The development history and technological evolution of aerospace reusable transportation systems were systematically analyzed. Based on application scenarios including near-Earth space, Earth-Moon（Mars）space, and deep space, the conceptual framework, technical pathways, and associated challenges of reusable transportation systems were proposed. Eight critical technologies requiring breakthroughs in various scenarios were explored, along with principles and methodologies for establishing a standardized system for reusable transportation systems.

To satisfy the requirements of highly autonomous and real-time Jupiter exploration, an autonomous orbit determination method based on active-reference measurements and stellar aberration was proposed. An onboard active optical reference source was used to establish a common alignment reference for multiple star trackers. By combining stellar aberration measurements derived from the optical axes of different star trackers with observations of Jupiter’s line-of-sight direction and apparent angular radius from a wide-field-of-view navigation sensor, autonomous spacecraft orbit determination was achieved. A stellar aberration measurement model and an active-reference geometric constraint model were formulated, and an Extended Kalman Filter-based autonomous navigation algorithm was developed. On-orbit experiments using a low-Earth-orbit satellite demonstrate a positioning accuracy better than 5 km, validating the feasibility of the proposed approach for high-precision autonomous navigation of deep-space spacecraft under long-range weak-signal conditions.

To address the significant rigid-flexible coupling effects and the difficulty of real-time planning under limited on-board computational resources during large-angle attitude maneuvers of flexible spacecraft, an active vibration suppression attitude planning method based on a dual-branch temporal neural planner was proposed. A controller-aware strategy to offline solve optimal trajectories was introduced, generating a dynamics-constrained expert dataset, based on this, a dual-branch temporal neural planner was designed, where the TCN branch extracts temporal vibration features and the Multilayer Perceptron（MLP）branch resolves instantaneous maneuver targets, jointly trained via a composite loss function. Once trained, the planner takes historical state sequences and maneuver targets as input and outputs attitude planning commands in real time. Simulation tests demonstrate that the proposed method effectively suppresses flexible vibrations, significantly shortens the settling time, and substantially reduces residual vibrations and control energy consumption.

The problem that the weak thrust of non-cooperative satellites, owing to its small magnitude and long duration, is highly susceptible to being submerged in observation noise, making detection extremely difficult, was prevalent in key stages such as precise orbit determination of low-Earth-orbit satellites and orbit control of deep-space probes, including midcourse corrections and near-Moon braking. To address this problem, a spatio-temporal graph convolutional network（ST-GCN） model based on temporal learning and spatial learning was proposed in this paper. By constructing the ST-GCN model, convolutional neural network（CNN）, graph neural network（GCN）, and feature fusion are introduced, and network parameter strategies such as adaptive learning rate scheduling and dynamic graph adjacency weights were adopted to improve detection accuracy and effectively solve the difficulty in detection caused by the extremely small magnitude of satellite micro-thrust. Experiments on three groups of low Earth orbit（LEO） satellite micro-thrust simulation datasets show that compared with current popular temporal models, the ST-GCN model proposed in this paper demonstrates the best overall performance in terms of both accuracy and efficiency. This method has the potential to be transferred to deep-space exploration scenarios and can provide a technical reference for the situational awareness of non-cooperative space targets.

Given the challenges faced by in-situ exploration missions at the lunar south pole, the complex terrain and rapidly changing illumination conditions make it difficult to ensure a safe landing, maintain a continuous lighting environment, and meet navigation and remote sensing imaging requirements. A method for spatiotemporally constrained mission design for in-situ exploration of the lunar south pole was proposed. Based on high-resolution Digital Elevation Model（DEM）and ephemeris data, terrain slope and dynamic illumination of the lunar south pole were modeled. Besides, various engineering constraints were taken into account during the pre-descent circumlunar remote sensing phase, the lunar surface landing phase and the lunar surface moving phase. Taking a potential landing area at the lunar south pole as an example, a landing site and landing time satisfying the continuous illumination constraint, a traverse path meeting the light-tracking requirement, and a remote sensing imaging window matching the landing time were obtained. The results demonstrate that the proposed method can provide implementable full-process mission planning support for in-situ exploration missions at the lunar south pole and can also serve as a reference for the mission design of China’s future lunar south pole exploration.

The Lunar Research Station is regarded as a strategic pivot for future deep space exploration. Its architectural design is constrained by multiple factors, including extreme environments, resource scarcity, and high-load scientific research tasks. To construct a scientific design guidance and evaluation system, the functional architecture of the station is delineated using the Function Analysis System Technique（FAST）, based on three core objective constraints: environment, resources, and human factors. Furthermore, the Function-Principle-Behavior-Structure（FPBS）framework is introduced to deduce the mapping mechanism from scientific residency requirements to physical entities. On this basis, a multi-dimensional objectives evaluation matrix centered on "Safety, Efficiency, and Habitability" is established, and the synergistic relationships among these targets are quantified by a coupling coordination degree model. Theoretical support is provided by this study for the scheme decision-making and performance evaluation of the Lunar Research Station.

The problem that the retarding effect of the disordered surface layer on helium-3 cross-interface migration is difficult to characterize in an open system where He-3-bearing ilmenite in lunar regolith is directly exposed to vacuum. In this paper, a nested model consisting of a crystalline ilmenite core and an amorphous TiO₂ coating was constructed, and molecular dynamics simulations were performed over 300–2300 K to examine the cross-layer migration and diffusion of helium-3. Within a fixed 1 ns observation window, the cumulative outward-migration fraction increased markedly with temperature and reached 8.92% at 2300 K; the effective diffusion coefficient of helium-3 in amorphous TiO₂ also exhibited a thermally activated increase. Because no vacuum free surface was explicitly included, the reported cumulative fraction represents atomic-scale migration across the coating rather than engineering-scale extraction efficiency. The results indicate that the dense disordered amorphous TiO₂ layer increases diffusion resistance and, together with the absence of an external escape driving force, suppresses helium-3 migration. hese findings provide a microscopic basis for the subsequent construction of multiscale release models incorporating vacuum boundaries and for the screening of heat treatment conditions.

In lunar in-situ exploration missions, the resin potting used in mechanical modules to withstand high-impact penetration environments induces nonlinear sensor responses, compromising the accuracy of acceleration signal measurements. To address this issue, this paper proposes a ‘co-planar excitation’ dynamic calibration method based on velocity parameters was proposed. The calibrated module and a standard accelerometer were symmetrically mounted on the movable platform of a shock amplifier. When the excitation pulse width exceeded 0.5 ms, both devices experienced identical acceleration and velocity, constituting co-planar excitation. Based on the principle of velocity invariance, the sensitivity of the calibrated module was determined via least squares fitting. Subsequently, a dynamic correction model was established using the Subspace Identification-State Space Method（SI -SSM）. Without relying on the mechanical parameters of the potting material, this model adaptively captures the nonlinear characteristics of the sensor response through discrete state equations, thereby correcting the acceleration output. The expanded uncertainty of the corrected measurements from the mechanical module is 4.16%, meeting the technical requirements for lunar in-situ exploration.

In this paper, the QH-E（Qinghua-E sample）lunar soil simulant was taken as the research object, and a temperature dependent cohesive tensor was introduced based on the Gudehus-Bauer hypoplastic model framework to establish a hypoplastic constitutive model coupled with temperature effects. By comparing the model results with physical experiments, the effectiveness of the model was verified, achieving a unified characterization of the strain softening and compressive hardening response of lunar soil under deep ultra-low temperature environmental conditions on the lunar surface. The deformation characteristics such as shear dilation/contraction transition and critical state approaching were effectively simulated, reflecting the significant influence of temperature on the mechanical properties of lunar soil simulant. Compared with traditional elastoplastic models, the hypoplastic model coupled with temperature effects in this paper can effectively reveal the strength and deformation characteristics of lunar soil in the lunar environment, and better reflect the inherent influence of temperature on the strength and deformation evolution mechanism of lunar soil simulant. It provides theoretical support for engineering problems such as stability analysis of lunar landers and construction of lunar base.

Aiming at the requirements for reliability and safety of the cables of asteroid probe, which will operate in orbit for 10 years and must withstand alternating extreme temperatures many times during long-term in-orbit flight, the insulation layer at the terminal of the wires inside the electrical connector shrinks after thermal cycling, exposing the wire core and creating a risk of electrical short circuit. A verification method was proposed based on the allometric growth model for the shrinkage of the insulation layer at the wire end after thermal cycling. Based on ground test data, a fitted curve of the insulation layer shrinkage along the wire axis was constructed to predict the shrinkage at the wire end after multiple extreme thermal cycles and to evaluate the effectiveness of the insulation protection at the wire terminal at both ends of the cable. The test results indicate that the proposed method can accurately predict the shrinkage of the insulation layer at wire terminals under alternating high and low temperatures, thereby confirming its effectiveness and practical feasibility in engineering applications. This verification method provides a reference for the reliability and safety design of cables under extreme temperature environments in deep space exploration.