Solar system boundary exploration is of great significance to obtaining important scientific discoveries，promoting strategic and forward-looking technological breakthroughs，and enhancing human space exploration capabilities. On the basis of introducing the definition and future plans of Solar system boundary exploration missions，this paper analyzed the mission characteristics，studied the current mission requirements and technical challenges，and systematically discussed artificial intelligence technologies that need to be broken through，including intelligent processing of exploration data，intelligent perception of environment，event and state and control，intelligent planning of exploration missions，and lightweight and reliable intelligent algorithms. This paper can provide reference for the planning，demonstration，development，and implementation of Chinese Solar system boundary exploration missions.
In the face of the challenges of the extreme environment on Mars，this paper systematically combed the key considerations of Mars base siting，analyzed the distribution and availability of in-situ resources on Mars，such as water-ice，minerals，atmosphere，energy，etc.，and discussed in detail the siting strategies for Mars impact craters，canyons and grooves，plains and highlands based on a comprehensive assessment of engineering elements related to base construction，such as landing buffer technology，terrain survey technology and construction，operation and maintenance technology. Drawing on the rich data accumulated by Mars exploration missions in recent years，the environmental characteristics of alternative landing zones were summarized in depth，providing multi-dimensional referrence for base site selection. At the same time，the limitations and future development direction of Mars base siting for in-situ resource utilization were accordingly pointed out，in hope of providing reference for future Mars base siting planning.
Based on the problem of impacting and flying alongside a near-Earth asteroid with a single launch vehicle，a model for the coordinated optimization of the trajectories of two is proposed. The optimization objective is to minimize the weighted velocity increment of the two spacecraft. An optimization framework for the flight trajectories of the two spacecraft，which are by a single launch vehicle and fly alongside each other before impacting，is given. Constraints such as launch C3，the impact relative velocity，and the impact sun angle are considered. The impact probe can use two transfer forms，one is direct transfer and the other is Earth flyby. This paper has optimized 15 candidate asteroids in the 2025 window and provided feasible engineering design solutions. The results can provide theoretical reference for China's asteroid defense mission.
To meet the requirement of adhesion detection on the surface of extremely weak gravitational small celestial bodies，a three-legged detector attachment buffer system was designed，and a stability analysis of the attachment process was carried out. In order to achieve stable attachment to the surface of the small body without rebound in a very weak gravitational environment，a two-stage buffer system was designed considering with the error of landing speed and inclination angle taken into account. The energy consumption of the hook and loop fastener and the crushing energy absorption of the aluminum foam were used to reduce the influence of the contact collision process on the stability of the detector. The multi-body system dynamics model of the detector and the contact collision dynamics model of the detector footpad-granular medium were established. Based on the joint simulation of multi-body dynamics and discrete element，the motion law of the detector under different landing inclination angles and speeds was obtained. The results show that the two-stage buffer system has a good buffer energy absorption effect，which can effectively prevent the detector from rebounding，slipping and overturning. The detector can be stably attached to the surface of the small celestial body within a certain inclination angle and velocity range. The research results can provide technical support for the landing scheme design of small celestial body exploration missions in the future.
The motion state and parameter estimation of small celestial bodies are important prerequisites for the successful implementation of small object attachment and sampling detection. Key parameters such as rotational angular velocity，inertia ratio and principal axis direction of small celestial bodies need to be obtained. However，due to the lack of markers and communication，and the typically tumbing motion of small celestial bodies，which are typical non-cooperative targets in space，estimating their motion state and parameters becomes a highly challenging task. In this paper，it is proved that the angular velocity，inertia ratio and other parameters of the attitude motion of the non-cooperative target in space are fully observable only by monocular sequence images，and the parameters such as the attitude motion and inertia ratio of the non-cooperative target are estimated by mathematical simulation，and the effectiveness of the method is verified by mathematical simulation.
Aiming at the characteristics of 1 GHz bandwidth Chirp transform spectrometer with high time resolution and narrow pulse width，as well as the demand for detection of weak signals，a real-time and high-precision back-end timing synchronization and pulse accumulation scheme for CTS system is proposed，which also has the advantage of adjustable integration time. The scheme achieves the synchronization control between the analog and digital parts of the 1 GHz bandwidth CTS system and the precise accumulation of 1 ns narrow pulse in the back-end through system clock design and FPGA algorithm design，in order to ensure that the system achieves a high frequency resolution. Through this synchronization scheme，The average in-band pulse width of the system after accumulation is 1.0136 ns，and the corresponding frequency resolution is 101.36 kHz，which is comparable to the resolution of the CTS carried by the JUICE of ESA，and provides an effective solution to realize the high-precision spectrum analysis of China's deep-space exploration mission.
To address the problem of heavy computational tasks and lengthy processing times in gravity field inversion，a parallel matrix computation method based on multi-GPU integration with CUDA was proposed. This method achieved highly parallel dense computation，significantly reducing the time required for inverting large matrices in planetary gravity field inversion by accelerating matrix multiplication and inversion operations. The computation rate was 191 times faster than that of using CPU. Moreover，it offered high computational accuracy，with inversion precision at the level of 10–17. Applied to the computation of GRAIL lunar gravity field inversion，the proposed method，when computing matrices of truncation orders 50 and 180 respectively reduced the processing time by 94.63% and 99.51% respectively compared to CPU-based methods. Furthermore，the method successfully computed a matrix of 900th order on the High-Performance Computing Platform at Wuhan University. The method employed in this paper can effectively reduce the time needed by traditional computing models，thereby conducive to aiding in the establishment of high-order，high-precision gravity field models.
At present，the research on transverse aeolian ridges in the ''Zhurong'' landing area on Mars mainly focuses on flat areas，while ignoring the impact of complex landform types on their spatial distribution and geometric morphology of these ridges. To solve this problem，this paper used high-resolution data obtained by the Tianwen-1 orbiter to conduct a survey of transverse aeolian ridges in the Crater Ejecta，Secondary Craters，Trough，Lobate Margin，pitted Cone，Plain，and Mesa around the landing area of the "Zhurong"，analyzed the relationship between the distribution and morphology of transverse aeolian ridges and landforms，and studied the influence of two topographic factors，elevation and slope，on the distribution and morphology of transverse aeolian ridges. The results show that different landform types have a significant impact on the spatial distribution and morphological size of transverse aeolian ridges. Under the complex topography，the distribution and morphology of transverse aeolian ridges are diverse，with large sizes and no significant differences in aspect ratios; in the range of –4 300 m to –3 900 m in elevation，the number of transverse aeolian ridges is on an upward trend，and their average length and average width are strongly negatively correlated with the elevation. The study area is dominated by extremely gentle slopes and gentle slopes，and the average length and average width of transverse aeolian ridges are moderately negatively correlated with the slope. This study provides data support for the formation and development of transverse aeolian ridges，and also provides a research basis for future studies on the types of wind conditions on the Martian surface and the paleo-environment in which they began to develop.
Potentially hazardous asteroids （PHAs） pose a significant threat to Earth，with the potential to cause biological extinction and even human destruction. To cope with the impact risk of potentially hazardous asteroids （PHAs） and create a defense plan，the mineral composition of PHAs was studied using Modified Gaussian Model （MGM），and the relationship between meteorite analogues was established. The model obtained the individual absorption characteristics of minerals by deconvolution of mixture spectra. Applying MGM to six PHAs，the results show that the six PHAs are S-type，Sq-type and Q-type，respectively. The minerals are mainly composed of olivine，low-calcium pyroxene，and high-calcium pyroxene. The forsterite index （Fo#） is 0.68-0.76，and the proportion of high-calcium pyroxene is 0.17-0.38. The meteorite analogues corresponding to asteroids Itokawa，Geographios，Apophis and Apollo are LL chondrites，and the meteorite analogues of asteroids Tomaiyowit and Touratis are similar to L chondrites.
To study the origin and formation of Main Belt Comets (MBCs)，the characteristics of non-active period MBCs，as well as the relationships between MBCs and other comets and asteroids are studied. It emphasizes the need to develop an in-situ detection method capable of covering the characteristics of dust particles should be developed. In light of the upcoming Chinese Tianwen-2 mission, the authors propose an integrated composite detection method for non-contact measurement was proposed based on an analysis of the relationship between the characteristics of dust in MBCs and scientific problems，which is capable of non-contact measurement of MBCs’ ejected dust particle size, velocity，momentum，morphology，and flux without changing the original characteristics of the dust. This design has been applied to the engineering practice of the Tianwen-2 mission.
