planetary radar can obtain the physical characterizations including precision orbit, rotation, topography of the asteroids by transmitting electromagnetic signals actively and receiving the echo signals from asteroids, it is crucial for near-Earth asteroids defense and planetary science. The research of ground based planetary radar is currently focused on Deep Space Array Planetary Radar (DSAPR). An overview of the development of DSAPR technology is presented in this paper, and the current status and trends of array radar technology is reviewed, including the Goldstone uplink array radar, Ka Band Array Radar for Near-Earth Objects Accurate Characterization, Deep space Advanced Radar Capability, China Compound Eye and downlink array technology. The state of the antenna array at Kashi Deep Space Station is introduced, and the technical advantages of the deep space array planetary radar based on the multi-antenna of the Kashi Deep Space Station are analyzed. Finally, the detection capability of the 4×35 m and 20×35 m DSAPR formed by the expansion of the Kashi Deep Space Station antenna array is analyzed.

The Tianwen-2 mission will investigate the internal structure of the near-Earth asteroid 2016 HO₃ with a monostatic radar system. In preparation for the processing of monostatic radar data, this study proposes a three-dimensional (3D) Full-Waveform Inversion (FWI) method for reconstructing the internal structure of asteroids using monostatic radar data. We first validate the feasibility and effectiveness of the proposed method using a 3D two-layered onion-shell asteroid model. Subsequently, we systematically examine the influence of three key parameters of radar acquisition geometry (including the number of orbits, the number of radar measurement points, and the spacing of adjacent orbits) on the FWI performances. Our analysis demonstrates that reliable reconstruction can be achieved when the acquisition geometry comprises 3 orbits with an inter-orbit spacing of 25~35 m and at least 20 measurement points per orbit. This study not only provides a high-accuracy inversion methodology for the processing of monostatic radar data, but also offers scientific guidance for designing radar acquisition geometry in the ongoing Tianwen-2 mission.

The enantiomers of chiral drugs have different physiological activities, and the external environment may lead to the racemization of a single enantiomer, which may result in the weakening or even loss of its biological activity. Although NASA and other organizations have studied the effect of space radiation on drug stability, the studies on the stability of chiral drugs are still limited. Flavonoids, as active chiral components of traditional Chinese medicine that are homologous to food and medicine, have potential space applications for the prevention and treatment of diseases. Therefore, in this study, chiral compounds of flavonoids were carried by manned spacecrafts and returned satellites, and chiral liquid chromatography analysis was utilized to investigate their chiral stability in the space environment. The experimental results showed that some of the flavonoid chiral compounds were stable in the space environment for up to one year of storage due to the substituent group types and stereochemical structure differences, while hesperidin and flagellin underwent different degrees of chemical degradation or chiral changes. The study in this paper provides a theoretical basis for the stability and structural protection of chiral drugs, as well as data support for the study of astronauts’ food and drug health in space.

This paper focuses on China’s first asteroid exploration mission. In accordance with the single-unit functional requirements of the payload management unit for the Tianwen-2 probe, it introduces the unit’s composition design, operating modes, and single-unit functions. This device ensures the power supply and distribution safety of the subsystem through designs such as power fault isolation. It enhances the system’s fault tolerance capability by means of on-orbit updatable and customizable status monitoring, fault recovery processing, and other measures. Relying on autonomous detection, it achieves precise mission switching and autonomous mission planning. Moreover, through data management designs like joint detection and scientific data preprocessing, it improves the efficiency of scientific detection. Ultimately, it enhances the reliability of the payload system, realizes integration, autonomy, and high efficiency, and lays a technical foundation for the design of payload systems in China’s subsequent deep-space exploration missions.

Deep space probes typically operate at vast distances from Earth, leading to prolonged communication delays and significantly reduced real-time monitoring and control capabilities. In many cases, telemetry data cannot be downlinked or can only be transmitted at extremely low rates. Therefore, deep space probes must possess autonomous fault diagnosis and long-term operational capabilities to reduce dependence on ground-based telemetry analysis. Under limited downlink conditions, it is essential for probes to transmit critical health status information in a timely manner to support ground-based flight control. Considering that the onboard computer system of deep space probes adopts a hybrid centralized-distributed architecture, this paper proposes a hierarchical approach to fault diagnosis and recovery at the module level, device level, and system level. This multi-level strategy enables multi-dimensional fault detection, which reduces the probability of missed or incorrect diagnoses. It also facilitates collaborative fault diagnosis and recovery among multiple subsystems, maximizing the utilization of onboard resources. This work lays a foundational methodology for future research and development in fault diagnosis and recovery for deep space onboard computer systems.

This study investigates dust eruption dynamics in the near-nucleus region of icy small bodies. To resolve the computational limitations of existing models, we extend Fink et al.'s (2021) one-dimensional simplified framework into three dimensions, simultaneously incorporating nucleus rotation effects (centrifugal/Coriolis forces) and eruption scales (global vs. local). Our approach establishes unified 3D dynamical models for both globally distributed dust-gas eruptions and localized eruptions with constrained source areas. Through numerical simulations parameterized with comet 67P/Churyumov-Gerasimenko's physical properties, we quantitatively examine dust particle lifting thresholds, trajectory evolution, and landing distribution patterns. Simulation results reveal that: (1) the critical lifting radius of dust particles decreases with increasing latitude; (2) the particle size profoundly influences their trajectories and ultimate dynamic behavior; (3) due to the nucleus rotation, a notable systematic north-south offset appears in dust landing points during global eruptions, while this offset is weaker in localized eruptions due to the constrained source scale. These results provide a theoretical foundation for predicting dust environment evolution around icy small bodies and assessing impact hazards for deep-space exploration missions.

Aiming at the short-term hazard assessment requirement of the satellite breakup event in constellation, a short-term hazard assessment algorithm of fragmented debris cloud based on boundary value problem is proposed. The spread velocity of the debris is obtained by solving the two-point boundary value problem, and the joint probability distribution density function of spread velocity and characteristic size is derived by using of the CSBM model. On this basis, the mathematical representation of collision risk of debris cloud with specific size is obtained. The algorithm is applied to the short-term hazard assessment of constellation satellite breakup scene. The results show that the impact risk of debris cloud is highly concentrated on coplanar satellites and some out-of-plane satellites intersecting with them at high speed. This kind of satellite has high collision risk when periodically crossing debris cloud and reaches the maximum at the first crossing. The collision risk of other satellites gradually accumulates with the spread of debris cloud, but the risk is lower. The proposed algorithm and related conclusions can provide support for short-term hazard assessment of breakup events

A trajectory planning algorithm combining Radau pseudospectral method and convex optimization method is proposed for the problem of small celestial body landing trajectory planning. The pseudospectral method uses non-uniform nodes and Lagrangian difference polynomials to approximate variables, providing a discretization method for continuous time Non-Linear Programming (NLP) problems. By constructing and convexifying the optimal control problem for segmented small celestial body landing trajectory planning, and discretizing the obtained convex optimization problem for small celestial body landing trajectory planning by the Radau pseudospectral method, a pseudo-spectral sequence convex optimization solution method for small celestial body landing trajectory planning with segmented state constraints is proposed. This method can simultaneously obtain the exponential convergence of Radau pseudospectral method and the fast solving speed of convex optimization method, and has high solving accuracy. Through simulation verification, the feasibility and effectiveness of the algorithm in autonomous landing of small celestial bodies have been demonstrated.

Studying the exposure age of asteroids is crucial for understanding their formation and evolution. The implementation of the Double Asteroid Redirection Test (DART) mission demonstrated the feasibility of using kinetic impact to deflect the trajectory of a near-Earth asteroid and also provided a valuable opportunity to investigate the exposure age and evolutionary processes of Didymos. This study investigates the exposure age of the surface of the primary asteroid Didymos and the ejecta of the secondary asteroid Dimorphos, based on visible and near-infrared spectral data obtained by ground-based telescopes before and after the DART impact. It shows that the exposure age of Didymos surface is approximately 457 thousand years, implying that the primary asteroid experienced a significant rotational fission event about 457 thousand years ago. This event had almost no effect on the surface age of the primary asteroid but reset the surface age of the secondary asteroid and the exposure age of the primary asteroid. The ejecta of Dimorphos share the same composition as the surface of Didymos but exhibit a lower degree of space weathering, suggesting that after the formation of the secondary, the surfaces of both the primary and the secondary underwent intense space weathering, while the material from the interior of the secondary was relatively less affected.

Against the backdrop of the rapid development of global low-orbit constellations, highly efficient and reliable propulsion technology has become key to large-scale deployment. Electric propulsion systems are the preferred choice due to advantages such as high specific impulse and low cost. Among them, the permanent magnet Hall thruster, characterized by its zero quiescent power consumption, high reliability, and compact structure, is emerging as the mainstream technological approach for low-to-medium power applications. This paper systematically compares the characteristics of both permanent magnet and electromagnetic excitation technical schemes, with a focus on the performance evaluation of a magnet Hall thrusters batch-applied for the first time in a major domestic constellation, based on ground and in-orbit data. Analysis of long-term telemetry data indicates stable thruster operation and good consistency in key parameters, successfully fulfilling orbital control tasks and verifying its long-term reliability in the actual space environment. This study provides substantial data support and engineering reference for the selection and design of propulsion systems in subsequent Chinese low-orbit constellations.

With the rapid development of space exploration, higher requirements have been put forward for aerospace equipment, functionality and serviceability of aerospace materials turn out to be increasingly significant. Therefore, high-performance fiber materials have been widely applied in the aerospace field due to their superior mechanical properties, lightweight characteristics, and weaveability. In recent years, researchers worldwide have conducted extensive studies on the preparation processes and intrinsic structures of aerospace fiber materials, and have carried out frontier explorations in areas such as mechanical reinforcement, space environment resistance and ultra-high temperature resistance. This paper systematically summarizes the currently widely used prevalent organic and inorganic high-performance fiber materials from the perspectives of structures, performance, and application. It particularly highlights cutting-edge technologies, material characteristics, and preparation methods of advanced textile materials in the aerospace field, as well as their application advantages in various aerospace sectors. Additionally, it outlines future development directions and application prospects of novel fiber materials in space technology, aiming to provide new insights for advancing aerospace fiber material research.

As a high-performance thermosetting resin, cyanate ester resin demonstrates significant application potential in the fields such as aerospace, electronic packaging, and radar communications, owing to its unique chemical structure and excellent comprehensive properties. In recent years, modification of cyanate ester resin to further enhance its thermal stability, mechanical properties, and processability while reducing costs has become a research hotspot in the field of polymer and composite materials. This paper aims to review the latest research progress on modification methods for cyanate ester resins. By exploring the effects of various modification methods on the properties of cyanate ester resins and their respective advantages and disadvantages, it seeks to provide methodological references for developing cyanate ester resins suitable for space environmental applications and to support the broadening of their applications.

Zirconia (ZrO₂) ceramic fibers have been widely used in various fields due to their advantages of high-temperature resistance, low thermal conductivity, and good chemical stability. This paper reviews the research progress of ZrO₂ fibers in recent years, including stabilization strategies, preparation methods, and applications. First, the stabilizers and stabilization mechanism of ZrO₂ fibers are introduced briefly. Then, various preparation methods for ZrO₂ fibers are discussed, including electrospinning, solution blow spinning, centrifugal spinning, template method, and dry spinning. After that, the applications of ZrO₂ fibers in thermal insulation, air filtration, and water treatment are introduced in detail. Finally, the preparation and application prospects of ZrO₂ fibers are prospected.

Under extreme service conditions involving long-term high temperatures, thermo-mechanical cycling, and concurrent oxidation/corrosion, the design of aerospace structural alloys is simultaneously constrained by the exponentially expanding compositional space, the scarcity and high cost of high-fidelity property labels, and the limited transferability of strongly coupled multi-scale mechanisms. Along the “composition–process–microstructure–property–service” chain, a materials intelligent design paradigm is constructed with physics-based constraints at its core: multi-modal and multi-fidelity data are standardized, aligned across domains, and stored in a unified database; conservation laws, crystallographic symmetry, and phase-diagram consistency are embedded into classical machine learning models, convolutional neural networks, graph neural networks, and Transformer/pre-trained architectures; microstructural intermediates such as segmented phase maps and size distributions are explicitly introduced to strengthen the mapping among processing, microstructure, and properties; and uncertainty quantification, domain adaptation, and out-of-distribution detection are employed to control the risk associated with model extrapolation. At the decision-making level, generative design and multi-objective Bayesian optimization are incorporated to form a closed-loop “generation–screening–validation–update” workflow. For γ–γ′-strengthened Ni/Co-based superalloys, L1₂-strengthened heat-resistant/high-temperature Al alloys, and multi-principal/high-entropy alloys, multi-objective trade-offs are performed with respect to γ′ volume fraction and solvus temperature versus lattice misfit, precipitation and coarsening kinetics versus the synergy between thermal conductivity and strength, and sublattice occupancy versus long-range order. Overall, this physics-informed intelligent framework enables robust extrapolation that balances performance and confidence under small-sample, cross-domain, and multi-modal data conditions, and provides a unified feature space and evaluation criterion for the continuous iteration of long-life high-temperature alloys.

Aerospace primary load-bearing components require structural materials that are lightweight and offer high specific stiffness, high specific strength, excellent wear resistance and good environmental adaptability, which poses a considerable challenge to conventional metals/alloys. In this work, SiCp/2024Al composites with dual-heterogeneous architecture were fabricated based on powder metallurgy route. By planetary ball milling, mechanically mixing, hot consolidation and extrusion, laminated bimodal grained Al matrix was inherited from the processed powder mixtures, integrated with micron and nano SiCp with deliberate spatial distribution. The dual-heterogeneous SiCp/2024Al composites exhibit outstanding comprehensive mechanical properties: elastic modulus >95.0 GPa, yield strength of 696.5 MPa, tensile strength of 792.1 MPa and elongation of 5.9%, maintaining comparable tensile strength while achieving a 136.0% increase in elongation, with only a 10.3% reduction in yield strength, compared with uniform ultrafine-grained counterparts reinforced solely with micron SiC particles. The superior strength is attributed to grain boundary strengthening and insufficient mobile dislocations, whereas the excellent strength-ductility synergy originates from hetero-deformation induced hardening and enhanced dislocation accumulation due to intragranular nano-precipitates. This study provides valuable insights for the toughness-strength balanced design and scalable production of lightweight Al matrix composites for aerospace load-bearing applications.

As deep space exploration missions progress and lunar base construction advances, in-situ lunar water ice extraction technologies have become pivotal for achieving resource self-sufficiency, reducing transportation costs, and supporting long-term lunar habitation. The permanently shadowed regions at the lunar poles are considered the most promising areas for water ice accumulation. However, the efficient extraction of water ice remains a significant challenge due to factors such as the extremely low thermal conductivity of lunar regolith, sublimation losses in the vacuum environment, and the formation of insulating layers. This paper provides a comprehensive review of the physical mechanisms governing the sublimation behavior of lunar water ice and the associated experimental simulation techniques. It also outlines the current state of in-situ heating extraction methods, including insertion heating, microwave heating, and solar heating, while highlighting the research progress and application potential of these approaches. A particular focus is placed on the impact of sublimation delay effects on extraction efficiency, with discussions on low-temperature isothermal heating strategies, the coupling of ice grain size with thermal field models, and the optimization of equipment layout. Based on this review, the paper offers insights into the future development trends of in-situ resource utilization systems for the Moon and emphasizes the need for enhanced coupling models of sublimation behavior with the actual properties of lunar regolith, as well as validation through ground-based environmental simulation experiments. These efforts are essential for advancing water ice extraction technologies toward greater efficiency and sustainability.

Asteroid monitoring technology forms a cornerstone in the effort to foster a community with a shared future for mankind against asteroid threats. Conducting in-depth research on near-Earth asteroid (NEA) monitoring technologies is essential not only for safeguarding human development and survival but also for establishing independent decision-making authority in critical global security events and assuming a voice and leadership role in international space affairs. This paper offers a comprehensive analysis of the hardware components, detection objectives, mission scenarios, operating modes, scientific contributions, technical characteristics, and highlight features of major foreign ground-based and space-based monitoring systems. Based on this assessment, it identifies future development trends in asteroid monitoring. Additionally, in light of the current state of development in this field in China, the paper provides systematic recommendations focusing on top-level design, technological layout, scientific development, mission execution, and international cooperation. These recommendations aim to serve as a reference for China’s effort to address NEA impact risks and enhance its NEA monitoring capabilities.

The pulsed laser has been proven to be a powerful tool for studying single event effects. In practical applications, laser test results must be correlated with high-energy particles to achieve accurate predictions of spatial SEE rates. Currently, most laser-high energy particle correlation methods are based on charge collection 3-D rectangular-parallel-piped or nested Parallelepiped models. These models still need to introduce the effect of ionization track differences. By adjusting the defocusing distance of the laser, an ionization track with varying feature sizes was obtained at different depths of the bipolar device operational amplifier LM324. The charge collection produced by the laser with different characteristic ionization tracks was compared, and the influencing factors and the action mechanism were analyzed. The results indicated that influenced by carrier density, the ionization track width at different depths of the semiconductor devices was the main factor that affected the charge collection. More charge was collected when the ionization track width in the surface area of the device was larger. The opposite result was observed in the depletion region and substrate layer. The implications of the results for laser-high energy particle correlations are further discussed. Considering the effect of the ionization track on the charge collection efficiency, the equivalent LET of the laser will be overestimated or underestimated.

Aiming at the phenomenon of overly conservative flight load design results in the high-wind zone of traditional launch vehicle design methods—caused by factors such as the use of statistical high-altitude wind fields, independent work across departments, and repeated consideration of parameter deviations across disciplines—this paper proposes a probabilistic flight load design method for the high-wind zone based on measured high-altitude wind data. This method integrates wind-compensated trajectory design, six-degree-of-freedom Monte Carlo simulation, active load alleviation, and load synthesis techniques to provide flight loads experienced by various structural sections of the launch vehicle in the high-wind zone. These loads are derived from historical measured wind field data and satisfy a certain probability threshold. The advantages of this method lie in its direct use of measured high-altitude wind data, avoidance of repeated parameter deviation considerations, and integration of trajectory wind compensation and active load alleviation technologies. This technology has been successfully applied to the pre-launch quasi-real-time wind compensation for the ZQ-2EY2 launch vehicle, as well as the high-wind zone flight load design for the ZQ-3 launch vehicles. It has effectively increased the launch-day high-altitude wind clearance probability for the ZQ-2EY2 and significantly reduced the high-wind zone flight loads for the ZQ-3, thereby lowering structural weight and improving launch vehicle performance.The application of this technology effectively enhances the launch vehicle's payload capacity and adaptability to complex meteorological conditions. It provides greater possibilities and opportunities for space exploration, driving the advancement of space science research and experimentation.

On May 29, 2025, The Tianwen-2 probe had been successfully launched, embarking on the China’s first asteroid and comet exploration mission. With a single launch, the mission aims to achieve sample return from asteroid 2016 HO3 and fly-by detection of comet 311P. The Asteroid Medium Angle Camera (AMAC) is one of the key optical payloads carried on the probe, designed for global imaging of asteroids. It is expected to determine physical parameters such as rotation characteristics, shape, and size of asteroids and main-belt comets, as well as study their surface morphology and other scientific objectives. This paper introduces the scientific objectives, functions, and performance specifications of the AMAC. It provides a detailed overview of the camera’s optical system design, structural design, electronics design, and FPGA software design. Additionally, the calibration tests, ground verification experiments, and their results are discussed. Currently, the camera has completed its first in-orbit imaging session, capturing some color images of earth and the Earth-Moon system. The output images are clear with accurate color reproduction.

The Earth’s magnetotail tail lobes are extended structures formed by solar wind compression on the sunward side of the magnetosphere. These regions are filled with low-density, high-temperature rarefied plasma, whose particle spectrum and flow characteristics significantly differ from typical magnetospheric environments like the solar wind. When the Moon periodically traverses this region, the interaction between charged particle streams and the lunar surface triggers redistribution of surface charge and alters the spatial migration characteristics of near-surface lunar dust. Therefore, this study employs the Spacecraft Plasma Interaction System (SPIS) software to simulate lunar surface charging behavior induced by charged particle streams arriving at and departing from the lunar surface within the magnetotail lobe environment. It investigates the evolution of lunar surface potential, current, and the spatial distribution of charged lunar dust during the particle influx process. Results indicate: During the initial charging phase, high-speed electron streams reach the lunar surface first, causing the surface potential to rapidly drop to approximately −39.00 V. As the negative surface potential intensifies, charged lunar dust generated by collisions with the electron stream migrates outward due to electrostatic repulsion, causing the potential to gradually rebound and stabilize between −1.00~−20.00 V. During the steady-state phase, electron, ion, and dust currents achieve flux equilibrium. Charged dust primarily accumulates within 0~100 m above the lunar surface, forming a near-surface dust layer with a density of approximately 10⁶ m⁻³.

Driven by the global commercial space wave, remote sensing constellations are accelerating their transformation towards ultra-large-scale deployment and multi-scenario market-oriented applications. Traditional simulation tools face prominent problems such as high model coupling, poor scalability, single scenario adaptability, and lack of commercial effectiveness quantification capabilities, making it difficult to support constellation design demonstration and operational decision-making. To address these issues, this paper focuses on the construction method of a large-scale multi-scenario space remote sensing satellite simulation system, and proposes and implements an integrated, high-fidelity, and scalable simulation platform. A four-layer architecture of “Application Layer - Task Layer - Service Layer - Basic Support Layer" is innovatively designed to break through the bottleneck of ultra-large-scale constellation simulation. An integrated modeling method combining component-based and parameterized approaches is adopted to realize flexible reuse and rapid configuration of core components such as satellite platforms and optical/synthetic aperture radar payloads. A multi-scenario driving mechanism based on standardized configuration files is constructed to support one-click switching of diversified scenarios including commercial mapping and agricultural monitoring. Based on the core logic of "mission-driven-resource collaboration - data closed-loop”, the complete link from mission analysis, resource scheduling to data output is connected, and commercial effectiveness indicators such as task completion rate and resource utilization rate are quantified. Simulation results show that the system can effectively support the simulation verification of constellations with a scale of 50~10 000 satellites, compared with the modeling cycle of traditional equipment systems (usually 1~2 months), the modeling cycle of the system can be shortened to within 1~2 days, significantly reduce the development risk and operational cost of commercial constellations, and improve the market response speed. The research in this paper provides key technical support for the digital construction, mission planning optimization and effectiveness evaluation of China’s ultra-large-scale commercial remote sensing constellations.

Recovering the test model is important in developing the techniques of measuring the parameter continuously and directly during its flying process on the ballistic range. It is more difficult to recover the test model with hypervelocity on the ballistic range with the increase of flying velocity and mass, and the requirement is much higher for the design of test model and recovery system. Soft recovery techniques were studied for the test model with launching velocity above 3.0 km/s on the ballistic range. The design requirement for the test model and sabot was summarized in order to ensure the model integrity during its deceleration and recovery process. The design method of shielding heat was summarized in order to protect the data storage components installed in the test model. The deceleration and recovery system was also designed. The intact free-flight model was recovered safely with a mass of 837 g and a launching velocity of 3.3 km/s, and the whole measurement data from onboard diagnostics were obtained, i.e. the acceleration, external pressure and temperature during the process of launching, flying and recovery. Based on the measuring requirement of aerodynamic force and the development of soft recovery techniques, the test method of recovering the model softly and using repeatedly was proposed on the ballistic range.

Characterization and classification prediction of hypervelocity impact flash radiation are crucial for the assessment and diagnosis of structural material damage. On the hypervelocity impact range of China Aerodynamics Research and Development Center, tests have been conducted to study the radiation characteristics of impacts. The projectiles contained aluminum spheres and aluminum-polycarbonate combination, and various structural targets were naked Hexogen（RDX）, empty box, and packed RDX. Within an impact velocity range of 2.6 km/s to 7.3 km/s, measurements were taken of the time-series signals of radiation intensity across two channels: 800.0 nm and 393.4 nm. By comparing the radiation time-series data, significant differences were observed in the peak radiation signals generated by impacts on different targets, which also showed correlations with impact velocity. Through quantitative extraction of radiation peak features from the signals, the power-law variation relationship between radiation characteristics and impact velocity under different experimental conditions were studied. This analysis revealed distinct differences in radiation signal characteristics corresponding to various targets. Furthermore, by mapping these radiation features onto a two-dimensional plane and performing analysis of two-dimensional feature classification, it was demonstrated that the radiation characteristics of different targets could be effectively classified and predicted.

Alumina-mullite biphasic fibers have attracted significant interest due to their exceptional mechanical properties and high-temperature stability. However, achieving the formation of mullite and α-Al₂O₃ biphasic structures at lower temperatures remains a challenge. This study introduces a novel approach for low-temperature preparation of alumina-mullite biphasic fibers. The method utilizes a biphasic hybrid sol precursor, leveraging the encapsulation effect of polyethylene glycol (PEG). Aluminum carboxylate sol and tetraethyl orthosilicate were selected as raw materials. PEG encapsulates both mullite and alumina precursor sol particles, creating a biphasic mixed sol system. Alumina-mullite biphasic fibers were then fabricated via a dry spinning process. Results show that when the Al₂O₃/SiO₂ ratio was between 60:15 and 70:15, the mullite precursor sol preferentially transformed to mullite. By encapsulating both mullite precursor sol particles (Al₂O₃/SiO₂ ratio of 65:15) and alumina sol particles with PEG 4 000, then concentrating and mixing the two sols, the fiber with a biphasic structure was formed at 1 300 °C. This structure consisted of rod-like α-Al₂O₃ and mosaic-shaped mullite. The study also clarified the underlying mechanism of PEG encapsulation, providing a theoretical basis for developing high-performance alumina-based fibers.