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Current status and prospects of guidance techniques for intercepting hypersonic glide vehicles:A review 认领 引用 被引量：2
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作者 Feng Wang Qiankun Qu +3 位作者 Hao Yang Shou Zhou Xibin Bai Shifeng Zhang 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2026年第4期241-259,共19页
Hypersonic vehicles present formidable challenges to existing air and missile defence systems due to their extreme velocity,extended-range strike capability,and exceptional maneuverability,driving the need for advance... Hypersonic vehicles present formidable challenges to existing air and missile defence systems due to their extreme velocity,extended-range strike capability,and exceptional maneuverability,driving the need for advanced guidance technologies of interceptors.To address the requirements for defensive operations against hypersonic vehicles,this review focuses on hypersonic glide vehicles(HGVs)as the primary object of study.Their flight characteristics are simulated,and critical interception challenges are analyzed.Then,key technological advancements in interceptor guidance,including midcourse guidance techniques,mid-terminal guidance handover,and terminal guidance laws,are reviewed,providing a comparative analysis of their respective strengths and limitations.Finally,the research summarizes the pivotal scientific problems confronting interceptor guidance technology and provides prospects for the research directions of related technologies.These findings provide a valuable reference for subsequent research on interceptor guidance technology and facilitate the development of next-generation aerospace defence architectures. 展开更多
关键词 Hypersonic glide vehicles interception Trajectory planning Trajectory tracking control Mid-terminal guidance handover Terminal guidance law Cooperative guidance
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Three-dimensional cooperative guidance law with practical predefined-time approach angle and time-to-go convergence 认领 引用 被引量：1
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作者 Zihao WU Wei FENG +3 位作者 Xiaofeng ZHANG Wenxing FU Zhang REN Tuo HAN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第5期530-546,共17页
This paper presents a Three-Dimensional(3D)cooperative guidance law with Practical Predefined-Time(PPT)convergence for multiple missiles considering approach angle(terminal lineof-sight)and simultaneous arrival constr... This paper presents a Three-Dimensional(3D)cooperative guidance law with Practical Predefined-Time(PPT)convergence for multiple missiles considering approach angle(terminal lineof-sight)and simultaneous arrival constraints.To achieve a salvo attack against a maneuvering target from various directions,the guidance problem is tackled by addressing two critical factors:ensuring that the time-of-arrival is consistent and that the desired approach angles can be met.Considering the short duration of the homing guidance process,the convergence with predefined time for guidance states(especially the approach angle and time-to-go)is factored in.First,for the simultaneous arrival,a PPT guidance law is developed,which can meet the same time-to-go convergence rate in the Line-of-Sight(LOS)direction.Then,in the normal LOS direction,a 3D PPT guidance law is presented considering the approach angle constraint so that the desired approach angles can be reached within a user-designed time.The time-based generator technique is employed in the proposed PPT Cooperative Guidance Law(PPTCGL)to avoid the time-varying gain singularity issue.Notably,this technique can allow the convergence time to be preset in advance,independent of initial system conditions and tuning parameters.Additionally,to avoid excessive gain and improve the robustness of guidance law,a PPT disturbance observer is designed against uncertainties and target maneuvers so that the guidance system perturbation can be compensated in real time.It is userfriendly that the convergence of disturbance estimation can be met with a flexible pre-setting time before achieving the terminal guidance constraints.Finally,extensive numerical simulations are conducted to verify the effectiveness and robustness of the proposed PPTCGL in both the nominal cases and the Monte Carlo test. 展开更多
关键词 Approach angle constraint Cooperative guidance law Maneuvering target Practical predefined-time consensus Three-dimensional guidance model
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Two-phase differential game guidance scheme against active defensive aircraft in three-body engagement 认领 引用
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作者 Xintao WANG Tao CHAO +2 位作者 Mingzhe HOU Songyan WANG Ming YANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第3期530-545,共16页
This paper proposes a two-phase game guidance strategy for the three-body confrontation scenario according to the linear quadratic differential game method,which includes an Attacker,an Interceptor,and a Target.The in... This paper proposes a two-phase game guidance strategy for the three-body confrontation scenario according to the linear quadratic differential game method,which includes an Attacker,an Interceptor,and a Target.The interception probabilities between the Attacker and the Interceptor-Target team are estimated using the probability density function.The desired zero-effort miss distances associated with the interception probabilities for the three-body conflict are acquired by virtue of the gradient descent method.The game combat is divided into two phases by introducing the switching time.In Phase 1,a differential game strategy is developed to guide the zero-control miss distance between the Attacker and the Interceptor-Target into the desired position,which guarantees that the Attacker has the maximizing probability of intercepting the Target and the minimizing probability of being captured by the Interceptor.In Phase 2,a differential game guidance strategy is proposed to ensure that the Attacker evades the pursuit of the Interceptor and intercepts the Target at the preset impact angle.Finally,numerical simulation verifies the effectiveness of the two-stage game guidance strategy. 展开更多
关键词 Active defensive aircraft Differential game Guidance law Three-body engagement Two-phase guidance
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Regulatory role of neuronal guidance proteins in spinal cord injury 认领 引用 被引量：3
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作者 Linyan Tang Zhi Song +2 位作者 Jie Wang Shenghua He Chao Liu 《Neural Regeneration Research》 SCIE CAS CSCD 2026年第6期2137-2144,共8页
Spinal cord injury is a severe neurological condition with limited neuronal regeneration and functional recovery.Currently,no effective treatments exist to improve spinal cord injury prognosis.Neuronal guidance protei... Spinal cord injury is a severe neurological condition with limited neuronal regeneration and functional recovery.Currently,no effective treatments exist to improve spinal cord injury prognosis.Neuronal guidance proteins are a diverse group of molecules that play crucial roles in axon and dendrite growth during nervous system development.Increasing evidence highlights their regulatory functions in spinal cord injury.This review provides a brief overview of the modulation patterns of key neuronal guidance proteins in neuronal axon growth during nervous system formation and subsequently focuses on their roles in neuronal regeneration and functional recovery following spinal cord injury.Neuronal guidance proteins include,but are not limited to,semaphorins and their receptors,plexins;netrins and their receptors,deleted in colorectal cancer and UNC5;Eph receptors and their ligands,ephrins;Slit and its receptor,Robo;repulsive guidance molecules and their receptor,neogenin;Wnt proteins and their receptor,Frizzled;and protocadherins.Localized Netrin-1 at the injury site inhibits motor axon regeneration after adult spinal cord injury while promoting oligodendrocyte growth.Slit2 enhances synapse formation in the injured spinal cord of rats.EphA7 regulates acute apoptosis in the early pathophysiological stages of spinal cord injury,while ephrinA1 plays a role in the nervous system’s injury response,with its reduced expression leading to impaired motor function in rats.EphA3 is upregulated following spinal cord injury,promoting an inhibitory environment for axonal regeneration.After spinal cord injury,bidirectional activation of ephrinB2 and EphB2 in astrocytes and fibroblasts results in the formation of a dense astrocyte-meningeal fibroblast scar.EphB1/ephrinB1 signaling mediates pain processing in spinal cord injury by regulating calpain-1 and caspase-3 in neurons.EphB3 expression increases in white matter after spinal cord injury,further inhibiting axon regeneration.Sema3A,expressed by neurons and fibroblasts in the scar surrounding the injury,inhibits motor neuron and sensory nerve growth after spinal cord injury.Sema4D suppresses neuronal axon myelination and axon regeneration,while its inhibition significantly enhances axon regeneration and motor recovery.Sema7A is involved in glial scar formation and may influence serotonin channel remodeling,thereby affecting motor coordination.Given these findings,the local or systemic application of neuronal guidance proteins represents a promising avenue for spinal cord injury treatment. 展开更多
关键词 Eph ephrin Netrin-1 neuronal guidance protein neuronal regeneration neuronal guidance protein SEMA3A SEMA4D semaphorin Slit spinal cord injury
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Neuronal guidance signaling in neurodegenerative diseases:Key regulators that function at neuron-glia and neuroimmune interfaces 认领 引用 被引量：1
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作者 Junichi Yuasa-Kawada Mariko Kinoshita-Kawada +6 位作者 Masaki Hiramoto Satoru Yamagishi Takayasu Mishima Shin’ichiro Yasunaga Yoshio Tsuboi Nobutaka Hattori Jane Y.Wu 《Neural Regeneration Research》 SCIE CAS CSCD 2026年第2期612-635,共24页
The nervous system processes a vast amount of information,performing computations that underlie perception,cognition,and behavior.During development,neuronal guidance genes,which encode extracellular cues,their recept... The nervous system processes a vast amount of information,performing computations that underlie perception,cognition,and behavior.During development,neuronal guidance genes,which encode extracellular cues,their receptors,and downstream signal transducers,organize neural wiring to generate the complex architecture of the nervous system.It is now evident that many of these neuroguidance cues and their receptors are active during development and are also expressed in the adult nervous system.This suggests that neuronal guidance pathways are critical not only for neural wiring but also for ongoing function and maintenance of the mature nervous system.Supporting this view,these pathways continue to regulate synaptic connectivity,plasticity,and remodeling,and overall brain homeostasis throughout adulthood.Genetic and transcriptomic analyses have further revealed many neuronal guidance genes to be associated with a wide range of neurodegenerative and neuropsychiatric disorders.Although the precise mechanisms by which aberrant neuronal guidance signaling drives the pathogenesis of these diseases remain to be clarified,emerging evidence points to several common themes,including dysfunction in neurons,microglia,astrocytes,and endothelial cells,along with dysregulation of neuron-microglia-astrocyte,neuroimmune,and neurovascular interactions.In this review,we explore recent advances in understanding the molecular and cellular mechanisms by which aberrant neuronal guidance signaling contributes to disease pathogenesis through altered cell-cell interactions.For instance,recent studies have unveiled two distinct semaphorin-plexin signaling pathways that affect microglial activation and neuroinflammation.We discuss the challenges ahead,along with the therapeutic potentials of targeting neuronal guidance pathways for treating neurodegenerative diseases.Particular focus is placed on how neuronal guidance mechanisms control neuron-glia and neuroimmune interactions and modulate microglial function under physiological and pathological conditions.Specifically,we examine the crosstalk between neuronal guidance signaling and TREM2,a master regulator of microglial function,in the context of pathogenic protein aggregates.It is well-established that age is a major risk factor for neurodegeneration.Future research should address how aging and neuronal guidance signaling interact to influence an individual’s susceptibility to various late-onset neurological diseases and how the progression of these diseases could be therapeutically blocked by targeting neuronal guidance pathways. 展开更多
关键词 amyloid-β axon guidance neurodegeneration neuroimmune interactions neuroinflammation neuron-glia interactions neurovascular interactions semaphorin synaptic remodeling tau TDP-43 TREM2 α-synuclein
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Quantized cooperative salvo guidance under limited bandwidth with time-varying directed topology 认领 引用
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作者 Peisheng WANG Chaoyang DONG +2 位作者 Xiaohui LIANG Xuehu MA Shen ZHANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第3期480-498,共19页
This study presents the development and evaluation of a quantized cooperative salvo guidance law designed to achieve simultaneous attacks on stationary targets under communication bandwidth constraints.A novel joint d... This study presents the development and evaluation of a quantized cooperative salvo guidance law designed to achieve simultaneous attacks on stationary targets under communication bandwidth constraints.A novel joint design methodology for encoders,decoders,and guidance laws is proposed,effectively overcoming cooperative guidance challenges in time-varying directed topology with limited bandwidth.This approach identifies the minimum bandwidth requirements for executing salvo attacks and provides valuable insights into the trade-offs between communication resource allocation and operational effectiveness.The method is systematically extended to two-dimensional cooperative guidance in fixed directed topology and further adapted to threedimensional cooperative guidance in time-varying directed topology,demonstrating its adaptability and scalability across different dimensions and network dynamics.Extensive simulations conducted in diverse operational scenarios validate the proposed guidance laws,showcasing their robust performance and practical feasibility. 展开更多
关键词 Cooperative guidance Salvo attack Bandwidth Time-varying topology Impact Time Control Guidance(ITCG)
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Exponential predefined-time spatial–temporal cooperative guidance method with obstacle avoidance 认领 引用
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作者 Guofei LI Yanan CHANG +1 位作者 Yonghua FAN Hua XIONG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第7期555-571,共17页
This paper investigates the cooperative guidance problem with effective obstacle avoidance considering spatial-temporal constraint.A novel cooperative guidance methodology is presented to make multiple flight vehicles... This paper investigates the cooperative guidance problem with effective obstacle avoidance considering spatial-temporal constraint.A novel cooperative guidance methodology is presented to make multiple flight vehicles not only attack the target with desired Line-of-Sight(LOS)angle intervals simultaneously,but also avoid the obstacle safely.First,we design the temporal cooperative guidance law along the LOS direction to meet the requirement of the simultaneous arrival,and present the lateral cooperative guidance law by utilizing the errors of the bias LOS angles to form the desired angle intervals.Then,the constraints of impact time and LOS angle are considered in the spatial-temporal cooperative guidance law.To achieve obstacle avoidance,an additional obstacle avoidance acceleration command is derived.This command leverages realtime measurements of both the distance and the relative orientation between each flight vehicle and nearby obstacles,generating repulsive maneuvers as needed.Finally,weighting coefficients,dynamically adjusted based primarily on the proximity to obstacles,are introduced to optimally blend the cooperative guidance acceleration components and the obstacle avoidance acceleration components.This allows the flight vehicles to prioritize obstacle evasion when critically close,while seamlessly resuming coordinated flight towards the target when safe,achieving spatial-temporal coordination and robust obstacle avoidance concurrently.Both theoretical analysis and numerical simulation demonstrate the effectiveness and robustness of the presented cooperative guidance approach. 展开更多
关键词 Cooperative guidance Impact time Line-of-sight angle Obstacle avoidance Spatial-temporal constraint
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Adaptive fixed-time fuzzy fault-tolerant cooperative spiral-diving guidance law with initial state-independent prescribed performance 认领 引用
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作者 Tianyi WU Zheng WANG +2 位作者 Caisheng WEI Xin NING Zhansheng CHEN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第5期483-503,共21页
This paper proposes a novel performance guaranteed fixed-time fuzzy adaptive faulttolerant cooperative spiral-diving guidance law for a group of flight vehicles subject to system internal uncertainties,actuator faults... This paper proposes a novel performance guaranteed fixed-time fuzzy adaptive faulttolerant cooperative spiral-diving guidance law for a group of flight vehicles subject to system internal uncertainties,actuator faults,and external disturbances simultaneously.Firstly,based on the analysis of the spiral-diving terminal guidance process,a novel set of guidance dynamic equations,which is different from the traditional line-of-sight angle equations but suitable for the design of a cooperative spiral guidance law,is established.Thereafter,by designing a novel Initial StateIndependent Fixed-Time Prescribed Performance Function(ISIFTPPF),the time-to-go free virtual guidance law that can ensure prescribed performance in spite of any initial condition is developed to generate spiral maneuvers.Subsequently,the fixed-time adaptive guidance law based on the auxiliary subsystem is designed,ensuring that actuator saturation constraints can be satisfied and the unknown disturbances as well as actuator faults can be effectively handled.It should be noted that the proposed method is a low-complexity hierarchical spiral guidance scheme that can remarkably reduce the consumption of computational resources.Theoretical analysis illustrates that the closedloop system is practically fixed-time stable,and the tracking errors will converge within the pregiven boundaries.Finally,the effectiveness,superiority,and practical application potential of the proposed cooperative guidance method are demonstrated by several numerical simulations. 展开更多
关键词 Adaptive fuzzy faulttolerant Cooperative guidance Multiple constraints Multiple flight vehicles Practical fixed-time stability Spiral trajectories
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Robust powered descent guidance considering mass and fuel consumption uncertainties:A convex optimization approach 认领 引用
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作者 Duozhi GAO Yanning GUO +3 位作者 Edoardo FADDA Youmin GONG Chuanjiang LI Paolo BRANDIMARTE 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第3期546-570,共25页
This paper addresses the challenge of mass uncertainty during the powered descent phase of a Mars lander and proposes a robust powered descent guidance algorithm that accounts for uncertainties in mass and fuel consum... This paper addresses the challenge of mass uncertainty during the powered descent phase of a Mars lander and proposes a robust powered descent guidance algorithm that accounts for uncertainties in mass and fuel consumption.First,the traditional trajectory optimization method based on convex optimization is improved by developing a fast and accurate solution approach using sequential convex optimization.Second,the effects of mass uncertainty on position are modeled and analyzed,with corresponding computational methods provided for different scenarios.Third,the worst-case scenario under mass uncertainty is analyzed through both geometric and theoretical approaches,and a modified glide-slope constraint method is proposed to ensure safe landing even in adverse conditions.Moreover,a closed-loop receding horizon based guidance is developed to further mitigate the effects of mass uncertainty and improve terminal landing accuracy.Finally,the proposed improved convex optimization algorithm and robust trajectory optimization algorithm are validated through simulation cases and compared with a probabilistic approach.The simulations further test various initial positions,velocities,and glide-slope angles,demonstrating that the solutions are both accurate and robust. 展开更多
关键词 Uncertainty Trajectory optimization Convex optimization Powered descent Closed-loop guidance
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Transparent high-frequency ultrasound transducer array for real-time interventional photoacoustic guidance 认领 引用
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作者 Junwei Wu Zhongwen Cheng +3 位作者 Chen Liang Yan Chen Lvming Zeng Xuanrong Ji 《Journal of Innovative Optical Health Sciences》 SCIE EI CSCD 2026年第3期70-81,共12页
Photoacoustic tomography(PAT)provides both structural and functional information,making it a powerful tool for guiding interventional procedures.However,conventional ultrasound transducers are generally optically opaq... Photoacoustic tomography(PAT)provides both structural and functional information,making it a powerful tool for guiding interventional procedures.However,conventional ultrasound transducers are generally optically opaque,complicating PAT system design and hindering seamless integration with other optical imaging modalities.A novel transparent ultrasound transducer(TUT)linear array has been developed specifically for real-time interventional guidance.The TUT array-based PAT system demonstrates high performance with 378.2μm lateral resolution,599.1μm axial resolution,and a fast imaging rate of 0.05s/frame.The system’s interventional imaging capability was demonstrated through real-time visualization of needle morphology and dye diffusion during injections in chicken breast tissue.In summary,the TUT array enables potential applications in real-time multimodal imaging,combining photoacoustic,ultrasound,and optical modalities for comprehensive tissue characterization. 展开更多
关键词 Photoacoustic tomography transparent ultrasound transducer interventional guidance
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Time control entry guidance method for hypersonic glide vehicles based on deep reinforcement learning 认领 引用
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作者 Zhenyu LIU Gang LEI +3 位作者 Yong XIAN Leliang REN Shaopeng LI Daqiao ZHANG 《Journal of Zhejiang University-SCIENCE A》 SCIE EI CAS CSCD 2026年第4期365-383,I0016-I0025,I0051,共19页
To meet the requirement of simultaneous arrival for multiple hypersonic glide vehicles(HGVs),we propose a time control entry guidance(TCEG)method leveraging deep reinforcement learning.First,the entry guidance problem... To meet the requirement of simultaneous arrival for multiple hypersonic glide vehicles(HGVs),we propose a time control entry guidance(TCEG)method leveraging deep reinforcement learning.First,the entry guidance problem is solved with a reinforcement learning framework based on a designed reference flight profile.By appropriately designing the observation space and training environment,the well-trained agent demonstrates robust guidance performance under varying widths of the heading error corridor.Then,a novel method for predicting the remaining flight time is established,which consists of two main components.The first component estimates the remaining flight time using an analytical formula,while the second component employs a deep neural network(DNN)to predict the residual error between the estimated and the true value.Subsequently,based on the predicted terminal time error,the threshold of the heading error and the observation vector are corrected in real time,thereby guiding the agent to dynamically adjust its output actions.This enables precise control of the terminal time.Since the generation of guidance commands only requires forward computations by the neural network,the proposed method exhibits excellent real-time performance.Finally,the effectiveness and robustness of the method are demonstrated through numerical simulations in various scenarios. 展开更多
关键词 Hypersonic glide vehicles(HGVs) Entry guidance Reinforcement learning Time coordination Deep neural network(DNN)
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Constrained RLV guidance via pseudospectral model predictive convex programming and predefined-height sliding mode approach 认领 引用
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作者 Zhe LIU Naigang CUI +1 位作者 Feng ZHANG Jialun PU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第5期466-482,共17页
Online trajectory generation and tracking for the Terminal Area Energy Management(TAEM)phase of a Reusable Launch Vehicle(RLV)is one of the core technologies for achieving a soft landing.The processing of complex non-... Online trajectory generation and tracking for the Terminal Area Energy Management(TAEM)phase of a Reusable Launch Vehicle(RLV)is one of the core technologies for achieving a soft landing.The processing of complex non-convex path constraints significantly reduces the real-time performance of guidance methods.In addition,the terminal full-element state constraints are difficult to satisfy due to the coupling of longitudinal and lateral motion of RLV.To address these issues,a high-precision constrained guidance method for RLV is proposed in this paper.The analytical sensitivity relationships among the terminal states,non-convex path constraints,and control profile are rapidly constructed via multi-interval pseudospectral discretization.The repeated recursive calculation of sensitivity matrix is avoided by linearizing the non-convex constraints at state output points and expanding the sensitivity matrix sequentially,which reduces the time consumption of constraint processing.Furthermore,a model-based prediction-correction process is introduced to eliminate deviation iteratively and constraints are handled using homotopy to improve convergence.Meanwhile,a robust parallel guidance method is presented to overcome numerical instability issues.The guidance commands obtained by trajectory online generation are prioritized executed,while the tracking commands are calculated in parallel to enhance the guidance feasibility.Instead of tracking a fixed reference trajectory,a predefined height-convergent sliding mode surface is designed and tracked online,which can guarantee that the RLV states converge to the desired values at a preset height,even under various uncertainties.Finally,Monte Carlo simulations are conducted to demonstrate the effectiveness and robustness of the proposed method. 展开更多
关键词 Convex optimization Model predictive Parallel guidance Pseudospectral discretization Reusable launch vehicle
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Approach angle constrained and varying speed cooperative guidance against maneuvering targets 认领 引用
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作者 Xiangjun Ding Jianan Wang +1 位作者 Junhui Liu Jiayuan Shan 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2026年第3期56-70,共15页
This paper addresses the three-dimensional(3-D)approach angle constrained cooperative guidance problem for speed-varying missiles against maneuvering targets.First,the guidance problem is formulated in a relative refe... This paper addresses the three-dimensional(3-D)approach angle constrained cooperative guidance problem for speed-varying missiles against maneuvering targets.First,the guidance problem is formulated in a relative reference frame and a virtual control input is selected.Then,the cooperative guidance law is designed on the basis of a prediction-correction framework.The time-to-go under the baseline command is estimated by an efficient prediction method with a realistic aerodynamic model and a biased command is developed by utilizing the time-to-go predictions for synchronizing different missiles'impact times.The design of the biased command is decoupled into the individual design of its direction and magnitude.It is proved that the designed cooperative guidance law can make the time-to-go consensus error converge to zero before interception.Finally,the designed guidance law is validated through a series of numerical simulations. 展开更多
关键词 Cooperative guidance Maneuvering target Time-varying speed Approach angle constraint
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Impact time and angle guidance strategy with maximum lateral acceleration constraints:Theory and experiment 认领 引用 被引量：1
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作者 Heng LI Xiaokang LÜ +3 位作者 Jianglong YU Qing WANG Kun ZHANG Xiwang DONG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第7期47-63,共17页
An Impact Time and Angle Control Guidance(ITACG)problem with constraints on maximum lateral acceleration is investigated in this paper.The goal for this problem is to achieve precise interception of a stationary targe... An Impact Time and Angle Control Guidance(ITACG)problem with constraints on maximum lateral acceleration is investigated in this paper.The goal for this problem is to achieve precise interception of a stationary target at the desired impact time and angle,while considering the maximum lateral acceleration constraint during the guidance process.The previous ITACG methods generally struggled to handle a large initial heading error,severely limiting the guidance law's application scenarios.To tackle this problem and account for the maximum lateral acceleration constraint,an ITACG strategy is proposed from the perspectives of optimal guidance trajectory design and trajectory tracking in this paper.First,a guidance model is formulated,where Bézier curves are used to fit the guidance trajectory,and by parameterizing these curves and analyzing the trajectory constraints in detail,the optimal guidance trajectory design problem is transformed into an optimization problem of the control parameters.Then,a multi-layer zeroth-order Adam trajectory optimization algorithm is introduced to determine the control parameters without relying on gradient information.Subsequently,a hyperbolic tangent vector field trajectory tracking guidance algorithm is proposed to follow the pre-designed trajectory accurately.Finally,numerical simulations and equivalent physical experiments verify the effectiveness of the proposed guidance strategy. 展开更多
关键词 Bézier trajectory shaping Impact angle guidance Impact time control Parameter optimization Trajectory tracking
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Technical development and future prospects of cooperative terminal guidance based on knowledge graph analysis:a review 认领 引用 被引量：4
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作者 Shuangxi LIU Zehuai LIN +1 位作者 Wei HUANG Binbin YAN 《Journal of Zhejiang University-SCIENCE A》 SCIE EI CAS CSCD 2025年第7期605-634,共30页
Cooperative guidance is a method for achieving combat objectives through information sharing and cooperative effects,and has emerged as a significant research area in the fields of missile guidance and systematic warf... Cooperative guidance is a method for achieving combat objectives through information sharing and cooperative effects,and has emerged as a significant research area in the fields of missile guidance and systematic warfare.This study presents a systematic review and analysis of current research on cooperative guidance.First,a bibliometric analysis is conducted on 513 articles using the Scopus database and CiteSpace software to assess keyword clustering,keyword cooccurrence,and keyword burst,and to later visualize the results.Second,fundamental theories of cooperative guidance,including relative motion modeling methods,algebraic graph theory,and multi-agent consensus theory,are summarized.Subsequently,an overview of current cooperative laws and corresponding analysis methods is provided,with categorization based on the cooperative structure and convergence performance.Finally,we summarize current research developments based on five perspectives and propose a developmental framework based on five layers(cyber,physical,decision,information,and system),discussing potential future advancements in cooperative terminal guidance.This framework emphasizes five key areas of research:networked,heterogeneous,integrated,intelligent,and group cooperations,with the goal of offering trends and insights for futurework. 展开更多
关键词 Cooperative guidance Guidance law Multiple missiles Cooperative operations Guidance and control Impact time control Impact angle control Consensus theory CiteSpace analysis
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Capturability distinction analysis of continuous and pulsed guidance laws 认领 引用
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作者 Yuting LU Qinglei HU +2 位作者 Yang YU Tuo HAN Jianying ZHENG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2026年第1期472-484,共13页
The capture zones of the continuous and pulsed guidance laws in the pursuit-evasion game are analytically discussed in this paper to provide deep insights into the capturability distinction between the continuous guid... The capture zones of the continuous and pulsed guidance laws in the pursuit-evasion game are analytically discussed in this paper to provide deep insights into the capturability distinction between the continuous guidance law and the pulsed guidance law.Specifically,first,in the pursuit-evasion game,various capture cases are defined regarding the Zero-Effort Miss distance(ZEM)to facilitate the capturability analysis.Then,for both the evader and the pursuer,the Linear-Quadratic Differential Game(LQDG)guidance laws concerning the continuous acceleration and the pulsed acceleration are converted into a unified form.In each capture case,the optimal solution existence conditions are derived,and the corresponding capture zones are formulated.The discussion on the capture zones shows that if the optimal solution exists,the distinction between the pulsed guidance law and the continuous guidance law can be neglected under small guidance effort weight.However,the capture zone of the continuous guidance law is larger than that of the pulsed guidance law with large pursuer guidance effort weight,but smaller with large evader guidance effort weight.Finally,various simulations are conducted to illustrate the distinction of the continuous and pulsed guidance laws,as well as the impact of the acceleration ratio and the time constant ratio on the capturability. 展开更多
关键词 Differential game theory Linear-quadratic differential game Pulsed guidance law Capturability Capture zone
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Attitude control of multirotor with image-aided terminal guidance for precision target strike 认领 引用
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作者 Shengrong Hu Qiang Wang +2 位作者 Yixian Li Wuhong Zhao Fei Wang 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2026年第5期1-18,共18页
Precise long-range strikes using multirotors equipped with rigidly fixed Explosively Formed Penetrator(EFP)encounter multiple challenges,including platform disturbances,inherent EFP dispersion characteristics,and visu... Precise long-range strikes using multirotors equipped with rigidly fixed Explosively Formed Penetrator(EFP)encounter multiple challenges,including platform disturbances,inherent EFP dispersion characteristics,and visual-control coupling during large maneuvers.To address these issues,this paper proposes an attitude control method based on image-aided terminal guidance.Firstly,a multi-physics coupling model incorporating EFP dispersion is constructed to derive the control boundary conditions.Subsequently,a singularity-free target feature representation characterized by quaternions is established using spherical projection.On this basis,an attitude controller combining Non-singular Terminal Sliding Mode(NTSM)control and a Super-Twisting Observer(STO)is designed.NTSM aims to achieve fast,finite-time convergence of attitude errors.STO is used to estimate and compensate for lumped disturbances in real-time,including wind gusts,unmodeled dynamics,and parameter uncertainties,thereby enhancing system robustness.Finally,the effectiveness of the proposed method is evaluated by three kinds of experiments.The comparison with the traditional striking methods is conducted to prove the advantages of the proposed method in terms of strike performance.The dynamic target striking simulations are used to validate the feasibility and superiority of the proposed method under challenging conditions.The comparative simulations of different controllers are deployed to show the benefits of the proposed method in terms of convergence time,robustness and attitude control errors.The results demonstrate that the proposed method significantly improves the aiming accuracy and disturbance rejection capability for strikes,especially the engagement of dynamic targets. 展开更多
关键词 Multirotor Spherical projection Attitude control Image terminal guidance Non-singular terminal sliding mode(NTSM)
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Application of intraoperative laparoscopic ultrasound guidance combined with Sonazoid contrast in surgical treatment of colorectal liver metastasis 认领 引用
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作者 Wen-Tao He Hua Chen +4 位作者 Hong Li Yu-Lin Li Hao-Ran Wu Wen-Bin Duan Yang Liu 《World Journal of Gastroenterology》 SCIE CAS 2026年第23期48-55,共8页
BACKGROUND Contrast-enhanced ultrasound(CEUS)performed intraoperatively for colorectal cancer liver metastases can detect concealed liver metastases not identified during preoperative examinations or routine intraoper... BACKGROUND Contrast-enhanced ultrasound(CEUS)performed intraoperatively for colorectal cancer liver metastases can detect concealed liver metastases not identified during preoperative examinations or routine intraoperative ultrasound.This capability is critical for determining the appropriate surgical approach.AIM To explore the advantages of Sonazoid-CEUS(S-CEUS)over gray-scale ultrasound(GSUS)for tumor localization during laparoscopic ultrasound-guided microwave ablation(MWA)in colorectal liver metastases(CRLM)and to evaluate the real-time guidance role of S-CEUS in ablation therapy.METHODS We retrospectively reviewed data from 259 patients with CRLM who underwent MWA at the First People’s Hospital of Changde City between June 2020 and December 2023.Intraoperative target lesion localization was performed using GSUS or S-CEUS.Target lesion visibility was scored using a 5-point scale,and visibility differences between GSUS and S-CEUS were compared.The duration of the Kupffer phase for the target lesions was observed,and the effects of MWA performed during the Kupffer phase were evaluated.RESULTS Preoperative magnetic resonance imaging(MRI)identified 273 lesions in 259 patients,whereas intraoperative SCEUS detected 281 lesions,all confirmed as liver metastases via needle biopsy.The target lesion visibility scores were 2.87±1.09 during GSUS scanning and 4.07±0.74(arterial phase)and 4.31±0.58(Kupffer phase)during the SCEUS.The visibility scores in both the arterial and Kupffer phases of S-CEUS were superior to those in GSUS(both P1 hour.In patients with multiple pre-known lesions,all lesions were localized with a single contrast agent injection.Three occult lesions undetected via preoperative imaging were identified during the Kupffer phase.All lesions underwent MWA in the Kupffer phase.Immediate reassessment with repeat Sonazoid injection 15 minutes post-ablation and enhanced MRI at 1 month postoperatively demonstrated complete ablation of all lesions.CONCLUSION During MWA for CRLM,target lesion visibility in both the arterial and Kupffer phases of S-CEUS was superior to that of GSUS,facilitating improved target lesion localization.The Kupffer phase of S-CEUS provided valuable realtime guidance for MWA. 展开更多
关键词 Colorectal cancer Liver metastasis Ultrasound guidance Laparoscopy Sonazoid contrast imaging
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Optimization of saturated super-twisting sliding mode guidance law using reinforcement learning algorithm 认领 引用
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作者 Hao Wu Xiaojun Ban Di Zhou 《Defence Technology（防务技术）》 SCIE EI CAS CSCD 2026年第8期458-473,共16页
This paper proposes a novel missile guidance law optimization method based on deep reinforcement learning,specifically targeting terminal guidance for missiles engaging highly maneuverable targets in near-space enviro... This paper proposes a novel missile guidance law optimization method based on deep reinforcement learning,specifically targeting terminal guidance for missiles engaging highly maneuverable targets in near-space environments.In scenarios where both the missile and target have comparable overload capabilities,effective interception becomes a significant challenge.Existing methods,such as the Saturated Super-Twisting Algorithms,demonstrate strong performance in maneuvering target interception but face difficulties in parameter tuning and control input saturation.To overcome these limitations,this study introduces the Twin Delayed Deep Deterministic Policy Gradient(TD3)algorithm to optimize the parameters of missile guidance laws,offering an innovative solution to these complex challenges.The TD3 algorithm,known for its ability to handle noisy environments and mitigate Q-value overestimation,enhances the guidance system's capability to intercept highly maneuverable targets with greater precision.Simulation results validate the proposed approach,demonstrating a substantial performance improvement over traditional methods,thus providing both theoretical and practical contributions to missile guidance system optimization for next-generation missile defense applications. 展开更多
关键词 Highly maneuvering target Input saturation Missile guidance control Super-twisting algorithm Reinforcement learning
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Online reentry guidance algorithm based on trajectory analytical solutions 认领 引用
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作者 SUN Weibo MA Ping +2 位作者 LI Xiaonan WANG Songyan CHAO Tao 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2026年第3期1002-1018,共17页
To enhance the real-time performance and accuracy of guidance command generation,we propose an online reentry guidance algorithm based on analytical solutions of the hypersonic glide trajectory(HGT).Initially,an altit... To enhance the real-time performance and accuracy of guidance command generation,we propose an online reentry guidance algorithm based on analytical solutions of the hypersonic glide trajectory(HGT).Initially,an altitude-velocity profile is designed in the longitudinal plane to satisfy both path and terminal constraints.Based on this profile,we derive analytical solutions for the flight path angle(FPA)and bank angle.Subsequently,by employing the Newton-Raphson method to linearize the reentry motion equations,analytical solutions for the latitude and heading angle are obtained.Furthermore,we introduce an improved particle swarm optimization(IPSO)algorithm to optimize the profile parameters.This approach significantly enhances the algorithm's global convergence by narrowing the parameter optimization range and adaptively adjusting the inertia weight and cognitive factors.Finally,we present an online guidance algorithm that combines the HGT analytical solutions with the IPSO algorithm.This algorithm effectively achieves longitudinal and lateral guidance by continuously updating the altitude-velocity profile and bank angle symbol in real time.Simulation results demonstrate that the proposed algorithm is fast,efficient,accurate,and holds significant potential for broader application. 展开更多
关键词 altitude-velocity profile analytical solution improved particle swarm optimization(IPSO) online reentry guidance
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