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Asymmetric integral barrier Lyapunov function-based three-dimensional integrated guidance and control design with field-of-view constraint and input saturation

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ADVANCES IN MECHANICAL ENGINEERING 2024年第3期16卷

作者： Feng, Dan Hou, Mingshan Wang, Wencong Wang, Dongyue Northwestern Polytech Univ Sch Automat 1 Dongxiang Rd Xian 710072 Shaanxi Peoples R China

This paper proposes an adaptive integrated guidance control (IGC) scheme for the flight vehicle intercepting the maneuvering target with asymmetric field-of-view angle constraint, input magnitude and rate saturation, and system uncertainties. A novel nonlinear three-dimensional IGC model is established in the body line-of-sight (LOS) coordinate system by employing the dual-integral control law. Based on this model, the input magnitude and rate saturation for the conventional IGC system can be converted to the limitations of the new augmented states. Asymmetric integral barrier Lyapunov function and dynamic surface control approach are applied to deal with the asymmetric state constraints of the proposed IGC model, and adaptive control laws are designed to compensate for model uncertainties. Furthermore, based on the Lyapunov stability theory, it is proved that all signals in the closed-loop system are bounded while the constrained states are not violated. Finally, the effectiveness and robustness of the proposed IGC scheme are illustrated with numerical simulations.

关键词： field-of-view constraint three-dimensional IGC design model integral barrier Lyapunov function body-LOS coordinate system strap-down seeker

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Impact time control guidance law with field of view constraint

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AEROSPACE SCIENCE AND TECHNOLOGY 2014年 39卷 361-369页

作者： Zhang, Youan Wang, Xingliang Wu, Huali Naval Aeronaut & Astronaut Univ Dept Control Engn Yantai 264001 Peoples R China

The problem of Impact Time Control Guidance (ITCG) with field-of-view (FOV) constraint is investigated. The proposed ITCG law is a combination of the well-known Proportional Navigation Guidance (PNG) law and an additional biased term of impact time error, which is defined as the difference between the impact time by PNG and the prescribed one. A rule of the cosine of weighted leading angle in the biased term is used to guarantee that the FOV constraint is not violated during the engagement. Stability of the closed-loop guidance system is proved strictly. Numerical simulation results are presented to demonstrate the effectiveness of the proposed guidance law. (C) 2014 Elsevier Masson SAS. All rights reserved.

关键词： Anti-ship missile Impact time control field-of-view constraint Missile guidance

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Distributed cooperative guidance law without numerical singularity with field-of-view angle constraint

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AERONAUTICAL JOURNAL 2024年第1336期129卷 1515-1533页

作者： Liu, Z. Li, S. Ren, L. Ma, D. High Tech Inst Xian Xian Peoples R China Tsinghua Univ Dept Automat Beijing Peoples R China

A distributed cooperative guidance law without numerical singularities is proposed for the simultaneous attack a stationary target by multiple vehicles with field-of-view constraints. Firstly, the vehicle engagement motion model is transformed into a multi-agent model. Then, based on the state-constrained consensus protocol, a coordination control law with field-of-view (FOV) constraints is proposed. Finally, the cooperative guidance law has been improved to make it more suitable for practical application. Numerical simulations verified the effectiveness and robustness of the proposed guidance law in the presence of acceleration saturation, communication delays and measurement noise.

关键词： distributed cooperative guidance law field-of-view constraint numerical singularity

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Integrated cooperative guidance and control of strapdown missiles

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2025年第6期239卷 528-556页

作者： Huang, Xiaoyang Zhao, Bin Zhou, Jun Xie, Jingjie Zhao, Wanli Northwestern Polytech Univ Inst Precis Guidance & Control 127 West Youyi Rd Xian 710072 Peoples R China Univ Warwick Sch Engn Coventry England Sci & Technol Electroopt Informat Secur Control La Tianjin Peoples R China

This paper develops an innovative integrated cooperative guidance and control (ICGC) law for multiple strapdown missiles, and explicitly considers both the attitude dynamics and field-of-view (FOV) limitations of the seekers. First, a model is rigorously established using strict state feedback to incorporate attitude dynamics, which employs the body-line-of-sight (BLOS) angle to characterize the FOV constraints of strapdown seekers. We propose a nonlinear observer to precisely estimate aerodynamic disturbances, target maneuvers, and unmodeled dynamics. Using the BLOS angle as a critical variable for multi-missile cooperation, we derive a novel ICGC law based on the barrier lyapunov function and the dynamic surface control method. This law enables strategic cooperative geometries among multiple missiles attacking a single maneuvering target, with detailed proof of stability provided. Extensive numerical simulations demonstrate that the proposed ICGC law significantly enhances cooperative engagement capabilities, ensuring effective target attacks while adhering to the FOV constraints. This research substantially advances missile guidance and control systems, offering a robust framework for cooperatively engaging maneuvering targets.

关键词： Integrated cooperative guidance and control law strapdown missiles field-of-view constraint body-line-of-sight

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field-of-view limited guidance with impact angle constraint and feasibility analysis

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AEROSPACE SCIENCE AND TECHNOLOGY 2021年 114卷 106753-106753页

作者： Hu, Qinglei Cao, Ruihao Han, Tuo Xin, Ming Beihang Univ Sch Automat Sci & Elect Engn Beijing 100191 Peoples R China Aviat Ind Corp China Xian Flight Automat Control Res Inst Xian 710065 Peoples R China Univ Missouri Dept Mech & Aerosp Engn Columbia MO 65211 USA

A look angle shaping guidance law with impact angle and seeker's field-of-view (FOV) constraints considering the time-varying speed is proposed. A look angle profile with respect to the relative range is first constructed as a cubic polynomial. The desired impact angle and the maximum look angle are expressed as functions of a parameter in the look angle profile. The impact angle constraint under limited FOV is achieved by solving this parameter with boundary conditions. Moreover, the feasible region of the desired impact angle is derived to ensure seeker's lock-on condition. By combining the first order look angle dynamics and the reference look angle profile, the impact angle control guidance (IACG) law with FOV constraint is obtained. The proposed guidance law is derived without relying on the linearized engagement kinematics, switching logic, constant speed assumption, and the LOS rate information during the guidance process. Moreover, the proposed guidance technique is helpful for user/designers to select feasible impact angle constraints in advance without tuning parameters. Finally, numerical simulations under a realistic model are performed to validate the effectiveness of the proposed guidance law. (C) 2021 Elsevier Masson SAS. All rights reserved.

关键词： Missile guidance Impact angle control field-of-view constraint Time-varying speed

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Integrated Guidance and Control Scheme for Unmanned Aerial Vehicle with Unknown Control Coefficient Accommodating Approach Angle and field-of-view constraints

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JOURNAL OF AEROSPACE ENGINEERING 2024年第3期37卷 04024008-04024008页

作者： Ding, Yixin Guo, Zongyi Cao, Shiyuan Guo, Jianguo Oliveira, Tiago Roux Northwestern Polytech Univ Inst Precis Guidance & Control Xian 710072 Peoples R China State Univ Rio De Janeiro UERJ Dept Elect & Telecommun Engn DETEL BR-20550900 Rio De Janeiro RJ Brazil

This paper investigates the issue of integrated guidance and control (IGC) design for an unmanned aerial vehicle with an unknown control coefficient, approach angle constraint, and field-of-view limitations. Different from the existing methods, the proposed approach integrates the approach angle and field-of-view requirements into a single reference to satisfy the constraints simultaneously, and meanwhile guarantees the successful mission despite the unknown control coefficient. Based on the established IGC model, a novel sliding mode strategy is generated to ensure that the approach angle and field-of-view constraints can be obeyed once the designed reference is tracked precisely. Then, the IGC issue are transformed into a tracking problem under an unknown control direction, and the periodic sliding mode control technique is introduced to construct the IGC law. The stability of the closed-loop system is analyzed in detail. The effectiveness of the proposed method is verified by numerical simulations.

关键词： Integrated guidance and control (IGC) Unknown control coefficient Unmanned aerial vehicle Approach angle field-of-view constraint

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Integrated cooperative guidance framework and cooperative guidance law for multi-missile

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Chinese Journal of Aeronautics 2018年第3期31卷 546-555页

作者： Jianbo ZHAO Shuxing YANG School of Aerospace Engineering Beijing Institute of Technology Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of Education

An integrated cooperative guidance framework for multi-missile cooperatively attacking a single stationary target is proposed in this paper by combining both the centralized and decentralized communication topologies. Once missiles are distributed into several groups, missiles within a single group communicate with the centralized leader-follower framework, while the leaders from different groups communicate using the nearest-neighbor topology. To implement the integrated cooperative guidance framework, a group of Finite-Time Cooperative Guidance（FTCG） laws considering the saturation constraint on FOV（FTCG-FOV） are firstly derived within the centralized leader-follower framework to satisfy the communication topology of missiles in a single ***, an improved sequential approach is developed to adapt the FTCG-FOV to satisfy the communication topology between groups. The numerical simulations demonstrate the effectiveness and high efficiency of the integrated cooperative guidance framework and the cooperative guidance laws, as well as the superiority of the developed sequential approach.

关键词： Cooperative field-of-view constraint Finite-time Framework Missile guidance Multi-missiles

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Two-phase guidance law for impact time control under physical constraints

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Chinese Journal of Aeronautics 2020年第11期33卷 2946-2958页

作者： Yang TANG Xiaoping ZHU Zhou ZHOU Fei YAN National Key Laboratory of Science and Technology on UAV Northwestern Polytechnical UniversityXi’an 710065China UAV Research Institute Northwestern Polytechnical UniversityXi'an 710065China School of Aeronautics Northwestern Polytechnical UniversityXi'an 710072China

An impact-time-control guidance law is required for the simultaneous attack of suicide attack unmanned aerial *** on the nonlinear model,a two-phase guidance strategy is *** impact time is derived in a simple analytical form of initial states and switching states,and it can be controlled by switching at an appropriate ***,a two-phase guidance law is designed to make the magnitude of the heading error decrease monotonically from its initial value to *** then,the feasible interval of the switching ranges and of the impact times under the acceleration constraint are given analytically in ***,a general form of twophase guidance law is proposed,which allows the magnitude of the heading error to increase in the first phase,to improve the applicability of the *** the same structure as proportional navigation guidance with a time-varying gain,the proposed algorithms are simple and easy to *** corresponding feedback form is presented for realistic *** a predefined impact time is taken within its permissible set,the constraints on the acceleration and fieldof-view will not be violated during the ***,simulations validate the effectiveness of the methodology in impact time control and salvo attack.

关键词： Acceleration constraint field-of-view constraint Guidance Impact time control Switching

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A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles

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Chinese Journal of Aeronautics 2015年第5期28卷 1438-1450页

作者： Zhang Youan Wang Xingliang Wu Huali Department of Control Engineering Naval Aeronautical and Astronautical University

The consensus problem of impact time is addressed for multiple anti-ship missiles. A new distributed cooperative guidance law with the form of biased proportional navigation guidance （BPNG） is presented. The proposed guidance law employs the available measurements of relative impact time error as the feedback information to achieve the consensus of impact time among mis- siles and, by exploiting the special structure of the biased cooperative control term, it can handle the seeker＇s field-of-view （FOV） constraint. The proposed scheme ensures convergence to consensus of impact time under either fixed or switching sensing/communication network, and the topological requirements are less restrictive than those in the existing results. Numerical examples are provided to illustrate the effectiveness of the proposed guidance law.

关键词： Cooperative Distributed field-of-view constraint Missile guidance Missile trajectory control

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field-of-view and Impact Angle Constrained Guidance Law for Missiles With Time-Varying Velocities

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IEEE ACCESS 2019年 7卷 61717-61727页

作者： Liu, Bojun Hou, Mingshan Li, Yajun Northwestern Polytech Univ Sch Automat Xian 710072 Shaanxi Peoples R China

A novel nonlinear non-switching guidance strategy is proposed for missiles with time-varying velocities intercepting stationary targets, considering impact angle, seeker's field-of-view, and input saturation constraints, simultaneously. A new nonlinear control oriented mathematical model is established, and the guidance design problem is converted to be the issue of tracking control of a nonlinear system with the partial state constraint. In the first step, a bounded virtual guidance law is designed based on hyperbolic tangent function. In the second step, the effect of the input saturation is compensated with a first-order filter. Integral barrier Lyapunov function based stability analysis shows that the tracking errors of the whole guidance system converge to zero uniformly, and the prescribed guidance constraints are not violated. Finally, the numerical simulations are performed to demonstrate the effectiveness of the proposed guidance law.

关键词： Guidance law impact angle control field-of-view constraint input saturation hyperbolic tangent function integral barrier Lyapunov function

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