The research and development of key technologies of manned lunar bases home and abroad were summarized in this paper. The landmark events and achievements of lunar exploration and lunar base research were studied. The four basic principles of lunar base construction were proposed, based on which the overall planning scheme and six major systems of the manned lunar base located in the polar region of the moon were developed. In addition, a number of key technologies were extracted from the aspects of lunar resource exploration and development, energy utilization and environmental control, life and health, lunar surface communication and intelligent technology, carrying and transportation, operation and maintenance and simulation. Finally, based on the research status of key technologies and the actual needs of the construction of lunar bases, the shortcomings of this research were summarized, to provide suggestions and prospects for the construction, operation and maintenance of future manned lunar bases.

Based on the requirements on the structural and functional materials used for the construction of lunar base, this paper discusses the feasibility of using lunar soil to prepare corresponding fibers to achieve this ambitious goal, and the latest progress in this field is reviewed. The unique advantages and application prospects of lunar soil fibers for structural protection, survival and life support in the lunar bases are then analyzed. Finally, theoretical and technological issues for future research and breakthroughs in the development of lunar fibers are proposed, in an effort to promote the prosperity of this promising field in both fundamental and applied research.

In this paper, a space-based orbit determination and time synchronization method for Earth-Moon spacecraft was presented. As a “space-based tracking station”, LEO satellite on the one hand receives GNSS navigation signals to achieve high-precision real-time orbit determination and timing；on the other hand, it establishes measurement links with Earth-moon space spacecraft to support the fast and high-precision orbit determination of Earth-moon spacecraft. Compared with ground stations, LEO satellites operate at a faster speed and orbit the Earth in a shorter period. The Earth-Moon spacecraft and its measurement link have the advantages of short invisible time interval, better measurement geometry, and no atmospheric delay in the measurement process. Therefore, using LEO satellite can improve the convergence speed and accuracy of orbit determination. This paper analyzed the space-based orbit determination and time synchronization performance of three typical orbits in Earth-Moon space, including the distant retrograde orbit (DRO), the highly elliptical orbit (HEO) and the Earth-moon transfer orbit. Space-based orbit determination simulation results show that when the LEO satellite position accuracy is high, the convergence time of the three orbits is less than 3 hours, the orbit position accuracy is about 50 m, and the time synchronization accuracy is tens of nanoseconds. Therefore, this method can hopefully solve the problems of limited deployment and heavy burden of ground stations.

Lunar water and other volatiles in permanently shadowed regions are not only key elements to studying the early history of the Moon and solar system, but also important sources for in-situ resource utilization for future lunar base construction. In this study, we compute the illumination rate of 2026 and slopes within a 15 × 15 km area near the lunar south pole based on the 20 m/pixel digital terrain model (DEM). We propose to use the illumination rate and slope to constrain landing area selection based on a finer map meshing within the study area and find that the distribution of potential landing areas varies with different constraints. We also extend the study area to polar regions ($ > 88.5^{\circ} $) based on the 60 m/pixel illumination rate map and DEM data. The result shows that there are 8 potential landing areas including three at the Shackleton crater rim, two at the de Gerlache crater rim, two at the ridge between the former two craters, and one at the ridge between the Shackleton and Slater craters. Our study provides candidates for future polar landing missions and a method for landing site selection from higher DEM data.

The manned lunar research station is an important basic facility for achieving medium- and long-term deep lunar exploration, and at the same time is a system project with multiple complex challenges. In this paper, from an architectural perspective, design constraints at macro, meso, and micro levels were analyzed first, and an implementation method for the architectural design of the manned lunar research station was provided using systems engineering, which consisted of four dimensions: the overall goal is “safety, sustainability, and intelligence”; the application ideas included process integration, model visualization, and design modularity; the application advantages are high efficiency, accuracy, and integration; the application framework was divided into application layer, model layer, and data layer. Finally, a three-dimensional structural model of architectural design system engineering was constructed, which included time dimension, logic dimension and knowledge dimension, and comprehensively embodied the structure of each task and related scientific knowledge in each stage, aiming to provide new perspectives and new ideas for the construction of manned lunar research station.

With the continuous progress of human society and the rapid development of aerospace science and technology, cislunar exploration and exploitation is entering the stage of large-scale and industrialization. Cislunar aerospace transportation system is an important component of large-scale cislunar exploration and exploitation, supporting various activities of cislunar exploration and exploitation. Firstly the global development status and trends of cislunar aerospace transportation are introduced in this paper. Then the composition of the cislunar aerospace transportation system is given, and the capacity demands in the future are predicted based on an analysis of future development needs. Facing to the large-scale and low-cost cislunar aerospace transportation in future, One-stop solution and Relay-style solution are proposed. At last according to the typical mission requirements of lunar landing and return, the propellant refueling and system scale requirements of two solutions are analyzed. The paper will provide reference for cislunar aerospace transportation system development.

When the lunar rover in the future performs complex tasks such as shadowed regions detection and autonomous sampling and return under weak communication conditions in the lunar south pole, the demand for high-precision autonomous navigation system will become more urgent. Taking into account the safety guarantee of the lunar rover and the lunar environmental factors with navigation benefits, a new fusion path planning algorithm for high-precision autonomous navigation was proposed in this paper, by integrating a global auxiliary path based on optimized A* algorithm with Dynamic Window Approach. With location error of simultaneous localization and mapping based on lidar serving as an evaluation index, a numerical simulation and a semi physical experiment were established to verify the feasibility of this algorithm and the effectiveness of improving navigation accuracy of the rover in different application scenarios. Experiment results show that compared with traditional path planning algorithms with single factor considerations, the average absolute location error of simultaneous localization and mapping algorithm in the two-dimensional plane was reduced by a maximum of 42% when the lunar rover moved along the path planned by the proposed algorithm, which can provide technical support for autonomous navigation and path planning tasks in the complex environment of the lunar south pole.

In recent years, international lunar exploration has mainly focused on the south pole of the Moon. Chang’E-7 (CE-7) mission, through the development of orbiter, lander, rover and hopper, will achieve a comprehensive exploration of the lunar south pole including surrounding, landing, moving, and leaping. The harsh lighting conditions, terrain conditions, and temperature conditions at the lunar south pole have brought many challenges to the design of the spacecraft. CE-7 spacecraft has broken through a series of barriers with advanced technologies including high-precision fixed-point soft landing on complex terrain, lunar surface leaping, lunar landing and walking, global perception and mission planning, and fidelity sampling of water ice and volatiles. It has laid a solid technical foundation for the smooth implementation of the mission and the subsequent aerospace cause in our country.

The lunar South Pole region’s limited illumination, extensive shadowed regions, and homogenous surface features with weak textures pose significant challenges to stereoscopic image matching and 3D terrain reconstruction. To address these issues, an Efficient Confidence-guided Stereo Matching (ECSM) algorithm was proposed. This algorithm improved matching precision and efficiency by assessing the confidence of non-support points, updating the support point dataset, constructing a triangulated mesh, and recalculating disparities within triangle vertices based on their confidence levels. On this basis, a photogrammetric method for lunar 3D terrain reconstruction was established. High-resolution image data from the Lunar Reconnaissance Orbiter’s Narrow Angle Camera was utilized for validation experiments conducted in the vicinity of the Shackleton crater within the lunar South Pole region. Qualitative and quantitative analyses of disparity maps and Digital Elevation Model (DEM) generated from different stereo matching algorithms demonstrated the reliability of the proposed algorithm in regions with weak and repetitive textures. Comparative analyses with the German Aerospace Center’s DEM and NASA’s Lunar Orbiter Laser Altimeter DEM (LDEM) for the same region revealed significant consistency in elevation and slope information, affirming the practicality and effectiveness of the proposed method. This study provides a methodological foundation for landing site selection for lunar South Pole explorations.

Based on multi-sensor data from star sensors and inertial sensors, a high-performance Kalman filtering algorithm with linearized quaternion measurements was proposed in this paper. According to the ultra-stable and ultra-static platform characteristics of the task, new pseudo-linear measurements were constructed by an approximate transformation for quaternion measurements under small angle change of the spacecraft so that the linear assumption of Kalman filtering was satisfied. Combined with the discrete-time state space model of spacecraft system and the multi-sensor measurements, a Kalman filtering algorithm with linearized quaternion measurements was designed, to achieve high-precision in-orbit state estimation of spacecraft system. The simulation experiments are provided to demonstrate the effectiveness of the proposed Kalman filtering algorithm, which meets the precision requirement of spacecraft attitude estimation for space-based gravitational waves detection and provides the high-precision observation for spacecraft attitude control.

The widespread impact craters and other concave obstacles on the lunar surface are the key factors threatening the safe landing and roving of the lunar rover. Once trapped, it will bring risks of tilt, landslide, and even rollover to the lunar rover. Therefore, the effective recognition and detection of lunar concave obstacles are conductive to obstacle avoidance, and provide necessary information reference for the safe landing and roving of the lunar rover. Based on the concave obstacles’ feature that there is a one-to-one matching between the shadows and the highlights in the sun, an automatic recognition and detection method for the lunar concave obstacles is proposed. The adaptive dual threshold method is used to automatically separate the shadows and the highlights of the concave obstacles from the background. Each shadow and highlight are clustered the specific position and one-to-one matched using the sunlight direction with the prior forecast information involved. Then the rough extraction of every single concave obstacle are obtained. Finally the original sub-images sequence containing every single concave obstacle is traversed for edge detection and ellipse fitting, which can avoid mutual interference of multiple obstacles and effectively detect the locations and ranges of all concave obstacles.

It is crucial to directly confirm the presence of water by detecting water ice and its content in the lunar polar region in situ. Spectroscopy and mass spectrometry are both important tools for identifying and quantifying material composition. They can complement each other to achieve comprehensive detection of water ice, volatile content, and H isotope abundance in the lunar polar region. The paper introduces the spectroscopy and mass spectrometry technique with Luna 25, Luna 27 and Viper as examples of typical in-situ detection applications. It includes the detection mechanism, operating mode and instrument functions, performance and applications. In last, we provided a brief introduction to the upcoming application of the “Chang’e-7” lunar polar region water molecule analyzer. This instrument comprises a laser absorption spectrometer, which is responsible for the in-situ analysis of H₂O and HDO, and a time-of-flight mass spectrometer that enables the analysis of gas molecules with mass numbers < 200 amu, such as H₂O and CH₄. The scheme can support in-situ analysis of water ice for lunar south pole landing missions.

First, the natural advantages of lunar lava tubes and the research on extraterrestrial farms were summarized. Then key technologies for in-situ resource utilization of the moon were summarized, the basic idea for lunar farm construction in lunar lava tubes was given, and a layout of lunar farm based on lunar lava tube was put forward. Finally, the technical difficulties for lunar farm were discussed. This paper provides new reference for lunar farm construction in lava tube.

To exploit water ice in-situ resources in lunar polar region, a design method of heat pipe array’s layout was proposed in this paper. Firstly, the heat pipe array was presented according to the water ice mining scheme, and heat conduction process of heat pipe array was numerically solved by three-dimensional finite difference method. Secondly, the objective function of water production and heat flow consumption was established. Genetic algorithm was used to optimize the layout of heat pipe array, and the optimal solution of heat pipe’s layout was acquired by iterative search. Simulation results show that the optimal layout of heat pipe array could obtain maximum water production with minimum heat flow consumption. Besides, mass of water ice collected in a task and total time required were given. The application of this design method to life support system of lunar base can improve the efficiency of polar in-situ resources’ collection.

In situ high-precision analyses of volatile abundance in lunar soil in the lunar polar regions require micro-quantification of test samples. In this paper, a sampling shovel scheme based on the end of a robotic arm was proposed. A shallow lunar soil profile was constructed by progressive shovel digging, micro-quantitative collection of lunar soil samples at fixed depths was achieved through the configuration of a fixed-capacity sampling chamber, and the shovel teeth could be used to scrape the debris formed by the water ice of the lunar soil for sample collection in extreme cases. To verify the feasibility of the sampling scheme, a simulated lunar soil profile shovel-digging sampling efficiency test platform was built, and progressive shovel-digging, fixed-capacity micro-sampling, and vibratory sampling tests were carried out. These tests show that the sampling shovel has the capability of constructing a 130 mm deep profile and a 200 ± 30 mg micro-quantitative sampling function. The research results provide a feasible scheme for the exploration and analysis of China’s lunar soil sampling in the polar regions of the Moon.

In response to the complex joint power supply testing mode, diverse inter spacecraft and ground communication scenarios, and high requirements for simulation flight test design and verification caused by the collaboration, high complexity, high coupling, and high intelligence of Chang’E-7 lunar probe, the difficulties in system level electrical testing were analyzed, and a digital testing and verification strategy for multi vehicle collaboration was proposed. It includes a model based intelligent safety auxiliary testing for multi device joint power supply, a multi scenario high autonomous measurement and control data transmission testing system based on multi-source data autonomous decision-making, and a flight program-simulation flight test design verification system, which changes the current situation where complex system level electrical testing mainly relies on manual or traditional single satellite automated testing technology. It was applied to the development of Chang’E-7 lunar probe, to provide strong support for fully verifying the correctness, consistency, and stability of the functions and electrical performance indicators of the lunar south pole probe, achieve comprehensive, reliable, and efficient testing and verification, and promote spacecraft testing to move further from traditional automated testing of single spacecraft to collaborative intelligent testing of multiple spacecraft.

In this paper, a hierarchical reconstruction modeling method and a two-layer optimization algorithm based on discrete orbit data were proposed to solve the multi-pulse orbit transfer problem under the Earth-Moon circular restricted three-body model. The minimum pulse problem was reconstructed and modeled as a two-layer optimization problem, and the two-layer optimization algorithm was given to realize the transfer orbit design. The upper layer optimization problem took the discrete orbit data constraints into account, and the algorithm adopted intelligent algorithm to make it universal and achieve computational efficiency. The lower optimization problem only optimized the pulse sequence under the constraints of start-end state constraints, time constraints, pulse constraints and pulse point constraints, so as to avoid the sensitivity to the initial value. The algorithm can obtain the local optimal solution by sequential quadratic programming. Through simulation verification in various scenarios, it can be concluded that the two-layer optimization modeling framework and solution algorithm proposed in this paper are suitable for different types of orbit transfer, and can achieve multi-pulse energy optimal transfer. Comparison simulation is of great significance to transfer orbit design between special orbits in the Earth-Moon three-body system.

Formation interferometry near the Sun-Earth libration point is an essential direction for developing high-precision astronomical observation. Keeping the formation configuration stable for a long time is the premise of achieving high-precision measurement. However, the solar radiation pressure will disturb the satellite’s orbit, which challenges the formation configuration’s stability. This paper studies the stable region of formation motion near the libration point under the influence of solar radiation pressure. Based on the Sun-Earth three-body model considering solar radiation pressure, then linearizing the dynamic equation near the reference trajectory of the formation, the analytical expression of the zero relative radial acceleration region near the chief satellite is derived. It is found that the zero relative radial acceleration region is a quadric surface passing through the reference trajectory. The evolution characteristics of zero relative radial acceleration region are further analyzed, and the variation law of region distribution with reference trajectory type, amplitude, and phase is given. Finally, the formation configuration evaluation indexes such as shape, size, and coplanarity are defined. The formation configuration design and control method based on zero relative radial acceleration region is proposed and applied to the design of the five-satellite formation mission. The simulation results show that the formation configuration is bounded within 70 days, and the change rate of the relative distance between the chief satellite and deputy satellite is less than 2% in the first 60 days. In this paper, the study of zero relative radial acceleration region under the influence of solar radiation pressure can provide a basis for designing future Sun-Earth libration point interferometry formation orbits.

In order to solve the trajectory planning problem of the launch vehicle during the large-scale lunar transportation, which involves vertical takeoff and landing, multiple maneuvers, and high landing accuracy requirements. Firstly, the equations of motion of the vehicle's center of mass are established, and a large-scale trajectory optimization model is constructed considering initial position, terminal position, velocity constraints, and thrust constraints. The nonlinear optimization problem is linearized and discretized using convex optimization methods; Secondly, the large-scale optimal trajectory planning problem is converted into a bilevel convex optimization problem. The optimization problems in the dynamic ascent phase, the large-scale dynamic flight phase, and the vertical descent phase are treated as the inner layer convex optimization problems, and solved using the interior point method. At the same time, combined with the fuel optimization purpose, the objective function is designed as the outer layer convex optimization problem, and iterative calculations are performed using the gradient descent method, obtain the optimal fuel trajectory for a wide range of vertical takeoff and landing. Simulation experiments show that the algorithm proposed in this paper ensure the vertical landing of the vehicle which meets the requirements of high-precision landing. Monte Carlo simulation is conducted considering position errors, and the results show that the algorithm has good robustness.

China’s deep space exploration has gradually developed from technology and science-driven to the stage dominated by science, leading to technological advances. Under our demand for high-quality development in deep space exploration, the Mega Interconnected Knowledge System in Deep Space Exploration (MIKSE) was innovatively proposed with its concept and scheme conceiving. Centering around the scientific goals, deep space exploration engineering, science, technology, and big data in the application were collected, techniques including artificial intelligence and cloud computing were utilized to perform organic organization, information association, and knowledge mining on relevant elements, a large model with genealogical associations and networks of connections was built, and an intelligent big knowledge platform was established. With the help of this platform, historical data and its current capabilities can be fully utilized to support generative knowledge and information for the future planning and development of deep space exploration and promote the paradigm shift of data-driven deep space research.

As solar radiation is an important source of energy received by the surface of the planets in the solar system, accurate modeling of solar radiation on the surface of Ceres is crucial for studying the thermal environment. However, the highly undulating terrain on Ceres makes determining terrain shading coefficients challenging. While the ray tracing method can accurately determine terrain shading coefficients, it is limited by the search radius. In the paper, it examines the effects of seasonal differences, landform types, and study area size on solar radiation simulation, and concludes that a minimum threshold search radius of 74 km is required to determine actual terrain shading. Using this radius, the paper simulates solar radiation over a solar day and finds that the search radius required for accurate shading information varies with time of year and landscape type. Surface faults are most consistently influenced by the search radius, while volcanic landscapes are most significantly influenced. The global solar radiation distribution of Ceres shows a gradual decrease from low to high latitudes. Results improve the theory and method of solar radiation modeling and provide data and theoretical support for future exploration of Ceres.

The aqueous alteration spectral features of carbonaceous chondrites for were studied for future volatile-rich asteroids exploration and remote sensing. The 1-20 μm infrared spectral features and petrographic characteristics of 15 carbonaceous chondrites with different alteration degrees were analyzed, and the spectral variation laws of the aqueous alteration were summarized. The findings demonstrate that as the degree of alteration of carbonaceous chondrites increases, the 3 μm absorption band, which indicates phyllosilicates and water molecules, and the 6 μm absorption band, which indicates only water molecules, both features increasing in strength and absorption centers shift to the short-wave. With more alteration, the 3 μm absorption band sharpens and resembles serpentine’s 3 μm absorption feature. However, as the degree of alteration increases, the 6 μm absorption band shape does not significantly change. The degree of alteration also affects the spectral shape of the 10-13 μm region. This region indicates silicate features. The 12.4 μm /11.4 μm reflectance ratio reduces as a result of the conversion of anhydrous silicates to phyllosilicates. Also discuss possible effects that the spectra and parameters discovered during this study may have on the outcomes from asteroids.

A lot of dust particles are ejected from the surfaces of the Jovian irregular moons by the impact of interplanetary meteoroids. In this paper, the dynamics of dust particles originating from the irregular satellites in the complicated Jupiter system with various perturbation forces were studied, using both the analytical method and the numerical simulation method. By analyzing the conserved effective Hamiltonian quantity and phase portraits in the orbit-averaged model that describes the long-term evolution of motion of dust, it is concluded that dust particles originating from the prograde satellites tend to be distributed in the direction away from the Sun, while dust particles originating from the retrograde satellite are predominantly distributed in the direction towards the Sun. With long-term numerical simulation, it is found that the orbits of particles originating from prograde satellites are more stable than those of particles originating from retrograde satellites, and the orbital stabilities of large-size dust particles are greater than those of small-size particles.

The reflection spectra of satellites are shifted to short wavelengths when seasonal scintillation caused by solar wings occurs, and the shorter wavelength UV band has potential advantages in space target solar wing detection. The space target detection signal-to-noise ratio and detection distance models were developed for space target detection. For the most influential material properties in the model, the spectral reflectance of typical satellite materials and solar wing cell materials in the UV and visible bands were measured, and other influencing factors such as detector and deep space background in the model were also analyzed. Using the SJ-5 and Skynet 5D satellites as examples, it was verified that there was indeed a significant advantage of UV in solar wing detection. The results show that compared with the main body visible detection of the satellite, the solar wing UV detection signal-to-noise ratio is enhanced by 1.3~1.6 times, and the detection distance can be increased by 1.5~1.8 times by the combination of UV and visible light. UV has obvious technical advantages over visible light in detection scenes such as Earth’s limb, occultation and engine tail flame detection during satellite deorbiting, thus UV detection has the obvious advantages of cost-efficiency ratio and detection capability in space target detection.

Soft landing exploration is an important method for exploring extraterrestrial objects, and guidance, navigation and control (GNC) is the key to successful soft landing of extraterrestrial objects. Firstly, the development status of soft-landing missions of foreign and domestic celestial bodies such as Moon, Mars, and small celestial bodies was reviewed. On this basis, the typical GNC schemes for soft landing missions of extraterrestrial objects and the main progress of autonomous navigation and control technology were summarized. Finally, the key technologies for autonomous navigation and control that require special attention and development were proposed for future pinpoint soft-landing missions of extraterrestrial objects, in order to provide the experience and reference for future technological development.

The Queqiao relay satellite which is located in the Halo orbit at Earth-Moon L2 libration point，needs to maintain its configuration by wheel off loading and orbit maintenance every 3-4 days. According to the orbit characteristics of the libration point，the influence of the component of the orbit determination error for the orbit control parameters is analyzed in the rotating coordinate system，and it is concluded that the orbit determination error affecting the orbit maintenance effect mainly concentrate on the velocity error of X-Y plane. In this paper，an orbit determination accuracy evaluation method for orbit maintenance control is proposed，the strategy of orbit determination is designed，and the influence of different strategies on orbit determination is evaluated. The orbit accuracy of the relay satellite in mission orbit is evaluated，and the results show that it can provide 1-3 mm/s velocity accuracy for orbit maintenance under the existing TT&C conditions.

To overcome the difficulty of absolute optical navigation in unknown environments, an intelligent fusion autonomous navigation method for Mars precise landing was proposed. Considering the difficulties of the inability to detect features and the low efficiency of recognition brought by high texture similarity in the extraterrestrial environment and perspective scaling between images, an unsupervised homography network was constructed to estimate the inter frame motion of the lander. Based on the inertial measurement information, a recursive model of the lander state was established. Using the established measurement model and state recursive model, real-time estimation of the lander position, velocity, and attitude was achieved through UKF. The simulation results verify the effectiveness of the proposed method without the need of feature detection and matching.

Only one vision sensor is incompetent for estimating the motion state of small body. In order to solve this problem, a small body motion state estimation method based on the fusion of camera and LIDAR was proposed. Firstly, a fused camera and LIDAR measurement model was built. By tracking image feature points with depth information, extended Kalman filter was used to estimate the spin angular velocity, spin axis direction, position and velocity of small body. Secondly, a feature fusion matrix was designed to achieve real-time updates of image feature points, point clouds, and fused feature points. Thirdly, the effectiveness of this algorithm and the impact of the number of feature points, observation height, and noise on the algorithm were analyzed. Simulation results show that the accuracy of the proposed algorithm is significantly higher than that of the spin parameter estimation algorithm of small bodies based on monocular camera.

Mapped Chebyshev pseudospectral convex optimization approach was proposed for Martian ascent trajectory optimization. Firstly, the lossless convexification technique was used to convexify the fuel-optimal problem of Martian ascent. Then, the convexified problem was discretized at mapped Chebyshev-Gauss-Lobatto points and interpolated by the barycentric rational interpolation techniques. Finally, the sequential convex optimization method was used to solve the convex problem iteratively to obtain the numerical optimal solution. Simulation results show that the proposed method is superior to the classical sequential convex optimization method in computational efficiency, and effectively improves the ill-condition of standard Chebyshev differential matrices.

The principle of radio frequency ion thrusters（RIT），as well as the research history and achievements of micro-newton and milli-Newton RIT at home and abroad in the past 60 years，was explained in detail. The radio frequency ion propulsion system involves a number of key technical challenges. Preliminary solutions to the problems of propellant selection， radio frequency（RF）circuit impedance matching，gas flow control，electrical neutralization control and lifetime were proposed， and the development trend and research direction were put forward combined with the future application of RIT.