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| 1 | Dynamic modelling and analysis of space webs显示文摘Future space missions demand operations on large flexible structures,for example,space webs,the lightweight cable nets deployable in space,which can serve as platforms for very large structures or be used to capture orbital objects.The interest in research on space webs is likely to increase in the future with the development of promising applications such as Furoshiki sat-ellite of JAXA,Robotic Geostationary Orbit Restorer (ROGER) of ESA and Grapple,Retrieve And Secure Payload (GRASP) of NASA.Unlike high-tensioned nets in civil engineering,space webs may be low-tensioned or tensionless,and extremely flexible,owing to the microgravity in the orbit and the lack of support components,which may cause computational difficulties.Mathematical models are necessary in the analysis of space webs,especially in the conceptual design and evaluation for prototypes.A full three-dimensional finite element (FE) model was developed in this work.Trivial truss elements were adopted to reduce the computational complexity.Considering cable is a compression-free material and its tensile stiffness is also variable,we introduced the cable material constitutive relationship to work out an accurate and feasible model for prototype analysis and design.In the static analysis,the stress distribution and global deformation of the webs were discussed to get access to the knowledge of strength of webs with different types of meshes.In the dynamic analysis,special attention was paid to the impact problem.The max stress and global deformation were investigated.The simulation results indicate the interesting phenomenon which may be worth further research. | YU Yang BAOYIN HeXi LI JunFeng | 2011 | Science China(Physics,Mechanics & Astronomy)2011，54，4： | 11 |
| 2 | Fuel optimal low thrust rendezvous with outer planets via gravity assist显示文摘Low thrust propulsion and gravity assist (GA) are among the most promising techniques for deep space explorations.In this paper the two techniques are combined and treated comprehensively,both on modeling and numerical techniques.Fuel optimal orbit rendezvous via multiple GA is first formulated as optimal guidance with multiple interior constraints and then the optimal necessary conditions,various transversality conditions and stationary conditions are derived by Pontryagin's Maximum Principle (PMP).Finally the initial orbit rendezvous problem is transformed into a multiple point boundary value problem (MPBVP).Homotopic technique combined with random searching globally and Particle Swarm Optimization (PSO),is adopted to handle the numerical difficulty in solving the above MPBVP by single shooting method.Two scenarios in the end show the merits of the present approach. | GUO TieDing JIANG FangHua BAOYIN HeXi LI JunFeng | 2011 | Science China(Physics,Mechanics & Astronomy)2011，54，4： | 8 |
| 3 | Formation reconfiguration in restricted three body problem显示文摘形成在太阳地球的一条光圈轨道附近飞的重构限制了三个身体系统与推动演习被调查。为短时间重构,二推动的演习与分析、数字的方法并且开始结束被调查()方法被证明是一精力最佳二推动的所有( TI )之一重构,和精力消费独立于主要太空船的位置,并且与重构时间减少。然后,基因算法被采用优化精力消费。结果证明最佳的精力与起始、最后的轨道之间的半径差别增加,并且与重构时间减少。 | Shengping Gong Junfeng Li Hexi Baoyin Yunfeng Gao | 2007 | Acta Mechanica Sinica2007，23，3： | 7 |
| 4 | Design and optimization of a trajectory for Moon departure Near Earth Asteroid exploration显示文摘The lunar probe often has some remaining fuel on completing the predefined Moon exploration mission and may carry out some additional tasks from the Moon orbit using the fuel.The possibility for the lunar probe to escape from the Moon and the Earth is analyzed.Design and optimization of the trajectory from the Moon orbit to the Near Earth Asteroids (NEAs) using the spacecraft's residual fuel is studied.At first,the semi-major axis,inclinations and the phase relations with the Earth of all the numbered NEAs are investigated to preliminarily select the possible targets.Based on the Sun-centered two-body problem,the launch window and the asteroid candidates are determined by calculating the minimum delta-v for two-impulse rendezvous mission and one-impulse flyby mission,respectively.For a precise designed trajectory,a full ephemeris dynamical model,which includes gravities of the Sun,the planets and the Moon,is adopted by reading the JPL ephemeris.The departure time,arrival time,burning time duration and thrust angles are set as variables to be designed and optimized.The optimization problem is solved via the Particle Swarm Optimization (PSO) algorithm.Moreover,two feasible NEA flyby missions are presented. | CHEN Yang BAOYIN HeXi LI JunFeng | 2011 | Science China(Physics,Mechanics & Astronomy)2011，54，4： | 7 |
| 5 | Robust extended Kalman filter with input estimation for maneuver tracking显示文摘This study investigates the problem of tracking a satellite performing unknown continuous maneuvers. A new method is proposed for estimating both the state and maneuver acceleration of the satellite. The estimation of the maneuver acceleration is obtained by the combination of an unbiased minimum-variance input and state estimation method and a low-pass filter. Then a threshold-based maneuver detection approach is developed to determinate the start and end time of the unknown maneuvers. During the maneuvering period, the estimation error of the maneuver acceleration is modeled as the sum of a fluctuation error and a sudden change error. A robust extended Kalman filter is developed for dealing with the acceleration estimate error and providing state estimation. Simulation results show that, compared with the Unbiased Minimum-variance Input and State Estimation(UMISE) method, the proposed method has the same position estimation accuracy, and the velocity estimation error is reduced by about 5 times during the maneuver period. Besides, the acceleration detection and estimation accuracy of the proposed method is much higher than that of the UMISE method. | Yuzi JIANG Hexi BAOYIN | 2018 | Chinese Journal of Aeronautics2018，31，9： | 7 |
| 6 | Information retrieval methods for high resolution γ-ray spectra显示文摘A program based on MATLAB 7.0 platform was developed to locate characteristic peak position and calculate net area of characteristic peak.The formula for the calculation of relative standard deviation of net peak area by Sterlinski’s method was found excellent in searching single peaks and resolving overlapping peaks in high resolution gamma-ray spectrum.Gaussian function fitting method using Levenberg-Marquardt algorithm was applied to calculate net area of peaks.A standard test spectrum supplied by the IAEA in 1995 was analyzed by the program and another two widely used commercial software.The analysis results show the program was superior to the latter two in searching single peaks and resolving overlapping peaks.The optimized fitting indexes are found between 0.962 and 0.996,which shows that the program adopted is feasible and accurate for extracting the net peak area in high resolution gamma-ray spectra. | WU Hexi ZHANG Huaiqiang LIU Qingcheng YANG Bo WEI Qianglin YUAN Xinyu | 2012 | Nuclear Science and Techniques2012，23，6： | 6 |
| 7 | Multi-swingby optimization of mission to Saturn using global optimization algorithms显示文摘Based on the trajectory design of a mission toSaturn, this paper discusses four different trajectories in variousswingby cases. We assume a single impulse to be appliedin each case when the spacecraft approaches a celestial body.Some optimal trajectories of EJS, EMS, EVEJS and EVVEJSflying sequences are obtained using five global optimizationalgorithms: DE, PSO, DP, the hybrid algorithm PSODE andanother hybrid algorithm, DPDE. DE is proved to be superiorto other non-hybrid algorithms in the trajectory optimizationproblem. The hybrid algorithm of PSO and DE canimprove the optimization performance of DE, which is validatedby the mission to Saturn with given swingby sequences.Finally, the optimization results of four different swingbysequences are compared with those of the ACT of ES A. | Kaijian Zhu Junfeng Li Hexi Baoyin School of Aerospace, Tsinghua University,100084 Beijing, China | 2009 | Acta Mechanica Sinica2009，25，6： | 5 |
| 8 | Dynamics of surface motion on a rotating massive homogeneous body显示文摘It is of great interest to study the dynamical environment on the surface of non-spherical small bodies, especially for asteroids. This paper takes a simple case of a cube for instance, investigates the dynamics of a particle on the surface of a rotating homogeneous cube, and derives fruitful results. Due to the symmetrical characteristic of the cube, the analysis includes motions on two different types of surfaces. For each surface, both the frictionless and friction cases are considered. (i) Without consideration of friction, the surface equilibria in both of the different surfaces are examined and periodic orbits are derived. The analysis of equilibria and periodic orbits could assist understanding the skeleton of motions on the surface of asteroids. (ii) For the friction cases, the conditions that the particle does not escape from the surface are examined. Due to the effect of the friction, there exist the equilibrium regions on the surface where the particle stays at rest, and the locations of them are found. Finally, the dust collection regions are predicted. Future work will extend to real asteroid shapes. | LIU XiaoDong BAOYIN HeXi MA XingRui | 2013 | Science China(Physics,Mechanics & Astronomy)2013，56，4： | 5 |
| 9 | Feasible region and stability analysis for hovering around elongated asteroids with low thrust显示文摘This paper investigates properties of low-thrust hovering, including the feasible region and stability, in terms of the dynamical parameters for elongated asteroids.An approximate rotating mass dipole model, by which the description of the rotational gravitational field is reduced to two independent parameters, is employed to construct normalized dynamical equations. The boundaries of the feasible region are determined by contours representing the magnitude of the active control. The effects of a rotating gravitational field and maximal magnitude of the low thrust on the feasible hovering regions are analyzed with numerical results. The stability conditions are derived according to the forms of the eigenvalues of the linearized equation near the hovering position. The stable regions are then determined by a grid search and the effects of the relevant parameters are analyzed in a parametric way. The results show that a close hovering can be easier to realize near the middle of the asteroid than near the two ends in the sense of both required control magnitude and stability. | Hong-Wei Yang Xiang-Yuan Zeng Hexi Baoyin | 2015 | Research in Astronomy and Astrophysics2015，15，9： | 5 |
| 10 | Sequence optimization for multiple asteroids rendezvous via cluster analysis and probability-based beam search显示文摘It is of great significance to visit multiple asteroids in a space mission.In this paper,the multiple asteroids mission optimization is implemented using cluster analysis and probability-based beam search.Clustering is performed to select the first asteroid to visit.Four cluster algorithms are investigated and affinity propagation is selected.Then four beam search algorithms that are deterministic beam search and three probability-based beam search variants,probabilistic beam search,ant-colony beam search,and evolving beam search,are applied to search for the rendezvous sequence.Deterministic beam search as a heuristic tree search algorithm is widely applied in multitarget sequence optimization,but it has an obvious drawback of the conflict between the number of pruned nodes and the possibility of finding optimal solutions,which can be improved by probability-based beam search.Among three probability-based beam search,the ant-colony beam search has a learning mechanism,and evolving beam search is constructed based on ant-colony beam search and has an evolutionary mechanism.Results show that the introduction of randomness can improve beam search,and beam search variants with the learning and evolutionary mechanism have an excellent performance. | LI HaiYang BAOYIN HeXi | 2021 | Science China(Technological Sciences)2021，64，1： | 3 |
| 11 | Trajectory design for the Moon departure libration point mission in full ephemeris model显示文摘The lunar probe may still have some remaining fuel after completing its predefined Moon exploration mission and is able to carry out some additional scientific or technological tasks after escaping from the Moon orbit.The Moon departure mission for the lunar probe is the focus of this paper.The possibility of the spacecraft orbiting the Moon to escape the Moon's gravitational pull is analyzed.The trajectory design for the Earth-Moon system libration point mission is studied in a full ephemeris dynamical model,which considers the non-uniform motion of the Moon around the Earth,the gravity of the Sun and planets and the finite thrust of the onboard engine.By applying the Particle Swarm Optimization algorithm,the trajectory design for the transfer from the Moon-centered orbit to the L1 halo orbit,the station-keeping strategies for the Earth-Moon halo orbit and the construction of homoclinic and heteroclinic orbits are investigated.Taking the tracking conditions and engineering constraints into account,two feasible schemes for the Moon departure libration point mission for the lunar probe are presented. | CHEN Yang BAOYIN HeXi LI JunFeng | 2011 | Science China(Technological Sciences)2011，54，11： | 3 |
| 12 | Feasibility analysis of the angular momentum reversal trajectory via hodograph method for high performance solar sails显示文摘In this paper a new phase space of hodograph method is adopted to investigate and better understand the two-dimensional angular momentum reversal(H-reversal) trajectories for high performance solar sails within a fixed cone angle.As the hodograph method and the H-reversal trajectory are not very common,both of them are briefly introduced.The relationship between them are constructed and addressed with a sample trajectory.How the phase space varies according to the sail quality and the fixed sail cone angle is also studied.Through variation of the phase space,the minimum sail lightness number can be obtained by solving a set of algebraic equations instead of a parameter optimization problem.For a given sail lightness number,there are three types of the two-dimensional possible heliocentric motion,including the spiral inward trajectories towards the Sun,the H-reversal trajectories and the directly outward escape trajectories.The boundaries that separate these different groups are easily determined by using the phase space.Finally,the method and procedures to achieve the feasible region of the H-reversal trajectory with required perihelion distance are presented in detail. | ZENG XiangYuan BAOYIN HeXi LI JunFeng GONG ShengPing | 2011 | Science China(Technological Sciences)2011，54，11： | 3 |
| 13 | Optimal four-impulse rendezvous between coplanar elliptical orbits显示文摘Rendezvous in circular or near circular orbits has been investigated in great detail,while rendezvous in arbitrary eccentricity elliptical orbits is not sufficiently explored.Among the various optimization methods proposed for fuel optimal orbital rendezvous,Lawden's primer vector theory is favored by many researchers with its clear physical concept and simplicity in solution.Prussing has applied the primer vector optimization theory to minimum-fuel,multiple-impulse,time-fixed orbital rendezvous in a near circular orbit and achieved great success.Extending Prussing's work,this paper will employ the primer vector theory to study trajectory optimization problems of arbitrary eccentricity elliptical orbit rendezvous.Based on linearized equations of relative motion on elliptical reference orbit (referred to as T-H equations),the primer vector theory is used to deal with time-fixed multiple-impulse optimal rendezvous between two coplanar,coaxial elliptical orbits with arbitrary large eccentricity.A parameter adjustment method is developed for the prime vector to satisfy the Lawden's necessary condition for the optimal solution.Finally,the optimal multiple-impulse rendezvous solution including the time,direction and magnitudes of the impulse is obtained by solving the two-point boundary value problem.The rendezvous error of the linearized equation is also analyzed.The simulation results confirmed the analyzed results that the rendezvous error is small for the small eccentricity case and is large for the higher eccentricity.For better rendezvous accuracy of high eccentricity orbits,a combined method of multiplier penalty function with the simplex search method is used for local optimization.The simplex search method is sensitive to the initial values of optimization variables,but the simulation results show that initial values with the primer vector theory,and the local optimization algorithm can improve the rendezvous accuracy effectively with fast convergence,because the optimal results obtained by the primer vector theory are already very close to the actual optimal solution.If the initial values are taken randomly,it is difficult to converge to the optimal solution. | WANG JianXia BAOYIN HeXi LI JunFeng SUN FuChun | 2011 | Science China(Physics,Mechanics & Astronomy)2011，54，4： | 3 |
| 14 | Effect of silver nanoparticles on an integrated fixed-film activated sludge–sequencing batch reactor: Performance and community structure显示文摘The effects of silver nanoparticles(AgNPs) on reactor performance, extracellular polymeric substances composition and microbial community structure and function in integrated fixed-film activated sludge–sequencing batch reactors(IFAS–SBRs) were investigated.Results showed that the addition of AgNPs from 0.1 to 10 mg/L exhibited no significant effects on nutrient removal. The average overall removal of COD, NH4+–N and PO43-–P was96.6%, 99.9% and 98.8%, respectively. The introduction of AgNPs caused an increase in extracellular polymeric substances content for the sludge and biofilm of IFAS–SBRs. The release of Ag+from Ag NPs and lactate dehydrogenase test implied the low toxicity of AgNPs to IFAS–SBRs. High-throughput sequencing revealed that microbial community structure showed significant shifts at phylum and genus levels after long-term exposure to AgNPs,but core functional groups responsible for nutrient removal remained at high abundance.Bacterial function prediction indicated that the metabolic categories showed no significant shifts under AgNPs stress, therefore good process performance could still be achieved. | Hexi Zhou Guoren Xu | 2019 | Journal of Environmental Sciences2019，31，6： | 2 |
| 15 | A rapid method for validation and visualization of agile Earth-observation satellites scheduling显示文摘This paper describes a rapid method for validation and visualization of agile Earth-observation satellites scheduling.Benefited from the previous work,various algorithms are proposed for scheduling the observations of agile satellites.However,the satellite maneuvers are three-dimensional,this characteristic makes it difficult for the operation engineers to validate and interpret the scheduled solutions.They have to plot these attitude data to analyze different situations such as an observing phase or a slew maneuver.Finally,one tries to imagine the three-dimensional situations from many one-dimensional plots,which is time-consuming and susceptible to errors.Moreover,now it is low-efficiency to deal with the data about ephemeris,targets,etc.,because different software platforms are required.In this research,a validation and visualization method is suggested to overcome this barrier.It is successful to integrate the Satellite Tool Kit ActiveX and the C#programming language.Based on the embedded scheme,all the interaction and assessment can be visualized.Practical techniques for modelling satellite objects,sensor objects,target objects and satellite attitudes are presented.Such a method has been applied for Chinese agile satellites project,and a software interface has been developed.The simulation results indicate that the proposed method is intuitive and efficient.Note that this method is general,and thus it can be applied to other Earth observation missions.Enough details are provided for interested readers to develop the software interface. | Mingwei Yin Jingyang Li Xianyu Wang Hexi Baoyin | 2018 | Astrodynamics2018，2，4： | 2 |
| 16 | Dynamical behavior of flexible net spacecraft for landing on asteroid显示文摘A new era of up-close asteroid exploration has been entered in the 21st century.However,the widely rugged terrain and microgravity field of asteroids still pose significant challenges to the stable landing of spacecraft and may even directly lead to the escape of the explorer.Owing to the substantial energy dissipation arising from the interaction among multiple bodies,the flexible net,which is a typical multibody system,may be capable of overcoming the above problems.In this study,a dynamical model was established to analyze the movement of the flexible net spacecraft(FNS)near and on the asteroid comprehensively.First,we investigated the dynamical environment of the target asteroid by combining the polyhedron method and spherical harmonics parametric surface modeling approach.Thereafter,we constructed the multibody dynamics model of the explorer using the linear Kelvin–Voigt method.Subsequently,we studied the collision process between the FNS and asteroid based on the spring–damper contact dynamics model.The trajectory and speed of the FNS could be derived by solving the system dynamic equations in parallel.Finally,we analyzed the deformation,descent,jumping motion,and surface movement process of the FNS during the movement.Consequently,a promising scheme is provided for asteroid exploration missions in the future. | Yu Zhang Yang Yu Hexi Baoyin | 2021 | Astrodynamics2021，5，3： | 2 |
| 17 | Smad5 acts as an intracellular pH messenger and maintains bioenergetic homeostasis显示文摘环境暗示和细胞内部的 bioenergetic 状态深刻地影响细胞内部的 pH (pHi ) 。一个房间怎么对 pHi 变化作出回应维持 bioenergetic 动态平衡,留下逃犯。这里,我们显示出那 Smad5,发信号的形态基因的蛋白质(BMP ) 回答到 pHi 的骨头的一个描绘得好的下游的部件变化。冷、基本或张力亢进的条件增加 pHi,它接着在 Smad5 的 MH1 域以内声言不赞成控告的氨基酸簇,推动它到细胞质的从原子核的重定位。在另一方面,加热,酸或张力减退的条件减少 pHi,堵住 Smad5 的原子出口,并且因此引起它的原子累积。环境变化和 pHi 变化导致的 Smad5 的活跃 nucleocytoplasmic shuttling 独立于 BMP 发信号, carboxyl 终点 phosphorylation 和 Smad4。另外, Smad5 的脱离引起在区别识别了的神经发展过程人的 pluripotent 干细胞建模的细胞的 bioenergetic 动态平衡和破坏正常的长期、不可逆的 dysregulation。重要地,在 Smad5 缺乏的房间的这些新陈代谢、发展的赤字能仅仅由细胞质的 Smad5 被救。细胞质的 Smad5 身体上与 hexokinase 交往 1 并且加速 glycolysis。一起,我们的调查结果显示 Smad5 充当一个 pHi 送信人并且由调整细胞质的新陈代谢的机械维持房间的 bioenergetic 动态平衡。 | Yujiang Fang Zhongliang Liu Zhenyu Chen Xiangjie Xu Mengtao Xiao Yanyan Yu Yuanyuan Zhang Xiaobai Zhang Yanhua Du Cizhong Jiang Yuzheng Zhao Yiran Wang Beibei Fan Daniel Terheyden-Keighley Yang Liu Lei Shi Yi Hui Xin Zhang Bowen Zhang Hexi Feng Lin Ma Quanbin Zhang Guohua Jin Yi Yang Bin Xiang Ling Liu Xiaoqing Zhang | 2017 | Cell Research2017，27，9： | 2 |
| 18 | New applications of the H-reversal trajectory using solar sails显示文摘Advanced solar sailing has been an increasingly attractive propulsion system for highly non-Keplerian orbits.Three new applications of the orbital angular momentum reversal(H-reversal) trajectories using solar sails are presented:space observation,heliocentric orbit transfer and collision orbits with asteroids.A theoretical proof for the existence of double H-reversal trajectories(referred to as‘H2RTs’) is given,and the characteristics of the H2RTs are introduced before a discussion of the mission applications.A new family of H2RTs was obtained using a 3D dynamic model of the two-body frame.In a time-optimal control model,the minimum period H2RTs both inside and outside the ecliptic plane were examined using an ideal solar sail.Due to the quasi-heliostationary property at its two symmetrical aphelia,the H2RTs were deemed suitable for space observation.For the second application,the heliocentric transfer orbit was able to function as the time-optimal H-reversal trajectory,since its perihelion velocity is a circular or elliptic velocity.Such a transfer orbit can place the sailcraft into a clockwise orbit in the ecliptic plane,with a high inclination or displacement above or below the Sun.The third application of the H-reversal trajectory was simulated impacting an asteroid passing near Earth in a head-on collision.The collision point can be designed through selecting different perihelia or different launch windows.Sample orbits of each application were presented through numerical simulation.The results can serve as a reference for theoretical research and engineering design. | Xiang-Yuan Zeng Hexi Baoyin Jun-Feng Li Sheng-Ping Gong | 2011 | Research in Astronomy and Astrophysics2011，11，7： | 2 |
| 19 | Two-point boundary value problem solutions to spacecraft formation flying 显示文摘 | JIANG FANGHUA LI JUNFENG BAOYIN HEXI | 2009 | Journal of Guidance Control and Dynamics2009，32，6： | 1 |
| 20 | Reachable domain for spacecraft with a single impulse显示文摘 | Xue Dan Li Junfeng Baoyin Hexi | 2010 | Journal of Guidance Control and Dynamics2010，33，3： | 1 |
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