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The stochastic sliding mode variable structure guidance laws based on optimal control theory

控制理论与应用（英文版） 2013年第1期11卷 86-91页

作者： Hongqiang WANG Daiqiang CAO Xudong WANG PLA 95997 Unit Engineering College Air Force Engineering University

A stochastic sliding-mode variable structure guidance law involving optimal control theory is presented for the missile target intercept model, in which state noise, uncertain system parameters, target movement and measured noise are considered. This guidance law synthesizes the merits of optimal guidance law with line-of-sight rate convergence and sliding-mode guidance law with strong robustness. Through theoretic analysis, it is proved that the sliding mode hyperplane is sub-achievable in the closed loop system. The numerical results show the effectiveness of the proposed control algorithm.

关键词： Stochastic system Variable structure control Optimal control guidance law Robust

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Effect of Autopilot Structure on Proportional Navigation guidance

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Journal of Beijing Institute of Technology 2007年第2期16卷 177-181页

作者：夏群力刘轶英祁载康 School of Aerospace Science and Engineering Beijing Institute of Technology

The dynamic characteristics of acceleration autopilot and attitude autopilot are discu.ssed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance （PNG） law is the better choice.

关键词： autopilot guidance law guidance and control guidance accuracy

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guidance laws for Path Following Control of Surface Vehicles

Guidance Laws for Path Following Control of Surface Vehicles

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第32届中国控制与决策会议

作者： Zhengyang Wang Bo Wang Qing Fei Beijing Institute of Technology

This paper investigates the fixed-time guidance laws for surface vehicles to pursue the maneuvering target at a desired heading in the presence of disturbance.We propose a new guidance law based on the constant bearing principle,which guarantees the fixed-time convergence of the line-of-sight angular rate regardless of different initial states.Using the proposed guidance law and a new sliding surface,we can track the maneuvering target at a desired angle in fixed time.The proposed algorithms are validated in several simulations.

关键词： guidance law path following surface vehicles sliding mode control

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Design and Implementation of guidance laws for Intercepting Targets with Towed Decoys

Design and Implementation of Guidance Laws for Intercepting ...

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第37届中国控制会议

作者： Zhihong Zhang Kemao Ma Manjun Lu Xiangzhen Yu Harbin Institute of Technology Shanghai Radio Equipment Research Institute

To attack non-maneuvering targets with towed decoys, a new compound guidance concept for head-on interception is proposed. Considering the conical blind area in front of decoy, we formulate a head-on engagement scenario: where the attacking missile enters the blind area of the decoy to avoid the radar jamming from the towed decoy and then attacks the target directly. Based on some common assumptions, the guidance laws for the missile inside and outside the blind area is presented respectively. Moreover, a sufficient condition for the existence of head-on engagement geometry is derived. Finally, numerical simulation is conducted, and the results show satisfactory performance of the compound guidance strategy.

关键词： guidance law Towed Decoy Head-on Interception Conical Blind Area

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Cubic Range Shaping guidance for Maneuvering Targets with Impact Time Constraint

Cubic Range Shaping Guidance for Maneuvering Targets with Im...

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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 cubic range shaping guidance with impact time constraint is proposed for intercepting maneuvering targets.To meet the desired impact time,the range dynamics is employed to track the desired range profiles created via a cubic range shaping approach.The coefficients involved in the range profiles are partially solved with boundary conditions.Then,a robust impact time guidance law is constructed to ensure bounded range tracking errors and estimate the target maneuvers as well using inertial delay control and sliding mode control.The implemented guidance law involves a single parameter that is limited in a compact region,thus making it easy to be tuned.Finally,numerical simulations with various cases are conducted to verify the proposed guidance law.

关键词： guidance law Range Shaping Impact Time

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Three-dimensional guidance method for air to ground missile with impact time constraint

Three-dimensional guidance method for air to ground missile ...

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第37届中国控制会议

作者： Dong Guo Peng Jiang Zixuan Liang Zhang Ren School of Automation Science and Electrical Engineering Beijing University of Aeronautics and Astronautics China Academy of Launch Vehicle Technology School of Astronautics Beijing University of Aeronautics and Astronautics

This paper presents a three-dimensional guidance method based on sliding mode control（SMC） theory for attacking fixed target with time constraint. Assuming the configuration is axisymmetric, the missile movement is decomposed to the lateral plane and longitudinal plane. In the lateral plane, a guidance law is proposed based on the SMC theory, which controls the impact time and the miss-distance simultaneously. In the longitudinal plane, another SMC-based guidance law is implemented to converge the line-of-sight（LOS） rate rapidly. The convergence for both the lateral and longitudinal guidance law is proved by the Lyapunov theory. Simulation results indicate that the proposed three-dimensional guidance method has high control precision for both the impact time and miss-distance. The proposed guidance method is also demonstrated to have the ability to salvo attack.

关键词： air-to-ground missile guidance law time constraint sliding mode control salvo attack

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Fault Tolerant Control for Missile guidance laws with Finite-Time convergence

Fault Tolerant Control for Missile Guidance Laws with Finite...

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2011 Chinese Control and Decision Conference（CCDC）

作者： Zheng Zhu,Yuanqing Xia and Mengyin Fu are with the Department of Automatic Control,Beijing Institute of Technology,Beijing 100081,China..Shuo Wang is with the Lab of Complex Systems and Intelligence Science,Institute of Automation,Chinese Academy of Sciences.

This paper aims to develop hit-to-kill guidance laws for missile interception with actuator faults.New faulttolerant control schemes with sliding mode control and finitetime control are proposed for the design of guidance laws to achieve the interception in the presence of bounded target acceleration.Also,simulation results are presented to illustrate the effectiveness of the control strategies.

关键词： guidance law Sliding mode control Fault tolerant control Finite-time control

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A Re-entry guidance Method for Vehicle Using Virtual Displacement Concept

A Re-entry Guidance Method for Vehicle Using Virtual Displac...

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2010 Chinese Control and Decision Conference

作者： Changsheng Gao,Ruikang Li,Wuxing Jing Department of Aerospace Engineering,Harbin Institute of Technology,Harbin,150001,China

＜正＞A new guidance law for reentry vehicle is presented in this paper.The proposed approach is based on the fact that lateral force is formed in a plane which is perpendicular to the reentry vehicle velocity.Particularly,the nominal impact point is defined as the impact point generated by zero lift trajectory.The virtual displacement is defined as the tiny change of the nominal impact point,which is caused by any instantaneous lateral force at the beginning of the traj ectory.The optimal direction of the lateral force is obtained by the solution of optimal virtual displacement,in which the optimal virtual displacement should point to the target.The analytical solution of reentry trajectory and the linear quadratic gauss（LQG） method are used to design this guidance law.The simulation results demonstrate the effectiveness of the proposed method

关键词： Reentry Vehicle guidance law Virtual Displacement Analytical Solution LQG

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Circular Formation Control for the Cooperative Ground Target Tracking of Unmanned Aerial Vehicle

Circular Formation Control for the Cooperative Ground Target...

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第40届中国控制会议

作者： Jiangbo Jia Xin Chen Min Zhang Weizhen Wang Zhen Li College of Automation Engineering Nanjing University of Aeronautics and Astronautics

This paper investigates a circular formation control strategy for the cooperative ground target tracking of unmanned aerial vehicle（UAV）. We regard the cooperative and tracking as a complete interconnected system and propose a guidance law which has coupled linear and angular velocities. The communication network among vehicles is modeled by a directed cycle graph. The proposed guidance law guarantees that all UAVs move with a prespecified direction and velocity along a common circle with the given center and radius, and maintain evenly spaced along the circle. The effectiveness of the proposed guidance law is validated by simulation.

关键词： circular formation UAV interconnected system guidance law cooperative and tracking

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A guidance-Based Robust Controller for Unmanned Helicopter on Three-Dimensional Path Following

A Guidance-Based Robust Controller for Unmanned Helicopter o...

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第37届中国控制会议

作者： Junfeng Chen Xiaoai Jiang Nanyu Chen Yaoming Zhou School of Aeronautic Science and Engineering Beihang University

A three-dimensional robust path following controller is proposed for an unmanned helicopter with uncertain external disturbance, which is implemented by using dual-loop structure, including an outer-loop for three-dimensional nonlinear path following and an inner-loop for the attitude control. The outer-loop controls the attitude angles and lift to track the expected path and velocity based on the line-of-sight guidance law derived in the flight-path coordination, and the inner-loop was designed based on a backstepping controller in the inertial coordination. The external disturbance were also compensated by using sliding mode disturbance observer based on super-twisting in the inner-loop and the torques were controlled to track the desired attitude.To provide a number of key parameters for path following, the calculation methods are presented. Finally a simulation was carried out to demonstrate the feasibility and performance of the proposed controller.

关键词： unmanned helicopter three-dimensional path guidance law robust sliding mode disturbance observer

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