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Impact time control guidance with field-of-view constraint accounting for uncertain system lag

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2016年第3期230卷 515-529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 with seeker's field-of-view constraint in the presence of uncertain system lag is addressed. A novel two-step control approach based impact time control guidance law with seeker's field-of-view constraint is proposed. Specifically, in the first step, a state constrained robust adaptive control law, using the dynamic surface control method combining with the control integral barrier Lyapunov function technique, is synthesized to achieve the required robust tracking performance with respect to the desired trajectory of lead angle in the presence of uncertain system lag and other uncertainties. In the second step, the desired trajectory of lead angle is generated online to guarantee target interception at the designated impact time under the assumption of ideal autopilot dynamics while not violating the seeker' field-of-view constraint. The proposed guidance law ensures the seeker's field-of-view constraint does not be violated in the presence of uncertain system lag and other uncertainties. Numerical simulations are provided to illustrate the effectiveness of the proposed guidance law.

关键词： Guidance impact time control field-of-view constraint uncertain system lag integral barrier Lyapunov function dynamic surface control

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Sliding mode control based impact angle control guidance considering the seeker's field-of-view constraint

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ISA TRANSACTIONS 2016年 61卷 49-59页

作者： Wang, Xingliang Zhang, Youan Wu, Huali Naval Aeronaut & Astronaut Univ Dept Control Engn ErMa Rd 188 Zhifu Dist 264001 Yantai Peoples R China

The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations. (C) 2016 ISA. Published by Elsevier Ltd. All rights reserved.

关键词： Guidance Sliding mode control Impact angle control field-of-view constraint Integral barrier Lyapunov function Nonlinear extended state observer

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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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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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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 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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Koopman Operator-Based Integrated Guidance and Control for Strap-Down High-Speed Missiles

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IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY 2024年第6期32卷 2436-2443页

作者： Zhou, Min Lu, Mingfei Hu, Guanjie Guo, Zongyi Guo, Jianguo Northwestern Polytech Univ Inst Precis Guidance & Control Xian 710072 Peoples R China XianJiaotong Univ Inst Artificial Intelligence & Robot Xian 710049 Peoples R China

This work focuses on addressing the challenges of integrated guidance and control (IGC) for strap-down high-speed missiles with nonlinearities and field-of-view constraints. To achieve this, a data-driven prediction model using the Koopman operator is developed, which exhibits high accuracy in capturing the significant nonlinearities of the investigated high-speed missiles. Furthermore, the field-of-view restrictions imposed by the strap-down seeker are addressed by introducing a Lyapunov-based model predictive control (LMPC) scheme based on the linear Koopman prediction model. To enhance the robustness of the system, a disturbance observer is integrated into the Koopman-operator-based LMPC (KLMPC), enabling the estimation and compensation of disturbances. A KLMPC-based IGC (KLMPC-IGC) design framework is then developed to solve the constrained IGC problem, ensuring the stability and robustness of the closed-loop system. Numerical simulation results validate the higher prediction accuracy of the proposed linear prediction model compared with traditional local linearization prediction, as well as demonstrate the effectiveness of the presented approach.

关键词： Missiles Aerodynamics Mathematical models Vectors Predictive models Robustness Predictive control field-of-view constraint high-speed missiles integrated guidance and control (IGC) Koopman operator Lyapunov-based model predictive control (LMPC)

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Polynomial shaping based three-dimensional impact angle and field-of-view constrained guidance

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AEROSPACE SCIENCE AND TECHNOLOGY 2024年 147卷

作者： Surve, Prajakta Maity, Arnab Kumar, Shashi Ranjan Indian Inst Technol Dept Aerosp Engn Mumbai 400076 India

This paper proposes a polynomial-based three-dimensional (3D) impact angle-constrained guidance law considering the seeker's field-of-view (FOV) bound. The guidance laws are derived using nonlinear coupled dynamics of the interceptor-target engagement against stationary as well as constant velocity targets. Line-ofsight (LOS) orientations between the interceptor and the target in both pitch and yaw planes are shaped as two cubic polynomial functions of relative range. An explicit expression for the look angle of the interceptor is acquired in terms of the LOS polynomials. This expression facilitates the embodiment of the FOV constraint in the boundary conditions inflicted on the polynomials. A system of equations with the eight unknown coefficients is obtained by employing the appropriate launch and terminal conditions of the interceptor-target engagement. Reference LOS angle and lead angle profiles are generated using the calculated coefficients, complying to which the interceptor achieves a zero miss distance with desired impact angle and FOV constraints. A tracking controller is then designed using a nonlinear control technique that enables the interceptor to follow reference lead angle profiles in mutually orthogonal planes. Unlike the already existing guidance strategies for 3D impact angle and FOV-constrained target interception, the proposed nonlinear guidance strategy is designed without the use of linearization or decoupling. Moreover, no switching logic or multi-phase guidance structures are employed in the proposed guidance strategy, which eliminates possible jumps in the guidance command. The effectiveness of the proposed guidance law is validated using numerical simulations, along with a comparison study with the existing strategy.

关键词： Impact angle control field-of-view constraint Polynomial shaping-based guidance Three-dimensional guidance

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Three-dimensional nonsingular impact angle guidance strategy with physical constraints

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ISA TRANSACTIONS 2022年 131卷 476-488页

作者： Yang, Xiao-yan Zhang, Yu-chen Song, Shen-min Harbin Inst Technol Sch Astronaut Harbin 150001 Heilongjiang Peoples R China

In this study, two nonsingular three-dimensional (3D) guidance strategies to intercept a stationary target with desired impact angles, subject to nonlinear coupled dynamics, field-of-view (FOV) limit and lateral acceleration bounds, are investigated. As a stepping stone, two novel sliding mode surfaces are designed, the convergence and boundedness of the two sliding mode surfaces can guarantee the impact-angle-constrained interception while maintaining the seeker's lock-on condition during the guidance. A novel auxiliary system is also presented to compensate for the effects caused by input saturation. In addition, the analytical achievable impact angles set is presented in terms of the initial engagement condition. Numerical simulations with various constraints, a realistic missile model and comparison study have been considered to show the feasibility and effectiveness of the proposed strategies.(c) 2022 ISA. Published by Elsevier Ltd. All rights reserved.

关键词： Impact angle guidance field-of-view constraint Input saturation Sliding mode surface Capture region

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Barrier Lyapunov Function Based Integrated Missile Guidance and Control Considering Phased Array Seeker Disturbance Rejection Rate

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IEEE ACCESS 2022年 10卷 31070-31083页

作者： Lin, Shih-Yao Wang, Jiang Wang, Wei Beijing Inst Technol Sch Aerosp Engn Beijing 100081 Peoples R China

A two-dimensional missile-target engagement geometry is established considering the effect of the disturbance rejection rate (DRR) problem caused by phased array radar beam pointing error and radome refraction error in the guidance and control system. Compared with the traditional two-dimensional missile-target engagement geometry, the established model clearly shows the effect of the disturbance rejection rate problem on the missile line of sight and field-of-view constraint. The integrated missile guidance and control scheme is developed by adding the integral barrier Lyapunov function to dynamic surface control to satisfy the seeker field-of-view constraint while ensuring that the system has strong robustness. The target maneuvering and unmodeled disturbance with the effect of the DRR error slope as uncertain disturbances of the system and use the reduced-order extended state observer for online estimation. Moreover, the actuator deflection angle and angular rate constraints are guaranteed via the command filter. Stability analysis and numerical simulations show that the estimation and compensation of the seeker DRR error allow the proposed scheme to intercept a high-speed target accurately.

关键词： Radomes Radar tracking Control systems Target tracking Phased arrays Radar Missile guidance Integrated guidance and control field-of-view constraint disturbance rejection rate barrier Lyapunov function

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