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.

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.

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.

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.

Food is crucial for space missions, tourism, deep space exploration, and mining, serving as the basis and energy sources for survival, health, and activities in space. However, the unique extreme environmental conditions in space, especially microgravity and high radiation, pose serious challenges to space food preservation and safety. Given of its importance in space missions, the research and development of space food has become an indispensable part of space technology development. Here, we introduced the new Space Life Investigation Database（SpaceLID）, a resource for space food research as well as for space biological research and public enquiry. SpaceLID contains a wide range of research on space food, including food variety, menu, quality, preservation methods and nutritional combinations. This article provides detailed overview of the information contents and navigation methods of SpaceLID, and the examples of the use of SpaceLID information for space food research. By in-depth analysis of the information in SpaceLID, one can better understand the needs and challenges of space food and design a safer, more nutritious diet that better meets the needs of human space missions.

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.

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.

This paper first provides an overview of the conceptual connotation, customer portrait, market size, and policy support from national and local governments regarding space tourism and exploration. Then the development of foreign space tourism is introduced in this paper from three dimensions respectively: suborbital tourism system, near-Earth orbit tourism system, and commercial space walk. Both Virgin Galactic and Blue Origin successfully carried out manned suborbital flights many times in 2021. SpaceX successfully achieved the first manned low Earth orbit flight in 2021 and the first commercial space walk in 2024. Then the current development of domestic space tourism is introduced in this paper, with a focus on the space tourism plans of three companies, namely Shenlan Space, CAS Space, and Beijing Interstellor Human Spaceflight Technology. Finally, this paper elaborates on the significant meaning of developing space tourism industry in multiple fields such as science, economy, technology and culture, and provides corresponding suggestions for the challenges faced by space tourism industry in the fields of technology, safety, business models, laws and regulations.

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.

Microbiological control technology in space station is a key technology ensuring the safety of astronauts and the long-term stable operation of spacecraft during extended manned missions. Firstly, the paper systematically reviewed the microbial contamination incidents in history space stations, summarizing the main characteristics of these incidents to provide warnings and lessons for the microbial protection and control of China Space Station. Then, it summarized the research progress in on-orbit microbial detection technology and on-orbit microbial control technology for space stations, with a focus on introducing the research conducted in these areas in China Space Station. Finally, the paper proposed a space station microbiological control technology system constructed by the author's research team from the perspective of systems engineering risk management, with the aim of accelerating the development of China Space Station microbiological control technology and fulfilling the microbial control requirements of China's manned space engineering.

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.

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.

In response to the requirements for precise positioning of on-orbit faults, fine maintenance, and intelligent process of typical power supply and distribution products in the space station, a technical solution for intelligent diagnosis and fine maintenance of on-orbit in-situ faults of typical power supply and distribution products is proposed. Discussions are conducted on the necessity, advancement, safety, and feasibility of the key technical links therein, as well as the application prospects. The overall concept of further reducing the maintenance level and on-orbit repair and reuse of Orbital Replacement Units (ORU) for board-level and component-level faults of products such as power control units and command bus units is expounded. The feasibility, complete technical routes, and implementation plans of essential key technologies for on-orbit maintenance, such as rapid intelligent fault diagnosis and precise positioning, and on-orbit fine-level welding maintenance, are explored. Regarding on-orbit maintenance supported by real-time and multi-mode interaction throughout the process based on augmented reality (AR), the disparities of existing AR technology in meeting the demands of board-level fine maintenance are examined. The significance of developing a domestically controllable and intelligent engine is proposed, along with the necessity and feasibility of key technologies such as dynamic registration technology, high-precision anchoring algorithm, flexible target recognition, and human-machine efficiency evaluation. A development plan for lightweight and highly comfortable wearable equipment is presented. A detailed analysis is carried out on the key technologies affected by differences between space and Earth, such as microgravity, in this set of solutions. The necessity, experimental methods, and implementation plans for on-orbit verification are proposed, including on-orbit welding technology, rapid and precise fault positioning technology, and AR-guided astronaut operations. This set of solutions not only possesses advantages such as low cost, multi-level, and refinement, which can effectively lower the maintenance level, optimize spare parts and supplies, and enhance system safety, but also has strong universality and can be extended to other experimental systems or more industrial fields, presenting broad application prospects.

The research on microalgae cultivation and microwave processing technology in a controlled space environment is of great significance for the new generation of environmental control and life support systems. In response to the scientific needs of conducting microalgae cultivation and microwave processing experiments on the China Space Station, firstly, seven candidate microalgae species were screened, and Spirulina and Nannochloropsis were determined as experimental species through factors such as availability, growth cycle, nutrients, and culture environment (light, water, pH); secondly, according to the experimental plan and candidate microalgae species, a microalgae cultivation and microwave processing device was developed, and two microalgae cultivation modes, solid-state and liquid-state, were proposed. The solid cultivation mode was used to evaluate oxygen production rate under a controlled environment, and the liquid cultivation mode was used to verify physiological characteristics of microalgae and microwave processing technologies; finally, key technologies such as controlled space design and miniaturized microwave processing were overcome, and a microalgae cultivation and microwave processing device was developed, and experiments such as ground simulation cultivation and microwave heating of microalgae were carried out. The results of ground experiments show that microalgae in liquid culture mode can be cultured for 30 days in a small volume controlled environment within the device, and the oxygen production rate of microalgae in solid culture mode is about 15 g·m⁻²·d⁻¹ in the first two days of culture. The targeted microwave heating can cook liquid microalgae in the range of 65~70℃. The microwave-processed microalgae has nutritional retention characteristics and food application potential.

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.

This paper analyzes the structural characteristics of the ventilation ducts of aerospace equipment, the structural constraints and functional requirements they impose on pipeline robots, and concludes that pipeline robots should at least have the ability to control the contact force with the pipe wall, the ability to provide stable support and steering through non-continuous ducts such as T-shaped pipes and gaps, and the ability to adapt to changes in pipe diameter. An integrated typical Series Elastic Actuator (SEA) robot leg scissor mechanism was designed to meet the demand for variable diameter adaptation. This mechanism has the ability to control flexible force. To address steering needs, swing and roll joints were designed. To overcome obstacles such as gaps, two sets of series leg mechanism modules were designed to achieve gap crossing through alternating support movements. This paper experimentally verified that the robot could navigate through complex pipelines of various sizes and types, achieving a variable diameter ratio of 2.

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.

On-orbit maintenance is essential for ensuring the long-term health and operation of spacecraft such as space stations and manned spacecraft. In the future, space robots will play a significant role in the on-orbit maintenance of spacecraft. Accurate pose estimation of spacecraft components is a prerequisite for space robots to perform on-orbit maintenance tasks, and it faces challenges such as unknown models, high real-time requirements, and the impact of complex lighting conditions in space. To address these issues, this paper first systematically reviews computer vision and deep learning-based pose estimation methods, analyzing the applicability of different methods in space missions. Building upon this foundation, a pose estimation method for spacecraft components based on viewpoint similarity is proposed. This method utilizes a vision transformer model to construct a reference viewpoint selector, combined with epipolar geometry constraints to achieve rapid estimation of the rough pose of target components. Then, precise estimation of the target component's pose is accomplished through viewpoint similarity weight allocation. The proposed method does not rely on target models, enhances algorithm robustness through similar viewpoint selection, and has been validated on a constructed dataset of spacecraft components. This method can provide methodological support for future intelligent and autonomous on-orbit maintenance by space robots.

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.

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.

Before the application of the controlled ecological life support system on Lunar or Mars bases, technical verification must be conducted on China Space Station to address the scientific and engineering challenges that arise during the application process. This article studied the task requirements and constraints for conducting the controlled ecological life support system, clarified the technical verification objectives, and developed in orbit specific technical verification approaches and scenarios. For the technical verification of efficient plant cultivation in the first state, technical process, verification contents, ground test scenario, facility development, and in orbit verification scenarios have been studied and clarified. The preliminary tests were carried out, with the selection of the plants varieties. Aeroponics cultivation and microbial control were also verified.

The variable gravity pool boiling experiment is one of the scientific experiments within the varying gravity rack of the Wentian experiment module of the China Space Station (CSS). It investigates the heat transfer performance and bubble dynamics during pool boiling are studied under varying gravity conditions. As a key component developed independently, the multi-functional integrated micro-heater (MIM) was fabricated using micro-electro-mechanical system technology. It features a 10 mm×10 mm×1 mm quartz glass substrate, on which several platinum thin films with specific structural parameters were fabricated to integrate multiple functions, including bubble triggering, temperature measurement, and power input. The chip-on-board packaging technology was used to form it as a separate component. The characteristic resistance-temperature curves of the local temperature sensors and the main heater of the MIM were calibrated using the on-orbit experimental data obtained aboard the CSS. The synchronized measurement data of the bulk liquid temperature within the boiling chamber served as the reference temperature data. The temperature uncertainty of the MIM was also analyzed. The single-phase natural convection heat transfer performance in different gravity conditions, obtained aboard the CSS, was calculated. These results were consistent with the predictions of the common-used empirical correlations and similar experimental data, indicating that the present space experimental results are reliable.

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.

In response to the technical requirements for powder level measurement for in-situ space resource utilization, this study proposes a level measurement method based on interdigital capacitors. The measurement characteristics were experimentally investigated with lunar regolith simulant in a vacuum environment. The results indicate that the capacitance of the interdigital capacitor varies linearly with the powder level, exhibiting a sensitivity parameter ranging from 10⁻¹ to 10⁰ pF/mm. This sensitivity is influenced by electrode structure parameters and powder layer thickness, with the electrode spacing and insulating layer thickness having the most significant impact. To achieve a higher sensitivity, smaller electrode spacing and insulating layer thickness should be used. Additionally, for a given electrode spacing, there exists an optimal electrode width that maximizes the sensitivity parameter. This study demonstrates that interdigital capacitors are suitable for measuring the powder of level of lunar regolith simulant in a vacuum environment. Furthermore, their underlying working principle suggests potential applications in powder arching detection and powder layer thickness measurement in future space missions.

During human space exploration, small-micro power generation technology for space heat sources can be used without relying on solar energy and is a useful option for deep space exploration missions, including manned Moon landings and Mars landings. The Tesla turbine, as a simple micro-expander, has great potential to play an important role in the field of small micro-generation, thanks to its unique structure and principle. In this study, the performance of the Tesla turbine is experimentally tested under different medium and low temperature heat source temperatures, flow rates, and loads. The experimental results indicate that the Tesla turbine and its accompanying power generation equipment, can achieve more than 60% isentropic efficiency and more than 95% shaft efficiency under different operating conditions at pressures below 1.4 MPa, respectively. It provides experimental basis for the future research and application of Tesla turbine.

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.

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.

Compared with unmanned spacecraft, manned spacecraft information systems must not only perform essential functions including system state monitoring, data routing, and command execution, but also address the human-in-the-loop coordination requirements inherent in crewed operations. With the increasing orbital longevity and mission complexity of contemporary spacecraft, three operational imperatives have emerged as critical challenges for manned spacecraft information systems: optimization of crew habitability during extended missions, enhancement of in-orbit operational efficiency, and improvement of multi-task management capabilities. To address these challenges, researchers have implemented advanced civilian technologies such as cloud computing and smart home in spacecraft environments, thereby generating different technical requirements spanning network bandwidth, latency tolerance, terminal density, and human-machine interface modalities. This study proposes a unified intelligent system design framework that holistically addresses four critical dimensions: system architecture, network protocols, seamless mobility, and system expandability. The proposed methodology demonstrates effective accommodation of diverse technical demands under resource-constrained multi-mission scenarios while maintaining system robustness.

This paper investigates the dynamics and control challenges associated with the deployment of a three-body tethered satellite system. For dynamic analysis and control purposes, two types of models are established. Initially, the relative attitude motion between the main satellite and the tether is considered, leading to the establishment of a simplified system model for controller design based on the dumbbell model assumption. Moreover, considering the flexibility of the tether and the satellite attitude, an accurate system model for dynamic analysis was established based on the spring-mass model assumption. In order to achieve the stable deployment process of the three-body tethered satellite formation system, a synthetic control strategy is proposed. First, taking into account the complex state of the system and the control input constraints during the deployment process, a nonlinear model predictive control method is proposed based on a simplified model. The control trajectory for the tether's elastic force and propulsion force is solved by the nonlinear programming method. To address the the control error resulting from trajectory tracking, a proportional-differential feedback controller is proposed to stabilize the system attitude and configuration. Finally, numerical simulations are presented to analyze the nonlinear dynamic behavior of the system during the deployment process and to verify the effectiveness of the control strategy.

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.

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.

To achieve dual-band imaging in the visible spectrum and near-infrared spectral ranges for a spaceborne multispectral camera, while adhering to the satellite payload requirements for volume, weight, and structural envelope, a compact coaxial catadioptric optical system with a shared optical path for multi-band imaging is designed. The system boasts a focal length of 1500 mm and a field of view of 1.37° × 1.37°. The average Modulation Transfer Function (MTF) across the full field of view exceeds 0.27 (at 55 lp/mm), ensuring clear imaging within the spectral range of 400~900 nm. Meanwhile, given the complex ambient light conditions in the space environment where the camera operates, stray light analysis is performed based on the spatial layout characteristics of the system. Key stray light paths are identified, and the primary and secondary mirror baffles, as well as the material properties of the optomechanical structure, are optimized. These enhancements further improve the stray light suppression capability of the optical system, ensuring that the Point Source Transmittance (PST) outside the avoidance angle of 45° is better than the 10⁻⁶ level. To meet the volume and weight requirements of spaceborne payloads, the system's stray light suppression is optimized to achieve the best possible performance without compromising the imaging quality of the space camera.

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.

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.

Named Entity Recognition (NER), a fundamental task in natural language processing, aims to automatically extract entities with specific meanings from texts. In the domain of space science, NER technology provides foundational support for critical tasks such as parsing massive space exploration data, analyzing aerospace mission reports, and mining astrophysical literature. This paper specifically focuses on the technical adaptation and optimization requirements of NER in scenarios including satellite payload parameter extraction, deep space exploration target identification, and space environment monitoring report analysis. We review the developmental status of NER technology, analyzing its evolution from early rule-based and machine learning methods to current deep learning-driven models. Special emphasis is placed on the unique applications of deep learning models in space science text processing, covering key technologies such as compound entity recognition in detector logs and multimodal spatial data fusion. Additionally, this paper highlights the major challenges faced by NER in space science, including handling multilingual mission reports, disambiguating space-specific terminology, and meeting real-time processing requirements for onboard devices. Finally, we propose a development roadmap for NER technology in space science research, offering technical support for future critical needs such as space station scientific experiment data management and planetary exploration target identification.

Photothermal melting and forming technology is a novel in-situ construction and manufacturing method. It utilizes focused beams to heat and melt lunar regolith along predefined paths, followed by solidification to achieve structural formation. This technology eliminates the need for binders and secondary energy conversion, enabling efficient utilization of in-situ lunar regolith and solar energy, which holds significant implications for the construction and long-term operation of future lunar research stations. This paper summarized the research progress in lunar in-situ construction and manufacturing technologies, details the characteristics and application prospects of the photothermal melting and forming technology, and analyzed existing challenges such as forming defects and unclear melting mechanisms in vacuum environments. To address these issues, a high-vacuum photothermal melting and forming experimental system was developed. For the first time, 3D printing of lunar regolith simulant was achieved under an ultra-high vacuum (10⁻³ Pa), successfully fabricating a 5 cm × 5 cm × 3 cm part. In-situ observations during the experiments revealed the dynamic evolution of molten pools in vacuum. The research not only verified the feasibility of lunar regolith photothermal forming under high-vacuum conditions but also established critical process parameters for regolith melting-based additive manufacturing. These findings provide essential technical foundations for developing specialized equipment for extraterrestrial additive manufacturing.

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.

Energy storage battery technology has been developed by leaps and bounds in recent years. As an electric guarantee for space vehicles, the maturity of energy storage batteries must be very high. However, rapid upgrading makes it unable to be fully verified on vehicles. The successful establishment and stable operation of the space station have provided a powerful platform for the in-orbit application verification research of new energy storage battery technologies. This article proposes a new in-orbit application verification for energy storage battery, including lithium-ion battery pack 1, lithium-ion battery pack 2, charge and discharge controller and discharge load. Using the mode of charging and discharging each other by two battery packs, two kinds of energy storage battery technologies can be verified at the same time, and the optimal use of energy can be achieved, only a small amount of energy loss needs to be supplemented by space station. The platform will provide a strong support for the replacement of the new energy storage battery technologies in the space vehicles.

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.

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.