- Current Catalog Online First Archive
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LIU Fucheng, ZHANG Jianqiao, KONG Xianglong, GAO Hao, SUN Shuokun, MA Yan, ZHANG Xiang
2025,42(6):1-17 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.001
Abstract:
The large multi-mission assemblable satellite platform is the key to meet the demands of multifunctional payloads and high-resolution remote sensing missions in the future.In this paper， the problems that need to be solved to achieve the core capabilities of such satellites，including multi-functional payload carrying，high-payload pointing accuracy，and multi-benchmark unification，are illustrated in the view of satellite design and application.Then，the current progresses and technical challenges that need to be addressed in the modular design of assemblable platforms，the design of docking mechanisms and assembly interfaces，the dynamic modeling of variable-topology assembly satellitea，high-precision stable attitude and wide-band micro-vibration control，multi-load common-benchmark precision measurement and control，and intelligent thermal control of large-scale variable-boundary platforms are deeply investigated.Finally，based on the phased research results，the future development trend of the key technologies for large-scale multi-mission modular assemblable satellite platform is prospected，with the aim of providing support for the further technique breakthroughs of China.
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YAO Xiaosong, MA Zhijie, LIU Guohua, CHENG Jiao
2025,42(6):18-25 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.002
Abstract:
The enhancement of satellite attitude maneuverability plays a crucial role in improving observation effectiveness.For large-angle rapid maneuvering missions with zero initial and final angular velocities，the strong coupling between the attitude dynamics and kinematics necessitates a two-layer control architecture comprising angular velocity trajectory planning and closed-loop tracking control.Conventional three-phase trajectory parameters(e.g.，angular acceleration and maximum angular velocity) are typically determined based on engineering experience，resulting in conservative constraints and underutilization of actuator potential.In this paper，grounded in the relationship between the flywheel and satellite attitude dynamics，the flywheel torque constraints are established，with which the conservative boundary values for trajectory parameters ensuring that all flywheel torques remain unsaturated are deduced.Furthermore，addressing the asymmetric output capacity of actuators across different Euler rotation axes(a characteristic of conservative trajectory parameters)，a differentiated trajectory parameter design method is proposed.This approach optimizes the maneuvering trajectory by maximizing the angular acceleration around each Euler axis while preventing flywheel saturation，thereby achieving the fastest dynamically feasible trapezoidal maneuver.The numerical simulations demonstrate that the proposed method significantly enhances the actuator utilization efficiency and enables rapid，stable attitude control.
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LI Ting, GAO Sheng, ZHANG Wei, ZHANG Rongpeng
2025,42(6):26-35 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.003
Abstract:
To address the limitations of traditional deep learning methods in feature extraction and fault diagnosis accuracy in complex space missions，this paper proposes a fault diagnosis method based on time-frequency representations and vision transformer (TFViT).First，the raw signals are transformed into multi-channel time-frequency representations (TFRs) to comprehensively preserve the time-frequency features of the signals.Then，the input layer and feature extraction module of the TFViT model are optimized，further improving the model’s capability to capture global dependencies within the TFRs，thereby enabling in-depth exploration of features from different time-frequency regions.With an experimental dataset constructed from a semi-physical simulation platform for spacecraft，systematic experiments are conducted to determine the optimal hyperparameter configuration of the TFViT model.The experimental results demonstrate that the TFViT model exhibits outstanding performance in fault diagnosis missions.The comparative analyses with several state-of-the-art deep learning methods fully validate the significant advantages of the proposed approach in diagnostic accuracy and robustness.
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GUO Zikang, TANG Chao, WANG Pengyu, GUO Yanning
2025,42(6):36-47 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.004
Abstract:
An optimal guidance law for the asteroid soft-landing fuel based on trajectory tracking is proposed based on the sliding mode control method.The guidance is designed and verified by numerical simulation.First，the dynamic model for a probe and the gravitational field model for an asteroid are established.Then，the optimal trajectory planning of the probe fuel is completed through the convex optimization method，and the trajectory tracking guidance law of the sliding mode control method is designed to complete the optimal fuel trajectory tracking.The zero-effort-miss/zero-effort-velocity(ZEM/ZEV) guidance law is used in the final trajectory to make the probe land as vertically as possible at the target position to ensure the safety of the soft-landing.Finally，simulation is carried out with the consideration of the uncertainty of gravity acceleration and the initial state deviation of the probe to verify the robustness of the guidance law.The results show that the guidance law has the advantages of high accuracy，fuel saving，and strong robustness.
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LI Xinglong, XU Hang, SONG Bin, CHEN Huanle, LI Genghuan
2025,42(6):48-56 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.005
Abstract:
Existing methods have problems such as high computational complexity and insufficient consideration of the correlation of orbital parameters when they are used for rapid target selection in multi-spacecraft missions in orbit.In order to solve such issues，in this paper，an intelligent selection method based on the combined orbit transfer strategy and cost space hypervolume calculation is proposed.The method combines the orbit transfer strategies of Hofmann transfer，planar change，and phasing transfer to quickly estimate the consumed speed increment cost，replacing the complex iterative calculation process of Lambert transfer.It quantitatively evaluates the fuel cost of orbital transfer processes for different target combinations.Through cost space hypervolume calculation，the method enables rapid estimation of the overall servicing cost of target clusters，and achieves efficient target selection.Simulation examples，compared with the genetic algorithm，verify that the new method not only yields better results but also significantly reduces the underlying Lambert transfer trajectory planning calculation process，cutting the computational load by an average of 91%.This provides rapid decision support for in-orbit servicing mission planning.
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LI Yuncheng, TIAN Lulu, GUO Yanning, MA Guangfu
2025,42(6):57-65 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.006
Abstract:
In this paper，an improved genetic algorithm based on mesh coordinates is proposed to address the sensor/actuator placement optimization problem for vibration control in large space truss structures.This approach effectively resolves the decoupling issue between nodal sequence and actual spatial positions through a binary mesh coordinate-based encoding scheme，while significantly enhancing the search efficiency by incorporating an elitist preservation strategy.The simulation experiments conducted on a large space truss structure demonstrate that the proposed algorithm accelerates the convergence process while improving the fitness values，exhibiting superior search efficiency and stability.The research results provide reliable technical support for vibration control in large space structures.
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ZHANG Zhiguan, ZHAO Lin, LIU Ying, WANG Yuwei, CHEN Xiao, LI Dongyu
2025,42(6):66-74 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.007
Abstract:
A mission prioritization scheme for Earth-Moon collaborative mission management is proposed to address the challenges of Earth-Moon coordination and international collaborative mission planning for the International Lunar Research Station(ILRS).Based on this scheme，a methodology is established to develop mission models and formulate mission plans according to mission levels.To meet the multi-mission and multi-facility management requirements of the complex engineering system of the ILRS，based on the classification of mission levels，different mission scenarios are analyzed，mission models are constructed，mission objectives and constraints are defined，and then mission planning solutions are achieved.Simulation verification is conducted with resource transportation missions and geological composition detection missions as case studies.The results demonstrate that this scheme effectively enables the planning and scheduling of typical ILRS missions by maximizing mission benefits.
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2025,42(6):75-89 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.008
Abstract:
A low-cost integrated navigation system for space vehicles based on cooperative objectives is designed and implemented for in-orbit satellite docking mission requirements. A loosely coupled， segmented integrated navigation approach based on the global navigation satellite system (GNSS)，inertial navigation system (INS)，laser rangefinder，and visual camera is employed，supporting full navigation from far to near.A cubature Kalman filter (CKF) algorithm is used for multisensory data fusion，and an autonomous switching algorithm of segmented integrated navigation mode is proposed，enabling autonomous smooth switching of different navigation modes.The system has the characteristics of low cost，high accuracy，and high availability.The semi-physical simulation results show that the system meets the requirements of in-orbit satellite autonomous rendezvous and docking or in-orbit services.
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HOU Lixian, MAO Chengli, LIU Chang, LIU Xiaomeng
2025,42(6):90-98 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.009
Abstract:
A planning strategy for multi-spacecraft close-range observation missions is proposed.The time constraint is considered，and the energy consumption is optimized.Based on the two-pulse multi-loop Lambert rendezvous principle，the inner is optimized with the particle swarm optimization (PSO) algorithm to design the time allocation for single spacecraft close-range observation missions，while the outer is optimized with the genetic algorithm (GA) to optimize the sequence for multi-spacecraft missions.The nested dual-layer optimization design is investigated.The simulation verification results show that the energy consumption for executing close-range observation missions can be effectively reduced by means of optimizing the pulse maneuver time of the single spacecraft and the mission sequence of the multi-spacecraft.
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XU Weihan, QIAN Yiwei, WANG Zhiyi
2025,42(6):99-105 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.010
Abstract:
Origami refers to the process of shaping various spatial forms using complete sheets of paper without any cutting. It has the advantages such as easy manufacturing， easy assembly， large folding ratio， and diverse configuration， has a wide application prospect in the field of space folding mechanisms， providing the possibility for spacecraft to carry more payloads， and meet the needs of more complex tasks. This paper focuses on the geometric features and realization methods of the main folding configurations， and reviews the research status of space folding mechanisms based on origami and their applications in the field of aerospace. In line with the future development trend of space folding mechanisms， this paper describes the characteristics， progress， application status， and development direction of thick plate origami， and then looks forward to the application of shape memory polymer in space folding mechanisms based on origami， aiming to provide reference for the research and application of large-scale space folding mechanisms in the future.
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XIONG Liqiang, HU Dike, WANG Wenzhe, TANG Guoan
2025,42(6):106-113 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.011
Abstract:
To mitigate torque loads on rotating components of a spacecraft’s flexible appendages(such as solar arrays) during start-stop processes，an optimized actuation timing scheme is developed for the actuator system.Through analytical methods，the optimal angular velocity profile for start-stop operations is derived under the first-order torsional vibration mode dominance.The results reveal that the optimal angular velocity profile is not a smooth continuous function under equivalent start-stop durations，but rather comprises step changes combined with uniform acceleration phases.Experimental validation using geometrically similar solar array models with natural frequencies comparable to actual spacecraft appendages demonstrates that implementing the optimized profile significantly reduces the maximum root torque by 50% compared with conventional uniform acceleration processes.
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WANG Tianyi, YANG Shengxi, JIANG Linghai, ZHANG Yang, YUAN Huiling, WEI Zhi, LIU Qingkang, HUANG Qitao
2025,42(6):114-120 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.012
Abstract:
The space docking mechanism is used for in-orbit docking of spacecraft，and serves as a crucial component in the construction of a space station.After docking，the docking mechanism forms an integrated assembly.During operations such as docking and separation，the docking assembly endures constant or alternating loads as well as environmental temperature variations.The docking lock is a key component that ensures the connection strength and sealing performance of the space station assembly.To ensure the safe operation of a space station within its design life，it is essential to conduct accurate and reliable evaluations of the docking lock’s lifespan.In this paper，based on the assumption of an unchanged failure mechanism，accelerated degradation tests(ADTs) are carried out.The temperature stress is used as the load，while the tension degradation of the docking lock is taken as the degradation quantity.Step-stress loading is applied，and the test data are used to calculate the pseudo-lifetime under different temperature stresses.The relationship between the median pseudo-lifetime and temperature is fitted using a lognormal distribution.The Kolmogorov-Smirnov(K-S) test verifies that the pseudo-lifetime follows the lognormal distribution.Finally，the median pseudo-lifetime of the docking lock under a failure threshold of 14 kN is estimated.
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ZHANG Ruixiong, CHEN Fan, YANG Shengxi, WANG Zhiyi, QUAN Lingxiao
2025,42(6):121-126 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.013
Abstract:
In view of the requirement of rendezvous and docking mechanisms for 15 years in-orbit operation lifetime，a temperature-based accelerated lifetime decay model is proposed，and a specific accelerated lifetime test scheme is designed for lifetime assessment.With the measured data for the locking force attenuation of three locking mechanisms at five different temperatures，the accelerated lifetime degradation equation is solved，and then the locking force attenuation of the locking mechanism during in-orbit operation is predicted.The results indicate that thermal tests can effectively accelerate the deterioration process of the locking mechanism’s lifetime.At a temperature of 25 ℃ on the thermal control coating，the initial locking force is 37.000 kN，and after 15 years of operation，it decays by 2.923 kN.The value obtained by the mathematical model calculation based on the component materials is 2.831 kN.Both the two lifetime analysis methods indicate that the locking force of the locking mechanism can meet the lifetime requirement in in-orbit environment.This study can provide a reference for the long-term reliable in-orbit operation of China’s space station and the assessment of the service life of institutional products.
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YANG Bo, YU Yunfeng, WANG Haozhe, HUANG Han, CHEN Jinbao, XU Shucai
2025,42(6):127-136 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.014
Abstract:
Penetrator penetration detection is one of the important methods for deep space exploration，which can be used to analyze the composition and geological characteristics of celestial bodies.In order to study the influence of the sharp-arched radius ratio and initial velocity of the penetrator warhead on the penetration characteristics under low-speed conditions，a finite element analysis(FEA) model of penetrator penetration into satellite soil is established.The accuracy of the model is verified through ground tests.The penetration processes under different penetrator working conditions are simulated and analyzed in three different densities of simulated satellite soil，and the variation laws of the penetration depth and peak acceleration are discussed.The multi-objective particle swarm optimization method is used to obtain the optimal parameters and penetration velocity of the penetrator structure.The results show that sharp-arched radius ratio of the penetrator under compactness conditions of planetary soil simulant is 1.5，and the optimal initial velocity ranges from 15.2 m/s to 16.8 m/s.This study can provide a reference for the structural design of penetrators and the setting of initial penetration conditions in low-speed penetration tasks of celestial bodies.
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LIU Xiangyang, LIU Yuanchun, DUAN Yi, TIAN Chuan
2025,42(6):137-145 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.015
Abstract:
In this paper，the re-entry process of the FIRE-II capsule is calculated based on the finite volume method.The Park two-temperature thermochemical non-equilibrium reaction model is used to analyze the influence of chemical reaction models with different species (7 species and 11 species) on the calculation results of flow field and radiation intensity on the lee side of the capsule.The results show that there is a significant thermochemical non-equilibrium effect in the wake flow field at the altitude of 67 km and flight Ma of 37.2，and there are a large number of N+ and O+ ions in the wake flow field by adopting the reaction model with 11 species.The ionization degree of the flow field is greatly underestimated by the reaction model with 7 species due to ignoring N+，O+，N2+，and O2+ ions，so that the number of electrons obtained by the reaction model with 7 species is much lower than that with 11 species.The reaction model with 7 species also underestimates the translational temperature of the wake flow field，so that the radiation intensity calculated by the reaction model with 7 species is lower than that with 11 species.
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WAN Feng, QIN Lei, MA Hailong, CHEN Ruiqi, CHEN Xiaodi
2025,42(6):146-155 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.016
Abstract:
Currently，the construction of large-scale satellite constellations has become an important development direction in the satellite field，and the satellite production mode is shifting towards multi-variety，variable batch，high efficiency，and low cost.In response to the needs of cross enterprise collaboration，rapid process design，efficient assembly，and real-time production process control in satellite batch production，based on the analysis of the workflow of satellite flexible assembly line，an overall architecture of cloud-network-edge-end collaborative production line is proposed.The key technologies，e.g.，knowledge-driven rapid design of assembly process，model-driven human-machine collaborative assembly and detection，real-time state perception based on the Internet of things，and assembly line monitoring and prediction based on digital twins，are studied，and the construction and application of the production line are introduced with examples.Through the application of this production line，the efficiency of satellite batch production has been effectively improved，and the assembly and testing time for typical satellites has been shortened by about 70%.
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YANG Boxian, HU Hualong, JIANG Shichen
2025,42(6):156-162 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.017
Abstract:
The world’s first geostationary orbit microwave meteorological satellite boasts an impressive 5-m diameter reflector antenna，which is capable of conducting high-frequency three-dimensional monitoring of crucial meteorological elements.However，under on-orbit conditions，the antenna’s components experience random perturbations across their six degrees of freedom(6-DOF).These perturbations can lead to alterations in the antenna’s maximum gain direction，thereby impacting the achievement of high-precision navigation alignment.Traditional simulation methods fall short in efficiently predicting these changes.To tackle this challenge，in this paper，an innovative deep learning-based approach is proposed to predict the maximum gain direction of multi-reflector antennas.A sophisticated deep learning model is built，and the 6-DOF perturbations for each reflector are used as inputs，while the maximum gain direction serves as the output.Additionally，to enhance the model’s efficiency，a weight-based pruning strategy and quantization techniques are employed.The results demonstrate that the carefully designed deep learning model not only effectively predicts the maximum gain direction of the spaceborne antenna with a determination coefficient of 0.94，but also increases the prediction speed to 3.5×10⁵ times that of traditional simulation methods while maintaining a prediction error of less than 1.5×10-3.
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LI Jiyu, HAO Yunbo, LU Qiuyang, TIAN Haodong, CHENG Lingyu, ZHAO Kai
2025,42(6):163-169 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.018
Abstract:
The Ti-6.5Al-3.5Mo-1.5Zr-0.3Si(TC11) titanium alloy is prepared by the laser melting deposition (LMD) technology.The effects of overlapping on the microstructures and properties of the LMD-TC11 titanium alloy are studied through microstructure characterization and mechanical property tests.The results indicate that the microstructures at the overlapping interface of LMD-TC11 titanium alloy primarily consist of Widmannstätten structures and basket-weave structures，similar to the base material.However，there are epitaxial grown grains in the base material near the interface.Comparison with the mechanical properties of the base sample shows that the overlapping process does not reduce the mechanical properties of the LMD-TC11 titanium alloy.Notably，the mechanical properties of the -45° overlapping sample are significantly higher than those of the -90° base sample.The tensile fracture analysis reveals that the fracture mode of the LMD-TC11 titanium alloy is primarily intergranular，which is mainly attributed to the continuous distribution of the α phase along the grain boundaries.
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MA Chi, HUANG Wang, MEI Yueni, WANG Ke, MA Yulin, FU Chuankai
2025,42(6):170-178 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.019
Abstract:
With the expansion of application scenarios，there is a greater need than ever to develop high-performance lithium-ion batteries (LIBs)，particularly those with the ability to operate steadily under extremely temperature conditions.Unfortunately，the electrochemical performance and cycling stability of current LIBs remain inadequate under extreme temperature conditions，particularly under extremely high-temperature (no less than 45 ℃) conditions，which greatly limits their applications in critical fields including aerospace and special equipment.The primary issues that LIBs encounter when operating in high-temperatures are covered in the first section of this article.Then，the selection of lithium salts，the design of solvation structures，and the use of additions are summarized in detail.Lastly，the research and development directions of electrolytes for high-temperature LIBs are prospected.In general，this paper can serve as a guide for the design and development of electrolytes for high-temperature LIBs and positively impact the advancement of product development and technology related to high-temperature LIBs.
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LIU Yunzhao, BAI Yunfei, SHEN Sile, ZHUO Qiming, YANG Zhuang, LI Wei
2025,42(6):179-183 ,DOI: 10.19328/j.cnki.2096-8655.2025.06.020
Abstract:
A novel MnO2/carbon skeleton composites cathode is successfully synthesized by a facile liquid-phase reaction process.Then，it is assembled into single-cellthermal battery with LiSi anode and LiNO3-KNO3electrolyte system.The thermal stability，crystal structure，and surface morphology of the active material areanalyzed by thermogravimetric (TG) analysis，X-ray powder diffraction (XRD)，and scanning electron microscope (SEM).The test results show that MnO2/carbon skeleton composites have nano-clustered morphology with good dispersivity and crystallinity.Meanwhile，the carbon skeleton substrate can effectively enhance the conductivity of MnO2.When the thermal battery is tested at the temperature of 300 ℃ and the current density of 30 mA/cm2，the initial discharge plateau reachesup to 3.34 V.The thermal battery showsa stable discharge platform and excellent electrochemical performance.The specific discharge capacity is as high as 903 mAh/g with a cut-off voltage of 1.8 V.
