检索结果-内蒙古大学图书馆

impact time control guidance Using Output Trajectory Shaping Method

JOURNAL OF guidance control AND DYNAMICS 2025年第4期48卷 961-967页

作者： Lee, Suwon Kim, Mingu Tekin, Raziye Kookmin Univ Dept Future Mobil 77 Jeongneung Ro Seoul 02707 South Korea Hansung Univ Div Mech & Elect Engn Seoul 02876 South Korea Roketsan Missiles Inc Tactical Missile Syst TR-06780 Ankara Turkiye

来源：评论

学校读者我要写书评

暂无评论

impact time control guidance law with time-varying velocity based on deep reinforcement learning

引用

AEROSPACE SCIENCE AND TECHNOLOGY 2023年第PartA期142卷

作者： Yang, Zhuoqiao Liu, Xiangdong Liu, Haikuo Beijing Inst Technol Sch Automat Beijing 100081 Peoples R China Beijing Inst Technol Sch Mechatron Engn Beijing 100081 Peoples R China

This paper investigates the problem of impact-time-control guidance law with the time-varying velocity caused by gravity and aerodynamic drag. Using the deep reinforcement learning (DRL) algorithm, we propose a novel impact time control guidance (ITCG) law in which a DRL agent is trained from scratch without using any prior knowledge. Different from the traditional ITCG law, the proposed method doesn't rely on the time-to-go estimation, which is difficult to derive and inaccurate with the time-varying velocity. Further, a prioritized experience replay method and a novel action exploration method are introduced in the DRL algorithm to improve learning efficiency. Additionally, the agent action is shaped to provide smooth guidance command, which avoids the problem that the guidance command generated by the intelligent algorithm may not be continuous. Numerical simulations are conducted to support the validity of the proposed algorithm.(c) 2023 Elsevier Masson SAS. All rights reserved.

关键词： time-varying velocity Deep reinforcement learning impact time control guidance Missile guidance

来源：评论

学校读者我要写书评

暂无评论

Field-of-view constrained impact time control guidance considering time-varying velocity 29

Field-of-view constrained impact time control guidance consi...

引用

29th International Conference on Automation and Computing (ICAC)

作者： Wang, Peng Chen, Wanchun Chen, Zhongyuan Hu, Jinchuan Beihang Univ Sch Astronaut Beijing Peoples R China Beijing Electromech Engn Inst Beijing Peoples R China

ISBN: (纸本)9798350360882;9798350360899

A field-of-view constrained impact time control guidance law, considering time-varying velocity, is proposed based on a neural network and a special switch function. First, a dataset containing the time-to-go and initial states of missile is obtained by simulating possible engagement scenarios, utilizing a biased proportional navigation guidance law as the nominal guidance strategy. To achieve an accurate estimation of time-to-go essential for impact time control, the neural network is employed to fit the highly nonlinear relationship between the time-to-go and initial states. Subsequently, the field-of-view constraint is achieved by employing a special switch function. When the leading angle approaches its maximum value, the proposed guidance law will return to the nominal guidance law, ensuring that the field-of-view constraint is satisfied throughout the engagement. Simulation results demonstrate that the proposed guidance law can achieve impact time control with field-of-view constraint under time-varying velocity.

关键词： impact time control guidance field-of-view constrained time-varying velocity neural network

来源：评论

学校读者我要写书评

暂无评论

Fixed-time impact time control guidance Law for Missiles With Input Saturation Constraints Against Maneuvering Targets 38

Fixed-Time Impact Time Control Guidance Law for Missiles Wit...

引用

38th Youth Academic Annual Conference of Chinese Association of Automation, YAC 2023

作者： Ding, Xiangjun Wang, Jianan Song, Weihao Shan, Jiayuan Beijing Institute of Technology School of Aerospace Engineering Beijing China Peking University College of Engineering Beijing China

ISBN: (纸本)9798350303636

This paper is concerned with the fixed-time impact time control guidance (ITCG) problem against maneuvering targets. Firstly, the fixed-time observers are adopted to estimate the maneuvering target's unknown acceleration. Then, a fixed-time ITCG law is derived by resorting to the time-to-go of deviated pursuit guidance, where the unknown target acceleration is compensated based on the estimates obtained from the fixed-time observers. Moreover, an auxiliary system is adopted to tackle the frequently encountered input saturation constraints, and the fixed-time stability of the proposed ITCG law is analyzed. Finally, simulation results are provided to demonstrate the designed ITCG law. © 2023 IEEE.

关键词： fixed-time control impact time control guidance input saturation maneuvering targets

来源：评论

学校读者我要写书评

暂无评论

Three-Dimensional Spatial-Temporal Cooperative guidance Without Active Speed control

引用

JOURNAL OF guidance control AND DYNAMICS 2023年第10期46卷 1981-1996页

作者： Dong, Wei Deng, Fang Wang, Chunyan Wang, Jianan Xin, Ming Beijing Inst Technol Natl Key Lab Autonomous Intelligent Unmanned Syst Beijing 100081 Peoples R China Beijing Inst Technol Sch Aerosp Engn Beijing 100081 Peoples R China Univ Missouri Dept Mech & Aerosp Engn Columbia MO 65211 USA Beijing Inst Technol Chongqing Innovat Ctr Chongqing 401120 Peoples R China

This paper investigates the three-dimensional (3D) spatial-temporal cooperative guidance problem for multiple missiles with time-varying speeds, which is addressed by a progressive design strategy. First, the zero miss distance and desired impact directions are realized by a 3D vector impact angle control guidance (IACG) law whose time-to-go is predicted accurately and efficiently by a numerical algorithm. Then, by introducing an implicit trajectory-to-go function, the time-to-go control mechanism is clearly revealed under missile speed variation. Accordingly, a coordinated biased term is added to the 3D vector IACG law to ensure a simultaneous attack. Finally, considering the seeker's field-of-view (FOV) limit, the resultant cooperative guidance law is further augmented by another biased term to prevent the lead angle from exceeding its upper bound. Unlike similar existing results, the proposed one can satisfy multiple complex spatial-temporal constraints without active speed control, thereby manifesting great practical significance. Several numerical simulations are provided to show the effectiveness and advantages of the proposed cooperative guidance law.

关键词： Sliding Mode control Zero Lift Drag Coefficient guidance System Cooperative guidance Tactical and Strategic Missile guidance Missile guidance Homing guidance impact time control guidance guidance Navigation and control Intercept Angle guidance Law

来源：评论

学校读者我要写书评

暂无评论

Generalized time-to-Go Inversion guidance with impact time and Angle Constraints

引用

JOURNAL OF guidance control AND DYNAMICS 2025年第3期48卷 555-574页

作者： Wang, Pengyu Lee, Chang-Hun Cho, Namhoon Wie, Bong Korea Adv Inst Sci & Technol Dept Aerosp Engn Daejeon 34141 South Korea Cranfield Univ Sch Aerosp Transport & Mfg Control & Optimisat Cranfield MK43 0AL England Iowa State Univ Dept Aerosp Engn Ames IA 50010 USA

A major challenge in homing guidance is that accurately predicting the time to go for missiles is generally difficult, which limits the practical application of a certain class of guidance laws with impact-time constraints or cooperative capabilities. To address this issue, a generalized method referred to as the time-to-go inversion guidance is presented, where the time to go is first specified as an explicit function and then the corresponding guidance law is inversely derived. By employing this new method, a variety of guidance laws and their globally accurate time-to-go solutions can be developed, regardless of whether the impact-angle constraint is considered or not. Different from all existing studies, the proposed method addresses the problem of time-to-go estimation without relying on any linearizing approximations or numerical iterations. To enhance the practicality of the proposed method, it is augmented with bias commands to result in either the impact time control guidance law or the impact time and angle control guidance law. Numerical simulation results demonstrate the higher accuracy, larger feasible solution region, and lower computational demand of the proposed guidance laws even for the missiles with nonconstant speeds.

关键词： guidance, Navigation, and control Systems Homing guidance Flight Path Angle Runge Kutta Methods Missile guidance and control Sliding Mode control impact time control guidance

来源：评论

学校读者我要写书评

暂无评论

Three-dimensional cooperative guidance strategy for heterogeneous vehicles without prior communication topology establishment

引用

AEROSPACE SCIENCE AND TECHNOLOGY 2025年 161卷

作者： Xiong, Yongcheng Li, Jianfeng Li, Changqing Hu c Tan, Liguo Harbin Inst Technol Dept Control Sci & Engn Harbin 150001 Peoples R China Harbin Inst Technol Ctr Control Theory & Guidance Technol Harbin 150001 Peoples R China Kazan Natl Res Tech Univ Inst Aviat Land Transportat & Power Engn Kazan 420111 Russia Harbin Inst Technol Frontiers Sci Ctr Matter Behave Space Environm Harbin 150001 Peoples R China

This study proposes a novel heterogeneous vehicle cooperative guidance law, named HKGG. This guidance law integrates the proportional navigation law (PNG) and the Hegselmann-Krause (HK) model, enabling multiple vehicles to self-organize and reach the target point in groups based on their own states. Firstly, a three-dimensional overload model for multiple flying-vehicles is established. Then, by deriving the combination form of the PNG term and the consensus algorithm through the vehicle-target model on a two-dimensional plane, normal and lateral guidance commands are derived based on the HK model and the estimation of the remaining flight time of the multi-vehicles. The proposed strategy does not require prior establishment of a communication topology, and the communication relationships between vehicles are time-varying. By employing the proposed strategy, the multi-vehicle system can significantly enhance its capability to strike high-defense/multi-interception facilities. Various simulation scenarios were considered to verify the effectiveness of the proposed control strategy.

关键词： Hegselmann-Krause model impact time control guidance Proportional navigation guidance Consensus algorithm

来源：评论

学校读者我要写书评

暂无评论

time-Constrained Interception with Bounded Field of View and Input Using Barrier Lyapunov Approach

引用

JOURNAL OF guidance control AND DYNAMICS 2024年第2期47卷 384-393页

作者： Singh, Swati Kumar, Shashi Ranjan Mukherjee, Dwaipayan Indian Inst Technol Intelligent Syst & Control Lab Dept Aerosp Engn Mumbai 400076 India Indian Inst Technol Dept Elect Engn Mumbai 400076 India

来源：评论

学校读者我要写书评

暂无评论

Three-agent time-constrained Cooperative Pursuit-Evasion

引用

JOURNAL OF INTELLIGENT & ROBOTIC SYSTEMS 2022年第2期104卷 1-27页

作者： Sinha, Abhinav Kumar, Shashi Ranjan Mukherjee, Dwaipayan Indian Inst Technol Dept Aerosp Engn Intelligent Syst & Control Lab Mumbai 400076 Maharashtra India Indian Inst Technol Dept Elect Engn Mumbai 400076 Maharashtra India

This paper considers a pursuit-evasion scenario among three agents- an evader, a pursuer, and a defender. We design cooperative guidance laws for the evader and the defender team to safeguard the evader from an attacking pursuer. Unlike differential games, optimal control formulations, and other heuristic methods, we propose a novel perspective on designing effective nonlinear feedback control laws for the evader-defender team using a time-constrained guidance approach. The evader lures the pursuer on the collision course by offering itself as bait. At the same time, the defender protects the evader from the pursuer by exercising control over the engagement duration. Depending on the nature of the mission, the defender may choose to take an aggressive or defensive stance. Such consideration widens the applicability of the proposed methods in various three-agent motion planning scenarios such as aircraft defense, asset guarding, search and rescue, surveillance, and secure transportation. We use a fixed-time sliding mode control strategy to design the control laws for the evader-defender team and a nonlinear finite-time disturbance observer to estimate the pursuer's maneuver. Finally, we present simulations to demonstrate favorable performance under various engagement geometries, thus vindicating the efficacy of the proposed designs.

关键词： Pursuit-evasion Unmanned vehicles impact time control guidance time-constrained cooperative control Multiagent systems

来源：评论

学校读者我要写书评

暂无评论

Proportional Navigation Based impact-time-control guidance for Maneuvering Aerial Targets

Proportional Navigation Based Impact-Time-Control Guidance f...

引用

2014 International Conference on Artificial,Intelligence and Software Engineering(AISE 2014)

作者： Xue-yi FANG De-yun ZHOU Kun ZHANG Jiao-na WAN School of Electronic and Information Northwestern Polytechnical University Research Institute of Highway Ministry of Transportation

A simple algorithm of impact-time-control guidance(ITCG) based on classical proportional navigation guidance(PNG) law is proposed for many-to-one aerial combat. The proportional ratio of PNG is taken as the control variable to make multiple missiles agree upon and endeavor to reach a consensus impact time against an aerial target. A weighted optimization problem where the missile with large weight dictates the desired impact time of the others is constructed. The normal acceleration command is the function of the consensus time, the solution of the optimization problem. Analytical form of the normal acceleration command can be acquired which ensures the real-time performance of the proposed algorithm. Furthermore, the algorithm can be implemented in a distributed manner. Numerical simulation validates the proposed method and shows that the PNG based ITCG algorithm outperforms the standard PNG scheme in the case study of this paper.

关键词： Proportional navigation impact time control guidance Maneuvering target

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：