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An adaptive fast fixed-time guidance law with an impact angle constraint for intercepting maneuvering targets

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Chinese Journal of Aeronautics 2018年第6期31卷 1327-1344页

作者： Yao ZHANG Shengjing TANG Jie GUO Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of Education School of Aerospace Engineering Beijing Institute of Technology

Sliding mode guidance laws based on a conventional terminal sliding mode guarantees only finite-time convergence, which verifies that the settling time is required to be estimated by selecting appropriate initial launched conditions. However, rapid convergence to a desired impact angle within a uniform bounded finite time is important in most practical guidance applications. A uniformly finite-time/fixed-time convergent guidance law means that the convergence（settling） time is predefined independently on initial conditions, that is, a closed-loop convergence time can be estimated a priori by guidance parameters. In this paper, a novel adaptive fast fixed-time sliding mode guidance law to intercept maneuver targets at a desired impact angle from any initial heading angle,with no problems of singularity and chattering, is designed. The proposed guidance law achieves system stabilization within bounded settling time independent on initial conditions and achieves more rapid convergence than those of fixed-time stable control methods by accelerating the convergence rate when the system is close to the origin. The achieved acceleration-magnitude constraints are rigorously enforced, and the chattering-free property is guaranteed by adaptive switching *** numerical simulations are presented to validate the efficiency and superiority of the proposed guidance law for different initial engagement geometries and impact angles.

关键词： Adaptive gain tuning Fixed-time convergence impact angle constraint Missile guidance Nonsingular terminal sliding mode control

Three-dimensional cooperative guidance law for multiple missiles with impact angle constraint

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Journal of Systems Engineering and Electronics 2020年第6期31卷 1286-1296页

作者： YANG Biao JING Wuxing GAO Changsheng School of Astronautics Harbin Institute of TechnologyHarbin 150001China

This paper proposes a cooperative guidance law for attacking a ground target with the impact angle constraint based on the motion camouflage strategy in the line-of-sight(LOS)frame.A dynamic model with the impact angle constraint is established according to the relative motion between multiple missiles and the *** process of cooperative guidance law design is divided into two ***,based on the undirected graph theory,a new finite-time consensus protocol on the LOS direction is derived to guarantee relative distances reach *** the value of acceleration command is positive,which is beneficial for engineering ***,the acceleration command on the normal direction of the LOS is designed based on motion camouflage and finite-time convergence,which can ensure the missiles reach the target with the desired angle and satisfy the motion camouflage *** finitetime stability analysis is proved by the Lyapunov *** simulations for stationary and maneuver targets have demonstrated the effectiveness of the cooperative guidance law proposed.

关键词： cooperative guidance law motion camouflage impact angle constraint finite-time

Fast Convergent Nonsingular Terminal Sliding Mode Guidance Law with impact angle constraint

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Fast Convergent Nonsingular Terminal Sliding Mode Guidance L...

Design of integral sliding mode guidance law based on disturbance observer

第37届中国控制会议

作者： Kuanqiao Zhang Suochang Yang Department of Missile Engineering Army Engineering University

In this paper, a nonsingular, essentially continuous and finite time fast convergent guidance law with impact angle constraint for some missiles attacking the targets with zero miss-distance and terminal impact angle constraint is presented by using terminal sliding mode control and finite time control theories. First, in order to avoid the singularity of terminal sliding mode control, and make the state variables achieve the equilibrium point in finite time, a fast convergent nonsingular terminal sliding mode control algorithm is improved. In the algorithm, the fast convergent nonsingular sliding mode function is employed to construct the sliding surface, and an adaptive exponential reaching law is employed to the reaching, so the system trajectory converges quickly from any initial state to the equilibrium point in the entire reaching phase. Then, a fast convergent nonsingular terminal sliding mode guidance law with impact angle constraint is presented base on this algorithm. Finite time control theory is used to analyze the convergence of the guidance law. Due to its inherent nonsingularity attribute, continuity and faster convergent rate, higher tracking precision of the desired impact angle in a shorter time interval with smoother guidance command can be guaranteed compared with conventional terminal sliding mode guidance law. A number of numerical simulation examples are implemented to justify the effectiveness of the proposed guidance law.

关键词： guidance law impact angle constraint nonsingular terminal sliding mode control exponential reaching law finite time convergence

来源： cnki会议评论

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Journal of Systems Engineering and Electronics 2024年第1期35卷 186-194页

作者： ZHOU Jianping ZHANG Wenjie ZHOU Hang LI Qiang XIA Qunli School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China School of Informatic Engineering Mianyang Techers’CollegeMianyang 62100China Beijing Institute of Electronic System Engineering Beijing 100854China Beijing Institute of Space Long March Vehicle Beijing 100076China

With the increasing precision of guidance,the impact of autopilot dynamic characteristics and target maneuvering abilities on precision guidance is becoming more and more *** order to reduce or even eliminate the autopilot dynamic operation and the target maneuvering influence,this paper suggests a guidance system model involving a novel integral sliding mode guidance law(ISMGL).The method utilizes the dynamic characteristics and the impact angle,combined with a sliding mode surface scheme that includes the desired line-ofsight angle,line-of-sight angular rate,and second-order differential of the angular *** the same time,the evaluation scenario considere the target maneuvering in the system as the external disturbance,and the non-homogeneous disturbance observer estimate the target maneuvering as a compensation of the guidance *** proposed system’s stability is proven based on the Lyapunov stability *** simulations reveale that ISMGL effectively intercepted large maneuvering targets and present a smaller miss-distance compared with traditional linear sliding mode guidance laws and trajectory shaping guidance ***,ISMGL has a more accurate impact angle and fast convergence speed.

关键词： disturbance observer pilot dynamics integral sliding mode impact angle constraint maneuvering target

A trajectory shaping guidance law with field-of-view angle constraint and terminal limits

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Journal of Systems Engineering and Electronics 2022年第2期33卷 426-437页

作者： FU Shengnan ZHOU Guanqun XIA Qunli School of Mechatronical Engineering Beijing Institute of TechnologyBeijing 100081China Beijing Aerospace Technology Institute Beijing 100074China School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China

In this paper, a trajectory shaping guidance law,which considers constraints of field-of-view(FOV) angle, impact angle, and terminal lateral acceleration, is proposed for a constant speed missile against a stationary target. First, to decouple constraints of the FOV angle and the terminal lateral acceleration, the third-order polynomial with respect to the line-ofsight(LOS) angle is introduced. Based on an analysis of the relationship between the looking angle and the guidance coefficient,the boundary of the coefficient that satisfies the FOV constraint is obtained. The terminal guidance law coefficient is used to guarantee the convergence of the terminal conditions. Furthermore, the proposed law can be implemented under bearingsonly information, as the guidance command does not involve the relative range and the LOS angle rate. Finally, numerical simulations are performed based on a kinematic vehicle model to verify the effectiveness of the guidance law. Overall, the work offers an easily implementable guidance law with closed-form guidance gains, which is suitable for engineering applications.

关键词： shaping guidance law field-of-view(FOV)constraint impact angle constraint terminal lateral acceleration constraint

impact angle constrained fuzzy adaptive fault tolerant IGC method for Ski-to-Turn missiles with unsteady aerodynamics and multiple disturbances

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Journal of Systems Engineering and Electronics 2022年第5期33卷 1210-1226页

作者： GUO Hang WANG Zheng FU Bin CHEN Kang FU Wenxing YAN Jie Research Center for Unmanned System Strategy Development Northwestern Polytechnical UniversityXi’an 710072China Unmanned System Research Institute Northwestern Polytechnical UniversityXi’an 710072China

An impact angle constrained fuzzy adaptive fault tolerant integrated guidance and control method for Ski-to-Turn(STT)missiles subject to unsteady aerodynamics and multiple disturbances is *** aerodynamics appears when flight vehicles are in a transonic state or confronted with unstable ***,actuator failures and multisource model uncertainties are ***,the boundaries of these multisource uncertainties are assumed *** target is assumed to execute high maneuver movement which is unknown to the ***,impact angle constraint puts forward higher requirements for the interception accuracy of the integrated guidance and control(IGC)*** impact angle constraint and the precise interception are established as the object of the IGC ***,the boundaries of the lumped disturbances are estimated,and several fuzzy logic systems are introduced to compensate the unknown nonlinearities and ***,a series of adaptive laws are developed so that the undesirable effects arising from unsteady aerodynamics,actuator failures and unknown uncertainties could be ***,an impact angle constrained fuzzy adaptive fault tolerant IGC method with three loops is constructed and a perfect hit-to-kill interception with specified impact angle can be ***,the numerical simulations are conducted to verify the effectiveness and superiority of the proposed method.

关键词： integrated guidance and control(IGC) impact angle constraint unsteady aerodynamics fault tolerant control(FTC) actuator failures

Extended optimal guidance law with impact angle and acceleration constriants

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Journal of Systems Engineering and Electronics 2014年第5期25卷 868-876页

作者： Ran Li Qunli Xia Qiuqiu Wen Department of Aerospace Beijing Institute of Technology China North Industries Group Corporation

The extended optima straints of miss distance and Schwartz inequality. To reduce guidance law with terminal conmpact angle is derived by the terminal acceleration and eliminate gravity disturbance absolutely, the object function, which designs the weight of control command to be the power function of time-to-go＇s reciprocal, is given. And the gravity is considered when building the state equation. Based on the parsing express of the guidance command change with varying time and adjoint system analysis method, the command characteristics and the non-dimensional miss distance of the guidance law are analyzed, a design principle of guidance order coefficients is discussed. Finally, based on the requirement of engineering, the method to calculate the guidance condition and maximal required acceleration of the guidance law is given. The simulation demonstrates that not only the guidance law can satisfy the terminal position and impact angle constraints, but also the terminal acceleration can be converged toward zero, which will support a good situation for the terminal angle of attacking control.

关键词： impact angle constraint optimal guidance law accel- eration command guidance order.

Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints

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Journal of Systems Engineering and Electronics 2018年第1期29卷 142-151页

作者： LI Ran WEN Qiuqiu TAN Wangchun ZHANG Yijie School of Aerospace Engineering Beijing Institute of technologyBeijing 100081China China North Industries Group Corporation Beijing 100081China Beijing Institute of Aerospace Automatic Control Beijing 100081China

In this paper, a new adaptive optimal guidance law with impact angle and seeker’s field-of-view(FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable impact angle weighting(IAW) coefficient is introduced and used to modify the guidance law to make it adaptive for all guidance constraints. After integrating the closed-form solution of the guidance command with linearized engagement kinematics, the analytic predictive models of impact angle and FOV angle are built, and the available range of IAW corresponding to constraints is certain. Next, a calculation scheme is presented to acquire the real-time value of IAW during the entire guidance process. When applying the proposed guidance law, the IAW will keep small to avoid a trajectory climbing up to limit FOV angle at an initial time but will increase with the closing target to improve impact position and angle accuracy, thereby ensuring that the guidance law can juggle orders of guidance accuracy and constraints control.

关键词： optimal guidance law impact angle constraint fieldof-view(FOV) angle constraint weighting coefficient

Three-dimensional impact angle constrained distributed cooperative guidance law for anti-ship missiles

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Journal of Systems Engineering and Electronics 2021年第2期32卷 447-459页

作者： LI Wei WEN Qiuqiu HE Lei XIA Qunli School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Sichuan Institute of Aerospace Systems Engineering Chengdu 610100China

This paper investigates the problem of distributed cooperative guidance law design for multiple anti-ship missiles in the three-dimensional(3-D)space hitting simultaneously the same target with considering the desired terminal impact angle *** address this issue,the problem formulation including 3-D nonlinear mathematical model description,and communication topology are built *** the consensus variable is constructed using the available information and can reach consensus under the proposed acceleration command along the line-of-sight(LOS)which satisfies the impact time ***,the normal accelerations are designed to guarantee the convergence of the LOS angular ***,consider the terminal impact angle constraints,a nonsingular terminal sliding mode(NTSM)control is introduced,and a finite time convergent control law of normal acceleration is *** convergence of the proposed guidance law is proved by using the second Lyapunov stability method,and numerical simulations are also conducted to verify its *** results indicate that the proposed cooperative guidance law can regulate the impact time error and impact angle error in finite time if the connecting time of the communication topology is longer than the required convergent time.

关键词： distributed cooperative guidance law impact angle constraint communication topology nonsingular terminal sliding mode(NTSM)control finite time convergent