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Deep-Space Exploration
Overview of Sun-Earth L1 Point Near-Earth Asteroid Monitoring Microsatellite Missions
Mier TAI, Baorui LUO, Shiyu AN, Yue ZHU, Jiyao ZHANG, Lei ZHANG, Jiahe HUANG, Mingchuan WEI, and Zhuoxi HUO
The field of view for near Earth asteroids observed by ground-based astronomical telescopes is limited due to backlighting,while observing form a Venus-like orbit or at the Sun-Earth L1 point can provide better visible ranges.In this paper,a proposal is made to use microsatellites positioned at the Sun-Earth L1 point fThe field of view for near Earth asteroids observed by ground-based astronomical telescopes is limited due to backlighting,while observing form a Venus-like orbit or at the Sun-Earth L1 point can provide better visible ranges.In this paper,a proposal is made to use microsatellites positioned at the Sun-Earth L1 point for monitoring near-Earth asteroids.The overall design of the mission microsatellites is described,the transfer orbit design is analyzed in detail,and a payload design scheme is provided.Through missions,several key technologies for deep space microsatellites are verified,including the overall design with large velocity increments using electric propulsion,the low-energy transfer orbit design for deep space,and the high-performance on-orbit processing of astronomical data,thereby exploring a cost-effective approach to deep space exploration..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 35 (2024)
Research on Optimal Selection of Optical Information Under the Fusion Positioning of Angle Measurement and Navigation Satellite Ranging for Deep Space Probe
Jing LIU, Shengying ZHU, Pingyuan CUI, and Yanjie LIU
To address the problem of autonomous positioning for deep space probe,an optimal selection method of optical information under the fusion positioning of angle measurement and navigation satellite ranging is proposed.The characteristics of optical angle measurement and navigation satellite ranging are analyzed,and a fusTo address the problem of autonomous positioning for deep space probe,an optimal selection method of optical information under the fusion positioning of angle measurement and navigation satellite ranging is proposed.The characteristics of optical angle measurement and navigation satellite ranging are analyzed,and a fusion positioning scheme of angle measurement and navigation satellite ranging is designed to realize the high-precision absolute positioning.On this basis,in view of the measurement accuracy of the sensor and the measurement geometry,the overall observability and relative observability of the angle measurement information are designed,the evaluation function of the angle measurement information is constructed,and the heuristic algorithm is used to optimize the selection of the angle measurement combination.Finally,numerical simulation is carried out,and the obtained results show that the designed optical selection method of optical information can effectively improve the navigation performance..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 44 (2024)
Progress and Prospects of Deep Space Exploration Missions
Zhong ZHANG, Di WU, and Hexi BAOYIN
A comprehensive overview for the latest progress of international deep space exploration mission design is presented,covering the fields of lunar exploration,major planetary exploration,and small celestial body exploration.In terms of lunar exploration,the strategic layouts of the Earth-Moon space,e.g.,the Artemis progA comprehensive overview for the latest progress of international deep space exploration mission design is presented,covering the fields of lunar exploration,major planetary exploration,and small celestial body exploration.In terms of lunar exploration,the strategic layouts of the Earth-Moon space,e.g.,the Artemis program in the United States and China's lunar exploration program,are demonstrated.In terms of major planetary exploration,the history and current status of the exploration missions for the Mercury,the Venus,the Mars,the Jupiter,the Saturn,and other outer planets,are reviewed.In terms of small celestial body exploration,the technical challenges and scientific significance are discussed,and the missions,such as flybys,orbits,sampling,and impacts,are expatiated.Based on these discussions,the enlightenment and development trends of deep space exploration missions are summarized,and relevant mission suggestions and concepts are put forward in combination with China's deep space exploration capability and the development of international planetary science,which could offer references for the design of future deep space exploration missions in China..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 52 (2024)
Advances and Prospect of Saturnian System Exploration Missions
Yang DU, Yi ZHANG, Xiaowen DUAN, Miao YU, Zhiqing GENG, Tongjie LIU, and Junpo NIU
According to the white paper “China's Aerospace 2021”,China's planetary exploration project will carry out asteroid exploration,Mars sampling return,and Jovian system exploration,but there is no clear plan for more long-term planetary exploration missions.The Saturn is the second largest planet in the solar sysAccording to the white paper “China's Aerospace 2021”,China's planetary exploration project will carry out asteroid exploration,Mars sampling return,and Jovian system exploration,but there is no clear plan for more long-term planetary exploration missions.The Saturn is the second largest planet in the solar system,with beautiful rings and many natural satellites,among which the Enceladus may have a subglacial ocean,and the Titan is the second largest natural satellite in the solar system and the only satellite with a dense atmosphere,all of which are of great scientific research value.In this paper,foreign Saturn exploration missions are investigated and analyzed,including Pioneer 11,Voyager 1,Voyager 2,and Cassini-Huygens,as well as the future missions,including Enceladus Orbilander and Enceladus Multiple Flybys.The characteristics of these missions and the key difficulties in the implementation of Saturnian system exploration are summarized.Finally,an overall mission assumption of Saturn system exploration is proposed,and the mission analysis and preliminary design are carried out,which can be used as a reference for China's follow-up planetary exploration mission planning..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 69 (2024)
Review of Planetary Ultraviolet Spectral Detection Payload Technology Development
Jun YU, Yang DU, Wei ZHANG, Yue YU, Runze QI, Wei WANG, and Zhanshan WANG
The atmosphere of planets is a crucial research orientation in fields such as deep space exploration and space astronomy,among which the ultraviolet (UV) spectral range is a significant aspect of planetary atmospheric activity research.To obtain UV spectrum information from various extraterrestrial planets,internationaThe atmosphere of planets is a crucial research orientation in fields such as deep space exploration and space astronomy,among which the ultraviolet (UV) spectral range is a significant aspect of planetary atmospheric activity research.To obtain UV spectrum information from various extraterrestrial planets,international research teams have conducted relevant technological studies over the past few decades,and have developed numerous scientific observation payloads.In this paper,the development of planetary UV spectrum detection payloads are reviewed,and the advancement and iteration of the spectrometer technology driven by the progress in the core UV component technologies are analyzed.Finally,possible future directions and key research areas in the field of planetary UV spectrum detection are presented..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 79 (2024)
Research and Analysis of Thermal Control Technology for Mars Surface Takeoff and Ascent
Jin YANG, Tongjie LIU, Liang XU, Song SHENG, Haowei NI, Ai DU, Hongkang MIAO, Tao XU, Wei WANG, Zhiliang WU, and Hong ZHU
The thermal control technology for Mars surface takeoff and ascent is a key technology for Mars sample-return exploration,involving the temperature control for storage,the temperature control for Mars surface takeoff and ascent,andthe temperature control for Mars in-orbit flight.It has the characteristics of high tempeThe thermal control technology for Mars surface takeoff and ascent is a key technology for Mars sample-return exploration,involving the temperature control for storage,the temperature control for Mars surface takeoff and ascent,andthe temperature control for Mars in-orbit flight.It has the characteristics of high temperature index requirements,large temperature control dimensions,and scarce resources.In this paper,the thermal control schemes of major Mars roversat home and abroad and the Mars ascenders ofthe National Aeronautics and Space Administration (NASA)are investigated and summarized.The results show that,according to the resource allocation,the thermal control technology of Mars surface probes mainly adopts two strategies.When the thermal control weight is not significantly limited,aiming at the reuse of waste heat,the mechanical pump driven fluid circuit technology is adopted to collect and transfer the heat of high heat consumption devices,in conjunction with conventional thermal control measures.When the thermal controlweight is severely limited,lightweight and low-power thermal control measures should be adopted.At this time,aiming at the lowest power consumption,the composite nano-aerogel thermal insulation technology is usually adopted to efficiently isolate the low-temperature convective environment on the surface of Mars,in combination with conventional thermal control measures.Subsequently,the key thermal control technologies for Mars surface takeoff and ascent are proposed,mainly includingthe nano-aerogel thermal insulation technology,the thermal insulation technology for in-situ resources on Mars,the mechanically pumped two-phase loop (MPTL) technology,the atmospheric dynamic thermal protection technology,and the thermal test simulation technology,which can provide some reference for subsequent Mars exploration..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 90 (2024)
Innovation and Exploration
Current Situation and Future Development of Sea-launch Launch Test Processes for Launch Vehicles
Liqun LI, Xiuli HAN, Cheng LI, Wei FENG, and Yongqing QI
Sea-launch has shown a trend of multi-model,high density,and normalization,and the simplification and efficiency of launch test processes directly affect the frequency and efficiency of sea-launch.In this paper,the current situation and future development of the launch test processes of sea-launch are investigated.FirsSea-launch has shown a trend of multi-model,high density,and normalization,and the simplification and efficiency of launch test processes directly affect the frequency and efficiency of sea-launch.In this paper,the current situation and future development of the launch test processes of sea-launch are investigated.First,the current situation of sea-launch launch test processes is analyzed.Then,the differences between the current typical sea-launch launch test processes in China and the launch test processes with different launch patterns are described.Finally,some suggestions for the future development of sea-launch launch test processes are put forward,e.g.,establishing industrial standards,exploring new patterns of multiple launches from one ship,and “space-based test launch”..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 99 (2024)
Collision Dynamics Analysis and Optimization of Space Tether-net Capture
Miao DONG, Chen WANG, Jinyao ZHU, Jinbao CHEN, and Chaoyu LU
The increasing amount of space debris and defunct satellites poses a significant threat to the usability and sustainability of orbital resources in space.Space tether-net capture is a novel and effective removal method,and the design and optimization of its core component,i.e.,the space tether-net system,is an importanThe increasing amount of space debris and defunct satellites poses a significant threat to the usability and sustainability of orbital resources in space.Space tether-net capture is a novel and effective removal method,and the design and optimization of its core component,i.e.,the space tether-net system,is an important prerequisite for the successful completion of on-orbit capture missions.Focusing on the collision process between the space tether-net system and the target,the dynamics of the space tether-net system and the dynamic model for tether-net-to-target collision are established based on the finite element method and Hertz theory.The captured collision process for different configurations and parameters of the space tether-net is simulated and analyzed by Abaqus.Meanwhile,with the help of Design-Expert,a three-factor response surface experiment is designed on the basis of mesh shape determination.After the interactive response analysis and optimization of several sets of experimental data,the optimal mesh configuration and parameters are obtained.The simulation verifies that the maximum contact normal force is 83.9 N,the maximum slip is 14.379 mm,and the maximum elastic strain energy is 836.4 J,which are all within 7% of the optimal target values.The optimization strategy reduces the contact normal force and slip displacement during the collision process of tether-net capture,decreases the probability of accidental entanglement or tearing of the tether-net during the capture process,and ensures sufficient elastic strain energy to meet the requirements for energy buffering.This approach provides valuable insights for the design of space tether-net configurations and parameters,offering a safe and reliable guarantee for space on-orbit capture missions..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 104 (2024)
Indirect Method of Energy-optimized Plane Trajectory Optimization for Electric Propulsion of Mars Orbit Insertion
Haiyang LI, Xiaowen DUAN, Yingjie ZHAO, Tongjie LIU, and Xi LU
Because of the low thrust,the time of planetary orbit insertion by electric propulsion has significantly increased.Electric propulsion has completely different characteristics from chemical propulsion,and greatly increases the difficulty in trajectory optimization.This paper focuses on the control problem of the low thBecause of the low thrust,the time of planetary orbit insertion by electric propulsion has significantly increased.Electric propulsion has completely different characteristics from chemical propulsion,and greatly increases the difficulty in trajectory optimization.This paper focuses on the control problem of the low thrust trajectory of planetary orbit insertion phase,and takes the trajectory optimization problem of Mars orbit insertion as an example.Based on the hyperbolic orbit parameters,research is conducted on the switch and control strategies of planetary orbit insertion under different performance indicators.An indirect method is used to solve the energy-optimized plane trajectory optimization problem and obtain the optimal control strategy.The optimal control strategy is compared with the control strategy in the opposite direction along the velocity direction.The results indicate that the proposed method has achieved optimized design for low thrust Mars orbit insertion.The error in the captured orbit is smaller than that of the target orbit,and the orbital safety can be guaranteed..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 113 (2024)
An Optimal Control Strategy for Cluster Spacecraft Cooperative Trapping of Non-cooperative Targets Based on State-dependent Riccati Equation
Yi CHENG, Kun ZHAO, Mingshuai WU, Zhuo YIN, and Yuan LIU
With the vigorous development of space technology,space security has increasingly become a focal point in the field of spaceflight.The pursuit of on-orbit targets in space will also develop from the pursuit of single spacecraft to the trend of cooperative fencing by cluster spacecraft.This paper presents a strategy andWith the vigorous development of space technology,space security has increasingly become a focal point in the field of spaceflight.The pursuit of on-orbit targets in space will also develop from the pursuit of single spacecraft to the trend of cooperative fencing by cluster spacecraft.This paper presents a strategy and method based on the state-dependent Riccati equation for the typical scenario of cluster spacecraft cooperative trapping of non-cooperative targets in space.First,based on the nonlinear relative motion model of spacecraft,a kinematic model of space cluster spacecraft cooperative trapping of noncooperative targets is established,and the quadratic objective functions (relative distance and fuel consumption) of both parties are designed accordingly,so that the trapping problem is transformed into a Nash equilibrium problem with differential countermeasures.Second,the state Riccati equation is solved,and thus the optimal strategy of cluster spacecraft against single non-cooperative target spacecraft is obtained.Third,with the null-space projection method,a distance-dependent priority-based mission planning scheme is designed to obtain the escape strategy of non-cooperative target spacecraft facing cluster spacecraft and to avoid the escape strategy conflict for the cluster spacecraft.Finally,numerical simulations are carried out,and the obtained results verify the effectiveness of the proposed cooperative fencing strategy and method..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 121 (2024)
Evaluation Method of Space Environment Based on Inactive Satellite Orbital Data
Juan YANG, Kai CUI, Zhaohui LIU, Wenji SHE, Yongqing YANG, and Feng WANG
When a satellite suffered an attitude and orbital control system failure,it would float freely in space,and then the long-term impacts and changes of the space environment will be directly reflected in the weak changes of its orbital parameters.In this paper,the feasibility and method for the in-situ traceability of loWhen a satellite suffered an attitude and orbital control system failure,it would float freely in space,and then the long-term impacts and changes of the space environment will be directly reflected in the weak changes of its orbital parameters.In this paper,the feasibility and method for the in-situ traceability of long-time space environment impacts based on the orbital parameter data of inactive satellites are studied.Based on the non-uniform Fourier transform (NUFT) method,the long-term frequency characteristics of open satellite orbital data are extracted.The results show obvious periodic disturbance related to the solar activity.From the analysis on the open orbital inclination data of several inactive satellites,it is identified that the periods of solar activity related space environment on the orbital perturbations of low-orbit satellites are 400 d,89 d,and 13.5 d.This method puts forward a new idea for the utilization of inactive satellite orbital data..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 130 (2024)
Adhesion and Locomotion Control of a Hexapod Rover in Low Gravity Environment
Shilin ZHANG, and Binbin ZAHNG
In order to address the detachment problem caused by low gravity on small celestial bodies,a locomotion and adhesion control scheme for a hexapod rover in low gravitational environment is studied.First,a foot-ground contact dynamics model is established,and the mechanical constraints of the hexapod rover to achieve adhIn order to address the detachment problem caused by low gravity on small celestial bodies,a locomotion and adhesion control scheme for a hexapod rover in low gravitational environment is studied.First,a foot-ground contact dynamics model is established,and the mechanical constraints of the hexapod rover to achieve adhesion without detachment and locomotion without slipping under low gravitational conditions are analyzed.Second,according to the mechanism characteristics and movement form of the hexapod rover,a smooth gait planning method based on a triangular curve is designed to suppress the impacts of the rover’s feet during locomotion.Third,a multi-legged cooperative adhesion method based on the terminal gait offset is established to ensure the stable adhesion of the rover to a small celestial body.Finally,through a simulation case,the effectiveness of the control scheme is verified,providing a new idea for the mobile detection task of a hexapod robot under low gravitational conditions..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 136 (2024)
Missile-target Dynamic Allocation Method Based on Neural Network Residual Time Estimation
Shi SU, Ying NAN, and Mingyong HE
A neural network-based residual flight time prediction method is designed for the dynamic target allocation of anti-aircraft missiles.This method not only takes into account the relative missile-to-target distance and the missile motion state,but also considers the influence of the motion state of the enemy target on tA neural network-based residual flight time prediction method is designed for the dynamic target allocation of anti-aircraft missiles.This method not only takes into account the relative missile-to-target distance and the missile motion state,but also considers the influence of the motion state of the enemy target on the prediction results,thereby improving the prediction accuracy.A target allocation model,which comprehensively considers the distance advantage,angle advantage,and residual flight time,is established in combination with the designed method.An auction algorithm is adopted to solve this model,by which an overall optimal target allocation scheme is achieved.The simulation results show that the prediction error of the neural network model is within 0.4 s,which is lower than that of the classical method.The computation time for reallocation with the auction algorithm can meet the real-time requirements of the system..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 145 (2024)
Special Paper of Expert
Jun LIN, Xi LU, Yuhao CHEN, Fan HUANG, Shenyi ZHANG, Yiteng ZHANG, Bin ZHOU, Zhenhua GE, Liu LIU, Hui TIAN, Jiansen HE, Xin CHENG, Pengfei CHEN, Xianyong BAI, Haisheng JI, Jiajia LIU, and Xiaoshi ZHANG
The Solar Close Observations and Proximity Experiments (SCOPE) is a space mission for solar observations.It aims to send a spacecraft into the solar atmosphere deeply,approaching to the Sun at a location around 5 solar radii from the center of the Sun,so as to explore the super-bright and super-hot “uninhibited zones” The Solar Close Observations and Proximity Experiments (SCOPE) is a space mission for solar observations.It aims to send a spacecraft into the solar atmosphere deeply,approaching to the Sun at a location around 5 solar radii from the center of the Sun,so as to explore the super-bright and super-hot “uninhibited zones” of the deep space near the Sun.A set of breakthroughs are expected to make by the mission in the limits to techniques such as high temperature and strong radiation protection,super-long distance delivery,orbit control at large distance,and advanced payloads.The observations and in-situ measurements of the Sun will be performed at a brand new position on the magnetic field and plasma structures with the special resolution better than 0.1".The spacecraft will traverse the magnetic reconnection current sheets,coronal mass ejections,associated fast mode shocks,and various charged particles occurring in the solar eruption for revealing the theoretical mechanisms of the solar eruption.The instruments will microscopically observe and in-situ measure the nano-flares smaller than 0.1" in the corona and the magnetic field and plasma structures smaller than 0.06" in the photosphere at an unprecedentedly close distance,identifying the features and associated mechanisms for corona heating.The detection of the charge states of heavy ions in the solar wind will help identify the origin and acceleration mechanisms of the solar wind.The coronal magnetic field and plasma,including those in the polar region,will be directly detected at the closest distance to the Sun,and the associated structures will be microscopically observed.The dust distribution of the dust around the Sun will be revealed,and the inner edge of the dust disk in the solar system will be explored.Two fundamental puzzles,i.e.,solar eruption and corona heating,which have challenged the solar physics community for about a century,will be solved with the success of the mission;and a breakthrough will also be realized in detecting the coronal magnetic field,including that in the polar region.In this paper,the background,science,expected scientific achievements,payloads,and key satellite platform techniques of the SCOPE are introduced..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 1 (2024)
China Response to Risk of NEA and Kinetic Energy Impact Deflection Researches:Retrospect and Prospect
Zizheng GONG, Guangming SONG, Chuan CHEN, Pinliang ZHANG, Wenjin LIU, Qingming ZHANG, and Renrong LONG
Near-Earth Asteroid (NEA) impact on the Earth is a major potential catastrophic threat to humanity for a long time.Based on monitoring,early warning and risk assessment,in-orbit disposal (active defense)is the best way to prevent and resolve the NEA impact risk.This paper provides an overview of the current situation aNear-Earth Asteroid (NEA) impact on the Earth is a major potential catastrophic threat to humanity for a long time.Based on monitoring,early warning and risk assessment,in-orbit disposal (active defense)is the best way to prevent and resolve the NEA impact risk.This paper provides an overview of the current situation and development trends of international response to risk of NEA,and introduces the main work progress since China launched the NEA impact risk response project since 2020.The research progresses on kinetic energy impact deflection technology in China from the aspects of experiment,numerical simulation and theoretical modeling were highlighted.The first demonstration and verification mission of NEA kinetic impact defense in China is prospected,and suggestions for the further development of the capability and technologies for NEA defense on-orbit disposal was put forward..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 11 (2024)
Characteristics and Technical Innovations of LM-6C Launch Vehicle
Xiufeng DING, Yansheng YU, Zhongqiang CHEN, Wenbin WANG, and Cunming HU
The Long March 6C (LM-6C) launch vehicle is a single-core,two-stage liquid oxygen/kerosene launch vehicle within the modified Long March 6 (LM-6)launch vehicle series,and is engineered to achieve a 2-ton payload capacity in the Sun-synchronous orbit (SSO).As a cornerstone of the new generation of Long March launch vehiThe Long March 6C (LM-6C) launch vehicle is a single-core,two-stage liquid oxygen/kerosene launch vehicle within the modified Long March 6 (LM-6)launch vehicle series,and is engineered to achieve a 2-ton payload capacity in the Sun-synchronous orbit (SSO).As a cornerstone of the new generation of Long March launch vehicles,the LM-6C launch vehicle has been refined with technological and developmental process innovations to shorten the development cycle,enhance the flight reliability and mission adaptability,simply the launch site operations,and heighten the cost-effectiveness and performance capability.It has broken through many key technologies such as the overall configuration optimization of two-stage tailless rocket,the 2.9 diameter foam sandwich common bottom,the highly reliable pressurization technology with strong mission adaptability,and the adaptive augmentation control.In this paper,an overview of the development background and history,characteristics,and technical innovations of the LM-6C launch vehicle is carried out,and the course for its future development pathways is charted..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 24 (2024)
Speciality Discussion
Design and Mechanical Analysis on the Lattice Structure for the Primary Load-Bearing Panel of a Satellite
Enxiang ZHANG, Yibei ZHANG, Xin XU, Qi ZHANG, Zhiming XU, Weiming YANG, and Baihong CHI
In order to meet the design requirements of the primary load-bearing panel of a satellite in terms of lightweight and stiffness performance and effectively reduce the dynamic responses of the panel,a lattice structure is incorporated into the design of the primary panel.First,the cell composition of the lattice structuIn order to meet the design requirements of the primary load-bearing panel of a satellite in terms of lightweight and stiffness performance and effectively reduce the dynamic responses of the panel,a lattice structure is incorporated into the design of the primary panel.First,the cell composition of the lattice structure is introduced.It is demonstrated that the satellite primary load-bearing panel filled with the lattice structure can reduce the weight of approximately 35% compared with the traditional honeycomb core panel,while maintaining the same external dimensions,thereby satisfying the lightweight design requirements for satellites.Second,theoretical mathematical models for the relative density,in-plane stiffness,in-plane strength,and shear stiffness of a single cell unit are established,and the accuracy of the models are validated through simulation analyses.The fundamental principles of dynamic analyses and the optimization methods are illustrated.Finally,based on the modal analysis results,harmonic and random vibration response analyses are conducted on the designed primary load-bearing structure.The results show that the structural stiffness distribution of the primary load-bearing panel is uniform and exhibits favorable responses to excitations,and all dynamic performance indicators meet the specified requirements..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 153 (2024)
Review on Solar Sail and Its Attitude Control Methods
Feng ZHANG, and Erliang WANG
As a new type of propellant-free spacecraft,solar sail has broad application prospects in deep space exploration.In addition,thanks to the action of constant solar radiation pressure,solar sail can operate in orbits that are difficult to achieve with traditional spacecraft,thereby realizing some unique uses.In this papAs a new type of propellant-free spacecraft,solar sail has broad application prospects in deep space exploration.In addition,thanks to the action of constant solar radiation pressure,solar sail can operate in orbits that are difficult to achieve with traditional spacecraft,thereby realizing some unique uses.In this paper,based on the brief introduction of the working principles and application prospects for solar sail,the essential characteristics,advantages,and disadvantages of the classical attitude control methods for solar sail are analyzed in detail.The research status of solar sail attitude control methods at home and abroad is investigated,the limitations of the classical attitude control methods on the attitude control of large scale solar sail are analyzed,and the feasibility and advantages of utilizing solar sail deformation to achieve attitude control torque is studied.Finally,some suggestions for the research and development of solar sail attitude control are put forward..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 162 (2024)
Microstructures and Bending Properties of Cf /Mg Composites
Xuejian LI, Haitao ZHOU, Zhenming SUN, Bo JIANG, Hailong SHI, Xiaoshi HU, and Xiaojun WANG
In order to meet the requirements of lightweight structural materials in extreme space environment,the T300,T700,and M40 carbon fiber-reinforced magnesium matrix composites (Cf/Mg) are fabricated by the pressure infiltration method.The effects of carbon fiber on the interfacial microstructures and mechanical propertiesIn order to meet the requirements of lightweight structural materials in extreme space environment,the T300,T700,and M40 carbon fiber-reinforced magnesium matrix composites (Cf/Mg) are fabricated by the pressure infiltration method.The effects of carbon fiber on the interfacial microstructures and mechanical properties of the Cf/Mg composites are investigated.The results show that there is a serious interfacial reaction product Al4C3 in both the T300/AZ91D and T700/AZ91D composites,which makes the composites brittle fracture under the low stress.However,the amount and size of Al4C3 are reduced significantly at the interfaces in the M40/AZ91D composites,which implies a moderate interfacial bonding strength.Therefore,the M40/AZ91D composite can fully exert its load transfer effect,and ultimately exhibits a high bending strength of 1 100 MPa..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 171 (2024)
Fusion Application of Knowledge Graph and Big Language Model to Aerospace TT&C Question-answering System
Yan SUN, Lixin ZHOU, Lianjun SUN, Bin YE, and Guolin WANG
With the development of natural language processing technology,the intelligent retrieval and question-answering system continuously developed.In order to improve the semantic parsing ability of traditional knowledge graph and the problem that the current general large language model is not deep enough for knowledge leaWith the development of natural language processing technology,the intelligent retrieval and question-answering system continuously developed.In order to improve the semantic parsing ability of traditional knowledge graph and the problem that the current general large language model is not deep enough for knowledge learning in the vertical domain,a large language model method integrating knowledge graph is proposed,and a two-step optimization is carried out.First,on the basis of named entity recognition and relationship extraction,Build a large model Prompt template for auxiliary enhancement generation,using the data stored in the map to provide relevant sources.Second,the low-rank adaptation (LoRA) strategy is used to freeze the original parameters of the large model,and some network parameters are added for fine-tuning training,so as to optimize the knowledge reserve and understanding of the model in the field of aerospace tracking,telemetering,and command (TT&C).Through the two-step improvement,the overall semantic analysis and knowledge details of the model are improved.Combined with the relevant textbooks,reports,and manuals in the field of aerospace TT&C,a knowledge question-answering system is built,and good results are obtained,indicating that the method has certain application value..
AEROSPACE SHANGHAI
- Publication Date: Oct. 25, 2024
- Vol. 41, Issue 5, 178 (2024)