The future development of space transportation system is studied. To this end, the development planning of main space powers in the world has been summarized, the main development trend of world space was then discussed and the capability requirements are analyzed for future space transportation system. On this basis, current transportation system development is further reviewed. Afterwards, the mission mode concepts and initial transportation system schemes are proposed for future large-scale access to space, space orbital transportation and human Mars explorations, providing suggestions for future development of China's space transportation systems.

A major aspiration in human space exploration is to establish a permanent lunar base. Europe, the United States, and China have successively proposed roadmaps and specific plans for construction of permanent lunar bases around 2030, with a key prerequisite of a safe, stable, and reliable water resource supply. Recent exploration and analysis suggests that the Permanent Shadow Regions (PSRs) at the lunar poles may contain adequate amount of natural water ice. However, our understanding of the evolution of water ice in geological timescale is largely limited, leading to a lack of reliable initial and boundary conditions for research on the large-scale recovery of lunar water ice: Elucidating the diffusion mechanics of rarefied water vapor in lunar regolith is crucial for clarifying formation and evolution of lunar water ice reservoirs. However, water ice in lunar PSRs is in extreme environment of extremely low temperatures, high vacuum, and is mixed with lunar regolith, that makes the diffusion models adopted for Earth conditions inapplicable. Specifically, there is lack of rigorous thermodynamic description for extremely sparse water vapor molecules within the microstructure of porous media, lunar regolith-water interaction data, in-situ packing structure of lunar regolith, and theory for diffusion in porous media under infinitely large Knudsen number. To address the aforementioned issues and thus establish a solid theoretical foundation for further exploration and recovery of lunar water resources, it is necessary to strengthen theoretical research, and to design more targeted analysis and testing of lunar samples in the future.

Space weathering, including micrometeorite impacts and solar wind irradiation, leads to the formation of metallic iron particles that range in size from nanometers to micrometers. These particles are commonly found on the surfaces of airless bodies, such as the Moon. Their presence significantly alters the spectral properties of the lunar surface, and the resultant optical effects vary depending on the particle size, making accurate interpretation of remote sensing data challenging. Despite decades of research, the formation mechanisms of metallic iron particles of different sizes remain unresolved. In this study, we conducted a systematic microscopic analysis of glasses from China's Chang'e-5 lunar soil samples, focusing on impact glass beads with well-defined impact origins and rotational features. We successfully distinguish large and small metallic iron particles formed before and after the solidification of these glass beads, clarifying them as products of micrometeorite impacts and solar wind irradiation, respectively. This research highlights the distinct roles of impacts and irradiation in space weathering, enhancing our understanding of the interaction between space environments and the lunar surface, and offering valuable insights for predicting weathering behavior under different space conditions.

Safe, reliable, fast, and low-cost space transportation is a prerequisite for large-scale exploitation and utilization of space resources. The future exploitation of space resources will obtain a large amount of strategic mineral resources urgently needed for the sustainable development of the Earth, requiring the capability of low-cost return to the Earth. A new low-cost entry method called tethered resource module return technology assisted by ultra-low orbit spaceship was proposed. Modeling analysis and numerical simulation results show that the tethered resource module effectively reduces orbital velocity and altitude, and thus alleviates the difficulty of re-entry back to the Earth surface. It is expected to provide a new technological means for green, low-cost, and large-scale re-entry into Earth's space.

With the vigorous development of space missions in Earth orbit, Lunar orbit, and Mars orbit as well as other missions such as Lunar or Martian research stations, the efficient utilization of solar energy resources in the space environment is critical for these missions. Perovskite solar cells have attracted much attention due to their excellent optoelectronic properties, low cost and simple fabrication process. We comprehensively introduced the research progress of perovskite solar cells/materials both domestically and internationally, including the basic optoelectronic properties, geometric structures, and research status of perovskite solar cells. We also focused on the application of perovskite solar cells in space environments, for example, their performance under special conditions such as high-energy particle irradiation, large temperature cycling and UV irradiation. Finally, a summary and explanation of the challenges it faces in the aerospace field was provided, and then we proposed the key issues needed to be investigated and solved in future.

With the increase of human demand for natural resources and the consumption of mineral resources on the Earth, it has become an inevitable trend of development to obtain resources from outer space, asteroid mining has a very high economic value. In recent years, NASA's OSIRIS-REx and JAXA's Hayabusa 2 missions have both successfully returned samples from asteroids. China's Tianwen-2 mission will also carry out asteroid sampling and return. However, asteroid mining just remains at the conceptual stage. In this work, we studied two asteroid mining schemes, surface mining and fly capture, as well as the associated dynamical problems, based on the modeling of asteroid polyhedral gravitational fields and spherical harmonic series surface. For surface mining, we proposed an efficient asteroid surface mining method, with selecting asteroid Bennu as the target, and analyzed the surface dynamical characteristics of Bennu in relation to the requirements for surface mining. For fly capture, we used a concentrated mass nonlinear spring-damper model to simulate the dynamic process of capturing an asteroid with a flexible tether net, and analyzed the displacement, velocity and acceleration of some nodes, which could provide theoretical guidance for future asteroid mining missions.

European Space Agency's mission Jupiter Icy Moons Explorer (JUICE) is the most advanced and complicated spacecraft ever launched in Jovian system exploration. As the first large mission of European Space Agency's "Cosmic Vision 2015-2025", JUICE is dedicated to making detailed observations of the largest planet in the solar system and characterizing Jupiter's three large icy moons Ganymede, Callisto and Europa to determine their habitability. JUICE mission's scientific objects, payloads, trajectory and key functions of the spacecraft are analyzed and discussed. A Jovian system exploration mission layout is proposed. Some advices and thoughts about China's Jovian system exploring mission are given based on the discussion.

During lunar surface exploration activities, the operations of astronauts and equipment significantly elevate dust concentrations beyond natural levels. These charged lunar dust particles not only affect the performance of space equipment but also pose serious health threats to astronauts due to their high abrasiveness and biotoxicity. To systematically understand lunar dust contamination, we first reviewed the physicochemical and electrical properties of lunar dust to gain insights into its contaminating behavior. By summarizing the dust-related issues encountered in previous lunar missions, we provided a detailed analysis of the impact of this contamination on various systems of lunar exploration equipment. Finally, we examined existing lunar dust mitigation strategies, evaluating their strengths, weaknesses, suitable scenarios, and future development directions, with a focus on dust prevention and removal technologies that primarily utilize electromagnetic forces. Future research will concentrate on in-depth investigations of key technologies for active dust prevention and removal through electric fields in simulated lunar environments, ensuring the smooth progress of lunar exploration activities and safeguarding the health and safety of astronauts.

The development and utilization of lunar resources is the core content and focus of lunar exploration by major space powers in the new era. We first introduces the technical challenges in lunar resource development engineering, and then proposes a cost-effective, large-scale technology scheme for the batch return of lunar resources. The core of this scheme is a newly designed lunar-based magnetic levitation rotational ejection system, and it offers significant advantages and features, such as strong originality, easy implementation, and high efficiency. Therefore, it can substantially enhance the efficiency of lunar resource transportation, and reduce return costs. Moreover, it has important practical significance for achieving large-scale batch return of lunar resources and promoting their commercial development. Additionally, We proposed a conceptual design for a large scientific facility of the lunar resource development and application system, aiming at supporting future lunar exploration scientific research as well as resource development and utilization.

Solar in-situ sintering of lunar soil can effectively realize the in-situ utilization of lunar resources, and is expected to be one of the most potential processes for lunar base construction. In this study, the test system of solar concentrating die sintering based on HUST-1 simulated lunar soil was set up. The surface radiation and solid heat transfer in the process of solar concentrating sintering were calculated by COMSOL, and the initial test of sintering under atmospheric and vacuum environment was carried out. The simulation results show that when the solar irradiance is 1368 W/m², the temperature in the mold can reach 1100℃, which meets the dynamic requirements of lunar soil sintering. The experimental results show that the sintering temperature is the key process parameter of lunar soil sintering in solar concentrator mold. When the temperature in the mold reaches 800℃, the simulated lunar soil solid-state sintering starts. Due to the difficulty of heat preservation caused by the scattering of sunlight by suspended particles in the Earth's atmosphere and the rapid heat dissipation in the sintering stage at high temperature, the formed blocks have low strength. Therefore, it is necessary to further optimize the test system to explore the densification mechanism of simulated lunar soil by solar concentrating sintering.

The Europa Clipper is the largest planetary explorer built by NASA to date. The goal of the mission is to assess the habitability of Jupiter’ s moon: Europa. After entering Jupiter orbit in 2030, the flight system will collect science data while flying past Europa 49 times. We explained, from a scientific research perspective, why Europa was selected as the target for this mission, outlining the scientific objectives of the Europa Clipper and its nine scientific instruments, as well as the implications of this mission for space science.

The successful implementations of Chang'e-5 and Chang'e-6 lunar sampling return missions and the Tianwen-1 Mars exploration mission indicate that China has entered into a new stage of deep space exploration. The study of the space environment of planets is of great significance for understanding the evolution laws of planets and for the future in-situ resource utilization. A review on the planetary space environment exploration missions that have been implemented or under preparation for the future by human beings was given in this paper. Opportunities and challenges faced by China's planetary space environment research were discussed, and some suggestions for the future developments were also given.

This paper analyzes the current status of space debris and active debris removal techniques, and proposes a space debris removal scheme. The scheme elaborates on the overall concept design, debris removal process, capture methods, and relevant computational models. Based on three-dimensional visualization technology, a software design for visual simulation of space debris removal was completed, and simulation verification tests were conducted to dynamically demonstrate the visual simulation process of space debris removal missions. The test results indicate that the proposed space debris removal scheme can effectively accomplish debris capture. This work provides visual services and verification support for validating the feasibility of space debris removal schemes, which holds significant implications for future proactive space debris removal efforts and other on-orbit space missions.

Uncontrolled spacecraft salvage is one of an important means of protecting space assets, and analysing and determining the target attitude motion state is very important for failed spacecraft salvage. This paper provides an overview and summary of uncontrolled spacecraft attitude motion and related influencing factors. The effects of space environment interference and spacecraft component interference are analyzed. Taking the SAST-1000 platform as an example, a comprehensive analysis of the effects of the above disturbances is carried out, and a simplified scheme of the attitude-motion model of the spacecraft and the effects of different disturbances on the momentum moment and the rotational kinetic energy are given for a specific case.

Lunar surface elemental composition has always been a focused topic in the field of lunar exploration and research. Particle detectors, such as Gamma-Ray Spectrometer (GRS) and Neutron Spectrometer (NS), are widely used to determine the distributions of natural radioactive elements (U, Th, K), major elements (Fe, Ca, Si, Al, Mg, etc.), and water ice (H) on the lunar surface. These findings have significantly promoted human understanding of the Moon origin and evolution, and have also driven the step to develop and utilize lunar resources, as well as to establish the lunar research station. Amidst future many lunar explorations, this paper discusses the generation mechanisms of gamma-rays and neutrons carrying elemental features. We introduce detection principles and detector responses of both GRS and NS, and give an overview of the main results and related data analysis methods for the lunar surface element composition over the past 30 years. This work can serve as a reference for future China lunar exploration missions such as Chang'E-7 and other deep space exploration tasks.

In view of the self-gravity requirements of space gravitational wave detection, we build a finite element model of the whole spacecraft based on the design scheme of "Taiji" space gravitational wave detector, and calculate the self-gravity of the test mass based on the finite element method. The self-gravity calculation deviation is analyzed when the test mass is approximated as a single particle, multiple particles, a cube and a quasi-cube, and the calculation effects of the integral function and the theoretical analytical formula is compared. The simulation results show that when the test mass is approximated as a single or multiple particles, the calculation accuracy is limited by the number of particles; when the test mass is approximated as a cube or a quasi-cube, the calculation accuracy is higher and the relative calculation deviation between the two methods is less than 0.02%; when using the integral function and the theoretical analytical formula to calculate self-gravity, the difference in the calculation results of the two methods does not exceed 10^-18 m/s². The theoretical analytical formula is faster in calculation and can be effectively used in subsequent self-gravity calculations.

The terrain of the lunar south pole is complex, and the extremely low solar altitude angle causes large changes in the shadow area, which poses a huge challenge to the autonomous navigation of the rover. This work proposes a multi-modal sensing and obstacle avoidance path planning scheme for the rover facing the lunar south pole. On the one hand, the RGB camera is used to obtain the global scene image for preliminary obstacle detection; on the other hand, the depth camera is used to obtain the real-time environment depth, and a local map is constructed through a simplified SLAM algorithm, that is, a point cloud map is generated in real time; and based on the point cloud information, to calculate physical environment information such as road surface roughness, slope, step information, etc. The above-mentioned multi-modal data combined with map data are used to update the posture and surrounding environment of the patrol vehicle in real time, and a combination of multi-modal local algorithms and obstacle detection algorithms are used for obstacle perception and obstacle avoidance decision-making, so that the patrol unit can dynamically adjust its path. The simulation results show that the autonomous navigation system significantly improves the autonomous navigation capability of the patrol unit in complex and unknown environments.

In this paper, the parachute recovery system designs and technical characteristics of global deep space unmanned sampling explorers were introduced and summarized. These explorers were successfully carried out far beyond the Moon including Genesis, Stardust, OSIRIS-Rex, HAYABUSA-1 and HAYABUSA-2. According to the discussion of the different parachute recovery system designs and features, we analyzed several key issues. These issues include the choice of parachute type, the feasibility of long-term space on-orbit storage of parachute and other fabric products, parachute opening control scheme options, the recovery location means during the parachute descending phase and after landing touchdown. Finally, a brief summary of the designs and key issues of deep space unmanned sampling and returning explorers parachute recovery systems was presented.

Lunar bases are strategically important for supporting long-duration human presence on the moon and scientific research. However, moonquakes pose great potential threats and security challenges to the construction and operation of lunar bases. The causes and characteristics of four types of moonquakes were summaried. The main reasons why shallow moonquakes may damage the structure of lunar bases were ‌analyzed, the common monitoring and data analysis methods of moonquakes were summaried, the impacts of moonquakes on different structures and the characteristics of structural dynamic response combined with four typical lunar base structures were discussed, the failure conditions, failure parts, stress distribution, and deformation degree of the typical structures under the action of moonquakes were given, so as to provide references and prospects for future lunar base structures research on the seismic design and seismic hazard prevention and mitigation.

In response to the potential threat of planetary impacts on Earth, often likened to the “Sword of Damocles” hanging over humanity, Near-Earth Object (NEO) defense technologies, such as Nuclear Explosion and Kinetic Impact, have become the preferred solutions within the international community. Despite the emergence of various institutions and cooperative models aimed at coordinating responses to NEO threats, the international legal framework governing this field remains underdeveloped. Consequently, China faces challenges in international cooperation, including limitations in monitoring and early warning systems, insufficient transparency in on-orbit management, and unreasonable decision-making mechanisms. In light of these challenges, China should actively build its own space discourse framework while promoting international cooperation. This involves integrating relevant provisions from international treaties and drawing on governance experiences from other global commons. China should also propose an action plan for NEO defense, establishing comprehensive international cooperation mechanisms for information sharing, decision-making, and oversight across the pre-event, mid-event, and post-event phases. These efforts will not only help extend the concept of “a community with a shared future for mankind” to outer space but also further promote the peaceful and sustainable use of outer space, safeguarding the common interests of all humanity in this domain.

This paper, Thermal-structural-optical integrated analysis and experimental research for the Cool Planet Imaging Coronagraph (CPI-C) on China Space Station Telescope (CSST). Firstly, temperature field distribution was simulated by a thermal simulation analysis software. Secondly, the temperature field was mapped onto the optical-mechanical system to calculate the mirror surface deformation. Then, the rigid translation and Zernike polynomial coefficients of the mirror surface were fitted by the finite element data of each mirror surface node. Then the analysis results are imported into Zemax to evaluate the influence of mirror surface shape change. Lastly, the optical performance was tested by 4D interferometer. The test results show that the RMS value of the wavefront distortion is 1/25 wavelength, which meets the design requirement of being better than 1/20 wavelength.

China's International Lunar Research Station (ILRS) project emphasizes a dual focus on scientific exploration and resource utilization, with in-situ resource utilization (ISRU) as a key technical component. To ensure the effective implementation of the ILRS, this study investigates the lunar transportation capacity required to support ISRU-related activities, including prospecting, mining, and construction. The paper begins by identifying the limitations of current lunar surface mobility in terms of range, speed, and sensory capabilities. It then defines the fundamental requirements for lunar transportation systems, focusing on the operational characteristics of both transportation lines and vehicles. As a solution, a vehicle-road coupled transportation system architecture is proposed. After evaluating existing technological options, the study outlines two potential development paths: integration and standardization. A trade-off framework is introduced to connect mission needs with candidate technologies. Additionally, three key research directions are recommended to guide the transition toward an optimized lunar transportation system in future high-level system designs.

It is a technology difficulty to carry out the high enthalpy aerothermodynamic ground test in China before. The magneto plasma dynamic heater, inductively coupled plasma heater and arc heater are combined to be one kind of ground test technology by China Academy of Aerospace Aerodynamics. This test technology can simulate the aerothermodynamic environment of second cosmic velocity reentry in ground test now. When the ϕ60 mm-SR90 mm uniform heat flux stagnation sample is utilized, the test technology can realize the aerothermodynamic condition as below: 8 ~ 87 MJ/kg enthalpy, 500 ~ 6800 kW/m² heat flux, and 1 ~ 66 kPa stagnation pressure. The ablation performances of four classic types of TPMs affected by heat flux and total enthalpy have been obtained in high enthalpy heating condition. The ablation mechanism of carbon silicon composite pyrolysis TPM has been proved through the research. When the total enthalpy is invariable, the ablation rate will rise in logarithmic curve with heat flux increase. When the heat flux is invariable, the ablation rate will decline in exponential curve with total enthalpy increase. The test technology has been used in subsequent phase of the Lunar Exploration Project, and can also be applied to the study of high temperature non-equilibrium effects, and will provide equipment foundation and technical reserves for future manned moon landings and deep space exploration projects.

Sintering lunar regolith simulant to prepare lunar brick is an effective in-situ resource utilization method for lunar base construction. However, the traditional high temperature sintering has the disadvantage of high energy consumption, which is not conducive to the initial construction of the lunar surface. Cold Sintering Process (CSP) is a process of densification of ceramics at ultra-low temperature, which provides a solution strategy to overcome the above problems. Two types of lunar regolith simulant materials (mare and highland) were densified by CSP at 120 ℃, 100 MPa, 15% 10 mol/L NaOH and 90 min. The sample densities reached 2.33 g/cm³ and 2.31 g/cm³, respectively. In the simulated lunar surface environment, the strength retention rates of the sample are 94% and 95% respectively, the thermal conductivity and thermal expansion coefficient are lower than that of the earth concrete, which indicates that the sample has high reliability in the extreme environment of the lunar surface. In addition, the energy consumption of the CSP equipment is only 0.79 kW·h, which saves 90.7% of the energy compared to the traditional high-temperature sintering peocess. Therefore, the CSP provides a broad prospect for energy-saving manufacturing of high strength and durability of lunar surface building materials.

Space debris can be classified into three groups: big debris, dangerous debris and micro-space-debris. As for the micro-space-debris, the size is less than 1mm. The research method of such debris is to “defense”the collapse. Firstly, establish the debris environment model, and then, evaluate the risk of the impact by such debris, at last, design the defense structure. Debris environment model is evolved and needs updating according to the measurement of the multiple-parameter information. This paper reviewed the development of the in-situ micro-space-debris detector, and then analyzed the development of the technology of such measurement. At last, this paper put forward the in-situ measurement system of the micro-space-debris.

Energetic neutral atoms from the solar system's heliopause and beyond serve as important carriers for understanding the neighboring interstellar medium and its interaction with the solar wind. Due to the limited duration and difficulty of missions to the heliospheric boundary of the solar system, remote sensing detection of energetic neutral atoms in the near-Earth space is more feasible. Studying energetic neutral atoms at the heliospheric boundary can enhance our understanding of the composition and properties of the local or nearby interstellar medium, thoroughly verify space science questions such as solar system evolution and planetary evolution in the solar system, and has significant implications for advancing China's space missions and frontier scientific development. This paper summarizes recent international cases of remote sensing detection of energetic neutral atoms at the heliospheric boundary, analyzes the key technologies and scientific objectives of these missions, and outlines the future trends and directions in this field, providing suggestions for the planning and construction of future heliospheric boundary exploration mission in China.

In 2023, the Space Commerce Office under the National Oceanic and Atmospheric Administration (NOAA) of the United States Department of Commerce launched the "Traffic Coordination System for Space" (TraCSS) project, based on the previous open database architecture. It is anticipated to offer fundamental space situational awareness data and services to civilian and commercial space operators, sending alert messages to spacecraft that might face collision risks, in order to achieve safe space flights, space sustainability, and the coordination of international space activities. This article, in accordance with the project information released by Space Commerce Office and relevant open-source information, combs and analyzes the system construction path, framework design, and the functions of each component of the system. TraCSS adopts a cloud-based containerized microservice architecture, achieving the integration and governance of US military, civilian, and commercial space situational awareness data. We analyzed the development process, system design, and possible influences of TraCSS. Also, we combined the characteristics of TraCSS to provide insights and recommendations for the development path and system construction of China's space traffic management.

The method of a low-cost verifiable in-orbit laser ablation experiment was given in this paper. With this method, a meteorite ball which was be releasing actively was ablated by multi-pulse continuous laser beams which were generated by a mall pulse laser with low energy. Through a combination of laser rangefinder, micro-propulsion module, and attitude control system, as well as acceleration curve measurement and integration, effective tracking and convenient measurement of velocity increment of the target meteorite ball have been achieved. Finally, specific design with specific experimental scenarios was provided, and preliminary simulation of the test effect was given. This work will provide a experimental idea for the impulse coupling coefficient in-orbit measurement which is the key parameter to evaluate the effect of laser ablation for asteroid orbit deflection with the real scene of asteroid defense.

Since the 1990s, the United States, Europe, Japan and China have successively implemented and planned their own asteroid exploration and defense missions, and asteroids have become a new hot spot for deep space exploration after the Moon and Mars. Looking at the development history of asteroid missions, the application of CubeSats and landers can play an important role in different types of asteroid missions, such as asteroid sampling return and near-Earth asteroid defense. Hayabusa 2 deployed two types of Micro/Nano-landers, MINERVA and MASCOT, in the mission to obtain high-precision in-situ detection data on the asteroid surface, which supplemented and enhanced the scientific discoveries of Hayabusa 2. DART observed the kinetic impact process and ejecta morphology by releasing the CubeSat LICIACube. The HERA mission will use two CubeSats, Milani and Juventas, to accurately measure the surface composition, internal structure and gravity field of the Dimorphos asteroid. This paper will analyze the application cases of CubeSats and landers in different asteroid missions, and propose some ideas for using CubeSats and landers in the mission based on the mission objectives and mission forms of my country's first asteroid defense mission.

Understanding the components of asteroids plays an important role in guiding research on the origin and evolution of asteroids, utilization of space resources, and asteroid defense. Siliceous asteroids are the main type of near-Earth and inner main belt asteroids and are also the most common parent bodies of ordinary chondrite. In order to improve our understanding of the mineral composition of siliceous asteroids, the mineral compositions of eight siliceous asteroids with high spectral signal-to-noise ratios were investigated. By deconvolving the mixed spectrum of asteroids, we have obtained the absorption characteristics of ferromagnesian minerals, including their magnesium olivine index (Fo#) and the proportion of high-calcium pyroxene and then we identified the corresponding meteorite analogues for these asteroids. The results indicate that Sr-type asteroids (3) Juno, (808) Merxia and S-type asteroid (4197) Morpheus have higher Fo# and lower high-calcium pyroxene content, with surface compositions similar to H chondrites. The Sq-type asteroid (433) Eros has a relatively low Fo# and a high proportion of high-calcium pyroxene, with surface compositions resembling L chondrites. Sv-type asteroid (5) Astraea and S-type asteroid (17) Thetis have surfaces almost devoid of olivine, while V-type asteroids (3908) Nyx and (4055) Magellan lack olivine altogether, with surface mineral compositions similar to basaltic achondrites. The results show that even if they are all siliceous asteroids, their types have mineral diversity, and their correspondence with meteorite types is also complex and diverse. This is related to the origin and evolution of the asteroid itself and its later transformations such as space weathering and impact metamorphism. It also shows that the existing asteroid spectral classification system needs to be improved, and caution is needed when interpreting the mineral composition and evolution of asteroids based on spectra.

Space debris poses a growing threat to the safety of space activities and the development of the aerospace industry in various countries, as its number increases annually. Addressing the challenges associated with space debris, such as its small size, high dynamics, and difficulty in long-distance detection. We proposed the application of distributed aperture radar in the field of space debris perception,and summarized the key technologies for realizing space-based distributed aperture radar from three aspects:high-precision formation flying, space-time-frequency synchronization, and beam forming. Additionally, recommendations and outlooks for future research were provided.

Near-Earth asteroid impacts represent a significant potential threat faced by all of humanity. Monitoring and providing early warnings to identify near-Earth asteroids with a high impact probability, as well as conducting impact predictions, are essential prerequisites for planetary defense. According to the core requirements of short-term impact forecasting for near-Earth asteroid, National Space Science Center, CAS independently designed and developed the System for Hazardous Asteroids Risk Prediction (SHARP). The Imminent Impactor Scenario of SHARP (SHARP-IIS) performs orbit determination, orbit propagation, and impact prediction for near-Earth asteroids that reach a certain proximity to Earth based on observational data to provide critical references for planetary defense. This paper introduces the basic principles of each functional module of the SHARP-IIS system and demonstrates its performance through the impact events of asteroid 2024 RW1 and asteroid 2024 UQ with different observation arc lengths. In the scenario of asteroid 2024 RW1 with an observation arc of seven hours, the SHARP-IIS system achieved a relatively high-level prediction accuracy. Compared with the airburst data recorded by the Center for Near-Earth Object Studies (CNEOS), the calculated airburst location error by SHARP-IIS was less than 20 km, and the minimum airburst timing error was around 1 s.

During the process of accurate measurement and identification of space objects, space searching camera must overcome complex space environment, such as the noise of massive star background, the deficiency of features within single visible images, rapidly relative orbital maneuvering of the spacecraft. In this paper, far range area target detection and close range feature recognition were proposed to extraction, matching and tracking of target feature parts in real-time and accurately. Using feature detection, shape analysis and deep learning methods, centroid of target feature parts could be measured or calculated. Base on the design of space searching camera with dual-band common aperture system, simulation and experiment of high resolution images were promoted. The resolution show that the resolution of image details has been improved by 10%~30%. At the same time, function of feature detection, centroid localization and match recognition was realized.

Electrical connectors, as the basic components of space equipment for in-orbit servicing and maintenance, have extensive assembly and disassembly access requirements. The automatic access technology involves key technologies such as force sensing, visual recognition and positioning, and compliance control of manipulators. It has important research significance and promotion value. Based on a 6-DOF manipulator, a binocular structured-light camera, and its control software, a test platform for automatic access of different types of electrical connectors was constructed. The template point cloud was precisely aligned using key-point extraction, RANSAC course registration, and ICP fine registration algorithms. The high-reliability identification of different types of electrical connectors in the access state was completed. The impedance control of robotic arm was used to achieve a series of manipulations, including grasping and positioning, aligning, screwing, plugging and disassembly. The feasibility of the platform system and method was verified by testing the automatic access operation of Y27 and J30 electrical connectors as typical cases.

This paper discusses the forms and characteristics of Thermal Protection Structures (TPS) for Reusable Launch Vehicles as well as the importance of health monitoring and maintenance. TPS play a crucial role in the operation of aerospace vehicles. They not only have to withstand extreme temperatures and pressures but also ensure the safety of the vehicle. The monitoring objects of TPS cover their service status and possible damages. We reviewed the technical means of health monitoring for TPS. Among them, optical fiber sensing technology has the advantages of high precision and anti-interference, and can monitor the temperature and strain of TPS in real time. Acoustic emission technology can effectively detect the occurrence of structural damage. Ultrasonic guided wave technology can perform rapid detection on large-area structures. Finally, taking the space shuttle as an example, the maintenance technology of thermal protection structures was introduced, including the repair of damaged parts, etc., to ensure that the TPS is always in a good working condition and provide strong guarantee for the safe operation of aerospace vehicles.

Based on the observation data from the Sanya Incoherent Scatter Radar during the 2020 Geminid meteor shower, this study analyzed the flux of micrometeoroids in near-Earth space. From December 13th to 14th, 2020, a total of 9,500 micrometeoroid events were detected over a continuous 24-hour observation period, with an average rate of approximately 400 events per hour. Considering the radar beam width and duty cycle, the flux of micrometeoroids in near-Earth space was estimated to be 4.3 events per day per 100 square meters. Given the radar's observational mode and sensitivity limitations, this estimated value is likely lower than the actual micrometeoroid flux. The diurnal distribution of micrometeoroid flux showed significant variation, with a peak occurring around 07:00 Beijing Time and a minimum around 19:00. The micrometeoroid flux density obtained by the Long Duration Exposure Facility (LDEF) in the United States through impact craters is three times higher than that obtained by the Sanya radar. In addition to differences in the spatial height and duration of measurements between the two methods, the local time distribution of micrometeoroid flux may also be one of the main reasons for the discrepancy between the two measured values. This study provides a reference for establishing an independent micrometeoroid flux model in China.

The efficient and stable transmission of the charged beams is of great significance in space technology's cutting-edge fields. In applications such as space high-energy physics and the charged beam irradiation studies, precise control of beam characteristics is essential for high-quality applications. However, during the charged beam transmission, issues like increased electron transverse displacement and decreased beam spot flux density have emerged, limiting its application and development. Traditional design methods struggle with the complexity of the charged beam-expanding magnet assemblies' numerous parameters, failing to achieve a global optimal solution and meet the demand for high-precision beam transmission. An intelligent optimization design method for these magnet assemblies was presented. Using a genetic algorithm-based design process, We first analyzed the phase space coordinates of electrons from the front-end accelerator. Then, based on charged particle beam optics and quadrupole magnet field theories, combined with beam component distribution, the beam transmission matrix was calculated to obtain the electron phase space vector at the device's end. Considering processing capabilities and actual conditions, the geometric parameters and relative positions of magnets were determined using a neural network-modified magnet field theory. Finally, the optimal beam-expanding mode and parameters were found through the genetic algorithm, achieving efficient optimization of the magnet assemblies, increasing the beam spot's transverse size, reducing Coulomb repulsion, and compressing the divergence angle. These research achievements are significant for the charged beam transmission technology. They help break through existing technical bottlenecks, enhance equipment performance and application effects, provide a foundation for further the charged beam manipulation research, and expand the innovative application prospects of the charged beams in more fields.

Highly hazardous asteroids refer to asteroids that can enter the Hill radius of the Earth, which are the important objects for monitoring and warning tasks of planetary defense. Based on the latest near-Earth asteroid orbit/size distribution model, we applied a high-precision small body orbit propagation package to establish a simulated sample database of highly hazardous asteroids with diameters of more than 10 meters, which could be used to generate any user-required number of highly hazardous asteroids within any given duration. Through orbital deduction, populations including potentially hazardous asteroids undergoing close approaches, highly hazardous asteroids within 100 years were identified. The occurrence rates of each population in the near-Earth-asteroid and the initial potentially-hazardous-asteroid population were calculated, which confirm the effectiveness of potentially hazardous asteroids as key monitoring targets. Further more, by analyzing distributions of orbital elements and variation of occurrence rates relative to the orbital elements, it shows that the distributions of semi-major axes and eccentricities of two encounter populations mainly depend on initial distribution of near-Earth asteroid orbits, which may cause high-eccentricity orbits to account for a large proportion among the encounter populations.

Extraterrestrial Artificial Photosynthetic (EAP) technology aims to simulate the natural photosynthesis of green plants in the extraterrestrial space environment, and convert carbon dioxide into oxygen and carbon-containing fuels through physicochemical processes, making it a promising technology for efficient carbon dioxide conversion and oxygen regeneration. This technology can not only convert the carbon dioxide produced by human respiration into oxygen to realize the regeneration of waste in confined spaces and greatly reduce the material supply requirements of manned space station or manned deep space spacecraft, but also utilize the abundant carbon dioxide and water in-situ resources of the extraterrestrial environment such as Mars to produce oxygen and fuel to achieve the extraterrestrial survival of human beings on other planets. This paper comprehensively overviews the recent progresses of extraterrestrial carbon dioxide conversion technologies. It also clarifies the concept and connotation of EAP technology and analyzes its characteristics and application prospects. On this basis, this study first proposes the space experiment objectives of EAP technology, and then presents the design of the experimental payload, relevant ground tests results, and on-orbit experiment progress. Finally, this paper summarizes and prospects the research progress of EAP technology.

The charged debris generated inside the conductive slip ring of the spacecraft will not only aggravate the wear of the slip ring, but also cause electric field distortion, induce vacuum flashover along the surface, and affect the working reliability of the solar cell array. In the paper, we simulate the distribution of the electric field, potential and magnetic field inside the conductive slip ring, and then study the motion of the live friction. Simulation analysis shows that the maximum internal electric field of the conductive slip ring under the electrostatic field is 2.65×10⁴ V/m, and the charged dust moves to the side of the insulated baffle, and the maximum speed can reach 3.92×10⁻³ m/s. In the space electron irradiation environment, the maximum value of the internal electric field is 3.7×10⁸ V/m, which appears at the “triple combination” point, and the maximum speed can reach 4.05×10⁻³ m/s, and the migration movement is more obvious. The on-orbit test confirmed that the debris moved and gathered to the side of the insulated baffle. This paper reveals the migration rules of the charged debris in the conductive slip ring, which provides theoretical support and test basis for the insulation optimization design of the conductive slip ring.