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Chinese Journal of Aeronautics 2022年第6期35卷 226-239页

作者： Guanlin LI Ming YANG Songyan WANG Tao CHAO Control and Simulation Center Harbin Institute of TechnologyHarbin 150001China

This paper deals with the problem of guidance law design for the single moving mass controlled reentry vehicle when Impact angle constraints and maneuvering target are taken into consideration.More specifically,a modified rolling guidance law is proposed with the interactive virtual target and the landing point prediction strategy.First,considering the fact that the roll channel can be controlled directly,the relative motion between the single moving mass controlled reentry vehicle and the target is described by the error angle between the relative velocity and the line-ofsight.Second,a nonlinear error angle command is given to reduce the rotation rate.To satisfy Impact angle constraints,an interactive virtual target is presented and the‘‘S”formed velocity of the virtual target is given to abate the error angle tracking difficulty at the final stage of the reentry phase.Then,the landing point prediction strategy is employed and the motion variation trend is also taken into consideration.As the maneuvering target is replaced with the predicted landing point,the error angle tracking difficulty caused by the target velocity decreases,which is helpful to meet Impact angle constraints and improve guidance accuracy at the same time.Finally,the finite-time rolling guidance law is proposed and proved via Lyapunov stability theorem.Compared with the existing method,lower-speed rotation,smaller missing distance and less Impact angle errors are obtained,which can be demonstrated by numerical simulations.

关键词： Reentry vehicles Guidance law Impact angle Maneuvering target Finite-time convergence

Impact angle/Time Constraint Guidance Design Based on Fast Terminal Error Dynamics

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Journal of Shanghai Jiaotong university(Science) 2022年第6期27卷 823-832页

作者：秦雪升刘远贺黎克波梁彦刚 College of Aerospace Science and Engineering National University of Defense TechnologyChangsha 410073China Human Key Laboratory of Intelligent Planning and Simulation for Aerospace Mission Changsha 410073China

Considering the problem that the optimal error dynamics can only converge at the terminal time,an Impact angle/time constraint missile guidance law with finite-time convergence is designed in this paper,which is based on the pure proportional navigation(PPN)guidance law and the fast terminal error dynamics(FTED)approach.The missile guidance model and FTED equation are given first,and the dynamic equation of Impact angle/time error based on PPN is also derived.Then,the guidance law is designed based on FTED,and the guidance error can converge to 0 in a finite time.Furthermore,considering the field of view constraint,the guidance law is improved by using the saturation function mapping method.Finally,a numerical simulation example is given to verify the effectiveness of the guidance law,which shows that the guidance law proposed in this paper can make the missile quickly adjust to the desired states in advance,and effectively relieve the overload saturation pressure of the actuator.

关键词： design of guidance law fast terminal error dynamics field-of-view angle impact time Impact angle

Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact angle Constraints

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International Journal of Automation and computing 2018年第2期15卷 218-227页

作者： Hui-Bo Zhou Jun-Hong Song Shen-Min Song School of Mathematical Sciences Harbin Normal University Center for Control Theory and Guidance Technology Harbin Institute of Technology

In order to improve the precision of guidance for the missile intercepting maneuvering targets, this paper proposes a sliding mode guidance law with Impact angle constraints based on the equation of the relative motion of the missile and the target in a 2D plane. Two finite-time convergent guidance laws are proposed based on the nonsingular terminal sliding mode, while, two exponential convergent guidance laws involving dynamic delay are developed through applying the higher-order nonsingular terminal sliding mode. The simulations denote that, in all the four scenarios of the target＇s maneuvering, the guidance laws are able to inhibit the chattering phenomenon of the sliding modes effectively; and from an expected aspect angle, the missiles could attack the targets with high precision and fast speed.

关键词： Autopilot Impact angle nonsingular terminal sliding mode finite-time convergent guidance

Impact angle control over composite guidance law based on feedback linearization and finite time control

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Journal of Systems Engineering and Electronics 2018年第5期29卷 1036-1045页

作者： ZHANG Xiaojian LIU Mingyong LI Yang ZHANG Feihu School of Marine Science and Technology Northwestern Polytechnical University

The Impact angle control over guidance(IACG) law against stationary targets is proposed by using feedback linearization control(FLC) and finite time control(FTC). First, this paper transforms the kinematics equation of guidance systems into the feedbackable linearization model, in which the guidance law is obtained without considering the Impact angle via FLC. For the purpose of the line of sight(LOS) angle and its rate converging to the desired values, the second-order LOS angle is considered as a double-integral system. Then, this paper utilizes FTC to design a controller which can guarantee the states of the double-integral system converging to the desired values. Numerical simulation illustrates the performance of the IACG, in contrast to the existing guidance law.

关键词： guidance law Impact angle feedback linearization finite time control global stabilization

Sliding mode control based guidance law with Impact angle constraint

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Chinese Journal of Aeronautics 2014年第1期27卷 145-152页

作者： Zhao Yao Sheng Yongzhi Liu Xiangdong School of Automation Beijing Institute of Technology Key Laboratory for Intelligent Control & Decision of Complex Systems Beijing Institute of Technology

The terminal guidance problem for an unpowered lifting reentry vehicle against a sta- tionary target is considered. In addition to attacking the target with high accuracy, the vehicle is also expected to achieve a desired Impact angle. In this paper, a sliding mode control （SMC）-based guidance law is developed to satisfy the terminal angle constraint. Firstly, a specific sliding mode function is designed, and the terminal requirements can be achieved by enforcing both the sliding mode function and its derivative to zero at the end of the flight. Then, a backstepping approach is used to ensure the finite-time reaching phase of the sliding mode and the analytic expression of the control effort can be obtained. The trajectories generated by this method only depend on the initial and terminal conditions of the terminal phase and the instantaneous states of the vehicle. In order to test the performance of the proposed guidance law in practical application, numerical simulations are carried out by taking all the aerodynamic parameters into consideration. The effec- tiveness of the proposed guidance law is verified by the simulation results in various scenarios.

关键词： Backstepping Impact angle Sliding mode control Terminal guidance Unpowered lifting reentryvehicle

Three-Dimensional impact Time and angle Guidance via Controlling Line-of-Sight Dynamics

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Three-Dimensional Impact Time and Angle Guidance via Control...

第32届中国控制与决策会议

作者： Tuo Han Yong Xi Guangshan Chen Qinglei Hu School of Automation Science and Electrical Engineering Beihang University Shanghai Aerospace Control Technology Institute Beijing Advanced Innovation Center for Big-Data Based Precision Medicine Beihang University

In this paper,a three-dimensional guidance law is developed for intercepting a maneuvering target with Impact angle constraint at a specified impact time.To achieve this goal,the LOS error dynamics is utilized to track a constant LOS signal and a quadratic LOS profile in the pitch and yaw planes,respectively.The designated LOS profile in the yaw plane has a simple structure,i.e.,a quadratic polynomial in time.To nullify the LOS tracking errors in finite time,the non-singular terminal sliding mode technique is utilized to obtain the guidance commands.Furthermore,a set of reliable LOS profiles are systematically determined to ensure the feasibility of the guidance law.The proposed guidance law can guarantee the desired Impact angles and zero miss distance as mandatory requirements.Meanwhile,a single tuning parameter provides an additional freedom to meet the desired impact time.Finally,numerical results with various engagement scenarios are provided to validate effectiveness of the proposed guidance law.

关键词： Three-Dimensional Guidance impact Time Impact angle Line-of-Sight Shaping

Circle Involute-Based Path Planning and Tracking for Impact angle Control

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Circle Involute-Based Path Planning and Tracking for Impact ...

第32届中国控制与决策会议

作者： Ziqi Wang Qingei Hu Tuo Han Kewei Zhong School of Automation Science and Electrical Engineering Beihang University Beijing Advanced Innovation Center for Big-Data Based Precision Medicine Beihang University Shanghai Aerospace Control Technology Institute

In this paper,a guidance law considering Impact angle constraint for missiles with time-varying velocity is proposed via geometric methods.The guidance concept is based on the geometric property of the circle involute.A simple path planning approach is proposed to find the desired involute trajectory that connects the missile and target while satisfying the Impact angle constraint.Once the desired involute trajectory is determined,the reference line-of-sight（LOS） profiles with respect to the downrange are obtained consequently.Then,a robust guidance law is constructed to achieve the precise tracking of the reference LOS profiles that finally guides missiles with time-varying velocity to meet the Impact angle constraint.Nonlinear simulations under various scenarios are conducted to validate the proposed guidance law.

关键词： Guidance Law Path Planning Impact angle Geometric Methods

Field-of-view Constrained Impact angle Control Guidance Law Against Stationary Targets

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Field-of-view Constrained Impact Angle Control Guidance Law ...

第37届中国控制会议

作者： Xiaotian Chen Jinzhi Wang State Key Laboratory for Turbulence and Complex Systems Peking University

A new Impact angle control guidance law with field-of-view constraint against stationary targets is proposed in this paper. A two-phased strategy with heading error shaping is used to design the guidance law. In the first phase, the missile heading error is driven to zero in finite time. In the second phase, the missile heading error is designed as a function of range. By selecting the guidance parameters, the guidance law can guarantee that the terminal Impact angle constraint is satisfied and the maximum heading error does not violate the limit. The performance of the proposed guidance law is investigated with numerical simulations.

关键词： Guidance Law Impact angle Stationary Targets

Optimal Control Based Guidance Law with Impact angle Constraint

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Optimal Control Based Guidance Law with Impact Angle Constra...

第36届中国控制会议

作者： Xiaotian Chen Jinzhi Wang Peking University

ISBN: (纸本)9781538629185

An optimal Impact angle control guidance law is proposed in this paper.The missile system is approximated under the small heading error assumption and the Impact angle control guidance law is derived based on the approximated system to minimize the energy cost.The proposed guidance law has a form of biased PNG law and it’s in accord with the previous result of PNG in the form acceleration command and time-to-go estimate.As the main advantages,the proposed guidance law has a simpler form and doesn’t require the time-to-go estimate in the acceleration command.In addition,it also shows better performance in energy cost.Numerical simulations are performed to demonstrate the performance of the developed method.

关键词： Missile Guidance Impact angle Optimal

Guidance Law Design Under Impact angle Constraint Based on Nussbaum-type Gain Technique

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Defence Technology（防务技术） 2010年第4期6卷 253-257页

作者：郭建国周军 Institute of Precision Guidance and Control Northwestern Polytechnical University

Aiming at the guidance problem under Impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic relationship between the missile and target in vertical plane,a mathematic model was formulated while the motion of target and the system structure perturbation were regarded as limited disturbances.Based on the ideas of zeroing the rate of line-of-sight(LOS)angle and the impact angular tracking error,a nonlinear control strategy was contrived to obtain adaptive robust guidance law by adopting Nussbaum-type gain technique under a desired Impact angle.The stability of guidance system in finite time is strictly proven by using Lyapunov stability theory.Finally,the numerical simulation verifies the effectiveness of the proposed scheme.

关键词： control and navigation technology of aerocraft stability guidance law Impact angle adaptive control