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火星上升器入轨段自适应迭代制导方案设计

深空探测学报（中英文） 2024年第1期11卷 31-39页

作者：宋春郭延宁郭敏文李琨空间物理重点实验室北京100076 哈尔滨工业大学控制科学与工程系哈尔滨150001 北京控制工程研究所北京100094

针对火星上升器入轨段的制导问题,设计了一种自适应迭代制导策略。为降低初始状态偏差和火星环境不确定性的影响,每个周期内在制导坐标系下迭代计算剩余飞行时间,求解出在上升器推力大小固定情况下满足目标点位置与速度矢量约束的最优... 详细信息

针对火星上升器入轨段的制导问题,设计了一种自适应迭代制导策略。为降低初始状态偏差和火星环境不确定性的影响,每个周期内在制导坐标系下迭代计算剩余飞行时间,求解出在上升器推力大小固定情况下满足目标点位置与速度矢量约束的最优控制角,进而实时修正飞行轨迹。仿真结果表明,相较于传统的开环制导方案,提出的方案显著地提升了制导精度,其中高度误差降低3个量级,最大速度误差降低至原开环制导的三分之一,入轨点轨道倾角和偏心率误差均满足基本工程需求,可作为未来火星上升器入轨段制导的一种可靠方案。

关键词：火星上升器入轨段迭代制导最优控制

Orbital rendezvous performance comparison of differential geometric and ZEM/ZEV feedback guidance algorithms

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Astrodynamics 2019年第1期3卷 79-92页

作者： Pengyu Wang yanning guo Bong Wie Department of Control Science and Engineering Harbin Institute of TechnologyHarbin150001China Department of Aerospace Engineering Iowa State UniversityAmesIA50011USA

In this paper,the performance of two distinct classes of feedback guidance algorithms is evaluated for a spacecraft rendezvous problem utilizing a continuous low-thrust propulsion system.They are the DG(Differential Geometric)and ZEM/ZEV(Zero-Effort-Miss/Zero-Effort-Velocity)feedback guidance algorithms.Even though these two guidance algorithms do not attempt to minimize the onboard fuel consumption orΔV directly,theΔV requirement is used as a measure of their orbital rendezvous performance for various initial conditions and a wide range of the rendezvous time(within less than one orbital period of the target vehicle).For the DG guidance,the effects of its guidance parameter and terminal time on the closed-loop performance are evaluated by numerical simulations.For the ZEM/ZEV guidance,its nearfuel-optimality is further demonstrated for a rapid,short-range orbital rendezvous,in comparison with the corresponding open-loop optimal solutions.Furthermore,the poorΔV performance of the ZEM/ZEV guidance for a slow,long-range orbital rendezvous is remedied by simply adding an initial drift phase.The ZEM/ZEV feedback guidance algorithm and its appropriate variants are then shown to be a simple practical solution to a non-impulsive rendezvous problem,in comparison with the DG guidance as well as the open-loop optimal guidance.

关键词： differential geometric guidance ZEM/ZEV feedback guidance orbital rendezvous initial drift phase

Orbital-Ordering Driven Simultaneous Tunability of Magnetism and Electric Polarization in Strained Monolayer VCl_(3)

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Chinese Physics Letters 2024年第4期41卷 126-131页

作者：郭的坪王聪王侣锦陆赟豪吴骅张妍宁季威 Beijing Key Laboratory of Optoelectronic Functional Materials&Micro-Nano Devices Department of PhysicsRenmin University of ChinaBeijing 100872China Key Laboratory of Quantum State Construction and Manipulation(Ministry of Education) Renmin University of ChinaBeijing 100872China Zhejiang Province Key Laboratory of Quantum Technology and Device State Key Laboratory of Silicon MaterialsDepartment of PhysicsZhejiang UniversityHangzhou 310027China Laboratory for Computational Physical Sciences(MOE) State Key Laboratory of Surface Physicsand Department of PhysicsFudan UniversityShanghai 200433China Institute of Fundamental and Frontier Sciences University of Electronic Science and Technology of ChinaChengdu 610054China

Two-dimensional(2D)van der Waals magnetic materials have promising and versatile electronic and magnetic properties in the 2D limit,indicating a considerable potential to advance spintronic applications.Theoretical predictions thus far have not ascertained whether monolayer VCl_(3) is a ferromagnetic(FM)or anti-FM monolayer;this also remains to be experimentally verified.We theoretically investigate the influence of potential factors,including C_(3) symmetry breaking,orbital ordering,epitaxial strain,and charge doping,on the magnetic ground state.Utilizing first-principles calculations,we predict a collinear type-Ⅲ FM ground state in monolayer VCl_(3) with a broken C_(3) symmetry,wherein only the former two of three t_(2g)orbitals(a_(1g),e_(g2)^(π)and e_(g1)^(π))are occupied.The atomic layer thickness and bond angles of monolayer VCl_(3) undergo abrupt changes driven by an orbital ordering switch,resulting in concomitant structural and magnetic phase transitions.Introducing doping to the underlying Cl atoms of monolayer VCl_(3) without C_(3) symmetry simultaneously induces in-and out-of-plane polarizations.This can achieve a multiferroic phase transition if combined with the discovered adjustments of magnetic ground state and polarization magnitude under strain.The establishment of an orbital-ordering driven regulatory mechanism can facilitate deeper exploration and comprehension of magnetic properties of strongly correlated systems in monolayer VCl_(3).

关键词： monolayer symmetry orbital

Data-driven model-free adaptive attitude control of partially constrained combined spacecraft with external disturbances and input saturation

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Chinese Journal of Aeronautics 2019年第5期32卷 1281-1293页

作者： Han GAO Guangfu MA Yueyong LYU yanning guo Department of Control Science and Control Engineering Harbin Institute of Technology

This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a novel dynamic linearization data model for the partially constrained combined spacecraft with external disturbances is established. The generalized disturbances composed of external disturbances and dynamic linearization errors are then reconstructed by a Discrete Extended State Observer(DESO). With the dynamic linearization data model and reconstructed information, a DESO-MFAC strategy for the combined spacecraft is proposed based only on input and output data. Next, the input saturation is overcome by introducing an antiwindup compensator. Finally, numerical simulations are carried out to demonstrate the effectiveness and feasibility of the proposed controller when the dynamic properties of the partially constrained combined spacecraft are completely unknown.

关键词： Attitude control Combined spacecraft Data-driven control Discrete Extended State Observer(DESO) Input saturation

Three-dimensional finite-time cooperative guidance for multiple missiles without radial velocity measurements

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Chinese Journal of Aeronautics 2019年第5期32卷 1294-1304页

作者： Teng LYU Chuanjiang LI yanning guo Guangfu MA Department of Control Science and Engineering Harbin Institute of Technology

In order to simultaneously attack a target with impact angle constraint in threedimensional(3-D) space, a novel distributed cooperative guidance law for multiple missiles under directed communication topologies is proposed without radial velocity measurements. First, based on missiles-target 3-D relative motion equations, the multiple missiles cooperative guidance model with impact angle constraint is constructed. Then, in Line-of-Sight(LOS) direction, based on multiagent system cooperative control theory, one guidance law with directed topologies is designed with strict proof, which can guarantee finite time consensus of multiple missiles' impact times. Next, in elevation direction and azimuth direction of LOS, based on homogeneous system stability theory and integral sliding mode control theory, two guidance laws are proposed respectively with strict proof, which can guarantee LOS angles converge to desired values and LOS angular rates converge to zero in finite time. Finally, the effectiveness of the designed cooperative guidance law is demonstrated through simulation results.

关键词： 3-D cooperative guidance Directed communication topologies Finite time Impact angle constraint Radial velocity measurements

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无限对序列观测者的双边纠缠目击

中国科学：物理学、力学、天文学 2024年第6期54卷 159-165页

作者：王静郭奋卓贾燕宁北京邮电大学理学院北京100876 河南省网络密码技术重点实验室郑州450001 北京邮电大学数学与信息网络教育部重点实验室北京100876

本文研究带噪声的两量子比特纠缠态的双边序列纠缠检测问题.根据目击算子和测量策略找到了一类可以实现无限对Alice和Bob共享纠缠的态.本文给出了这类态能够实现无限对Alice和Bob共享纠缠的具体证明过程,并对作为这类态的特例的两量子... 详细信息

本文研究带噪声的两量子比特纠缠态的双边序列纠缠检测问题.根据目击算子和测量策略找到了一类可以实现无限对Alice和Bob共享纠缠的态.本文给出了这类态能够实现无限对Alice和Bob共享纠缠的具体证明过程,并对作为这类态的特例的两量子比特最大纠缠态、一般纠缠纯态以及Werner态进行了具体的图例分析.实现带噪声的两体系统纠缠态族的任意对观测者的双边纠缠共享在多用户场景和量子网络中有重要意义.

关键词：量子密码纠缠共享序列测纠缠目击

Spacecraft formation-containment flying control with time-varying translational velocity

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Chinese Journal of Aeronautics 2020年第1期33卷 271-281页

作者： Liangming CHEN Chuanjiang LI yanning guo Guangfu MA Baolong ZHU Department of Control Science and Engineering Harbin Institute of TechnologyHarbin 150001China School of Electrical Engineering and Automation Qilu University of Technology(Shandong Academy of Sciences)Jinan 250353China

This paper investigates the problem of Spacecraft Formation-Containment Flying Control(SFCFC)when the desired translational velocity is time-varying.In SFCFC problem,there are multiple leader spacecraft and multiple follower spacecraft and SFCFC can be divided into leader spacecraft’s formation control and follower spacecraft’s containment control.First,under the condition that only a part of leader spacecraft can have access to the desired time-varying translational velocity,a velocity estimator is designed for each leader spacecraft.Secondly,based on the estimated translational velocity,a distributed formation control algorithm is designed for leader spacecraft to achieve the desired formation and move with the desired translational velocity simultaneously.Then,to ensure all follower spacecraft converge to the convex hull formed by the leader spacecraft,a distributed containment control algorithm is designed for follower spacecraft.Moreover,to reduce the dependence of the designed control algorithms on the graph information and increase system robustness,the control gains are changing adaptively and the parametric uncertainties are handled,respectively.Finally,simulation results are provided to illustrate the effectiveness of the theoretical results.

关键词： Adaptive gain technique Distributed control Formation-containment Formation control Spacecraft formation flying

Optimal terminal-time determination for the ZEM/ZEV feedback guidance law with generalized performance index

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Astrodynamics 2019年第2期3卷 127-136页

作者： Jaemyung Ahn Pengyu Wang yanning guo Bong Wie Department of Aerospace Engineering KAISTDaejeon 34141Republic of Korea Department of Control Science and Engineering Harbin Institute of TechnologyHarbin 150001China Department of Aerospace Engineering Iowa State UniversityIA 50011USA

This paper investigates a problem of determining the optimal terminal-time or time-to-go of the ZEM/ZEV(Zero-E ort-Miss/Zero-E ort-Velocity)feedback guidance law for a variety of orbital intercept or rendezvous maneuvers.A generalized ZEM/ZEV guidance problem,whose objective is to minimize a combination of the control energy and terminal time,is examined.Algebraic equations whose solution provides the optimal terminal-time of the orbital intercept/rendezvous problems are derived based on the optimal control theory.The e ectiveness of the proposed approach is demonstrated for various orbital maneuver problems.

关键词： Zero-Effort-Miss/Zero-Effort-Velocity(ZEM/ZEV) optimal feedback guidance terminal-time determination intercept rendezvous

电推进GEO卫星的改进粒子群轨道保持优化设计

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宇航学报 2024年第4期45卷 523-531页

作者：吕跃勇王成李笑月郑重郭延宁哈尔滨工业大学航天学院哈尔滨150001 中国科学院微小卫星创新研究院上海201203 哈尔滨工业大学机电工程学院哈尔滨150001

针对地球同步轨道(GEO)卫星轨道保持问题,提出了一种基于改进粒子群算法(PSO)的序列电推力轨道保持方法。首先,建立了GEO卫星高精度非线性轨道动力学模型和序列电推力模型。然后,设计了GEO卫星相对轨道保持策略,建立了以燃料消耗为性能... 详细信息

针对地球同步轨道(GEO)卫星轨道保持问题,提出了一种基于改进粒子群算法(PSO)的序列电推力轨道保持方法。首先,建立了GEO卫星高精度非线性轨道动力学模型和序列电推力模型。然后,设计了GEO卫星相对轨道保持策略,建立了以燃料消耗为性能指标的序列电推力轨道保持问题优化模型并进行了离散化。接着,通过引入差分进化算法和维度学习策略对粒子群优化算法进行了适应性改进,同时对推力大小和作用时间进行寻优计算。最后,通过数值仿真对所提出的改进粒子群优化算法进行了对比校验。结果表明,该方法在完成GEO卫星轨道保持任务的同时具备燃料消耗低和收敛速度快等优点。

关键词：卫星轨道保持电推进粒子群优化差分进化维度学习