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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

Highly Maneuvering target tracking using multi-parameter fusion Singer model

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Journal of Systems Engineering and Electronics 2017年第5期28卷 841-850页

作者： Shuyi Jia Yun Zhang Guohong Wang Research Institute of Information Fusion Naval Aeronautical and Astronautical University Department of Aircraft Engineering Naval Aeronautical and Astronautical University

An algorithm of highly Maneuvering target tracking is proposed to solve the problem of large tracking error caused by strong maneuver. In this algorithm, a new estimator, named as multi-parameter fusion Singer (MF-Singer) model is derived based on the Singer model and the fuzzy reasoning method by using radial acceleration and velocity of the target, and applied to the problem of Maneuvering target tracking in strong maneuvering environment and operating environment. The tracking performance of the MF-Singer model is evaluated and compared with other manuevering tracking models. It is shown that the MF-Singer model outperforms these algorithms in several examples.

关键词： Maneuvering target multi-parameter fusion Singer (MF-Singer) fuzzy reasoning Singer model

Modified unscented Kalman filter using modified filter gain and variance scale factor for highly Maneuvering target tracking

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Journal of Systems Engineering and Electronics 2014年第3期25卷 380-385页

作者： Changyun Liu Penglang Shui Gang Wei Song Li National Laboratory of Radar Signal Processing Xidian University College of Air and Missile Defense Air Force Engineering University

To improve the low tracking precision caused by lagged filter gain or imprecise state noise when the target highly maneuvers, a modified unscented Kalman filter algorithm based on the improved filter gain and adaptive scale factor of state noise is presented. In every filter process, the estimated scale factor is used to update the state noise covariance Qk, and the improved filter gain is obtained in the filter process of unscented Kalman filter （UKF） via predicted variance Pk｜k-1, which is similar to the standard Kalman filter. Simulation results show that the proposed algorithm provides better accuracy and ability to adapt to the highly Maneuvering target compared with the standard UKF.

关键词： unscented Kalman filter （UKF） target tracking filter gain Maneuvering target nonlinearity modified unscented Kalman filter （MUKF）.

Maneuvering target tracking by adaptive statistics model

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The Journal of China Universities of Posts and Telecommunications 2013年第1期20卷 108-114页

作者： JIN Xue-bo DU Jing-jing BAO Jia College of Computer and Information Engineering Beijing Technology and Business University College of Informatics Zhejiang Sci-Tech University

A good model can extract useful information about the target＇s state from observations effectively. There are many models used to tracking a, Maneuvering target such as constant-velocity （CV） model, Singer acceleration model （zero-mean first-order Markov model） and current model （mean-adaptive acceleration model）, etc. While due to the complexity of Maneuvering target, to seek the target model which can get better performance is still a subject worthy of study. Based on statistics relation between the autocormlation function and the covariance of Markov random processing, this paper develops a model which can adaptively adjust system parameters on line. Simulations show the good estimation performance get by the model developed here, and comparing CV, Singer and current models, the model can adaptively get the model parameter while tracking the trajectory and needn＇t doing several tests to obtain a priori parameter.

关键词： Maneuvering target target model statistics relation state estimation

Rotational parameters estimation of Maneuvering target in ISAR imaging

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Journal of Systems Engineering and Electronics 2010年第1期21卷 41-46页

作者： Wenchen Li Jin Liu Xuesong Wang Shunping Xiao Guoyu Wang 63880 Unit PLA Luoyang 471003 R R. China School of Electronic Science and Engineering National University of Defense Technology Changsha 410073 P. R. China

The rotational parameters estimation of Maneuvering target is the key of cross-range scaling of ISAR （inverse synthetic aperture radar）, which can be used in the target feature extraction. The cross-range signal model of rotating target with fixed acceleration is presented and the weighted linear least squares estimation of rotational parameters with fixed velocity or acceleration is proposed via the relationship of cross-range FM （frequency modulation） parameter, scatterers coordinates and rotational parameters. The FM parameter is calculated via RWT （Radon-Wigner transform）. The ISAR imaging and cross-range scaling based on scaled RWT imaging method are implemented after obtaining rotational parameters. The rotational parameters estimation and cross-range scaling are validated by the ISAR processing of experimental radar data, and the method presents good application foreground to the ISAR imaging and scaling of Maneuvering target.

关键词： inverse synthetic aperture radar Maneuvering target rotational parameters estimation cross-range scaling scaled Radon-Wigner transform imaging.

Nonlinear differential geometric guidance for Maneuvering target

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Journal of Systems Engineering and Electronics 2012年第5期23卷 752-760页

作者： Jikun Ye Humin Lei Dongfeng Xue Jiong Li Lei Shao Department of Missile Engineering Missile Institute of Air Force Engineering University Sanyuan 713800 E R. China Department of Strategies Science College of Air Force Engineering University Xi'an 710051 E R. China

Based on the idea of zeroing the line of sight rate（LOSR）,a novel nonlinear differential geometric（DG） law for intercepting the agile target is proposed.In the first part,the DG formulations are utilized to describe the relatively kinematics model of missile and target,and the nonlinear DG guidance（DGG） law is proposed based on the nonlinear control theory to eliminate the influence brought by target.Further,the missile guidance commands are derived to overcome the information loss caused by decoupling condition,the new necessary initial condition is developed to guarantee capture the agile target.Then,the designed nonlinear DGG commands are transformed from an arc-length system to the time domain.A desirable aspect of the designed guidance law is that it does not require rigorous information about target acceleration.Representative numerical results show that the designed guidance law obtain a better performance than the traditional DGG law for agile target.

关键词： guidance differential geometric nonlinear control stability Maneuvering target

New computing method of weighted coefficients for tracking a Maneuvering target using PDAF in the presence of clutter

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Journal of Systems Engineering and Electronics 2009年第5期20卷 968-973页

作者： Liu Zongxiang Xie Weixin Huang Jingxiong Coll. of Information and Engineering Shenzhen Univ. Shenzhen 518060 P. R. China

To avoid or reduce the influence of unpredictable motion mode on data association, a new computing method of weighted coefficients of measurements for PDAF is presented in which it is assumed that the current turn rate of a Maneuvering target changes within a limited range and its turn may be in arbitrary direction during data association. Thus, the predicted center for computing the weighted coefficients is a curved surface in 3-D space, which differs from the predicted center for setting up a validation gate, namely, a point in 3-D space. The distance between a measurement and the curved surface is used to compute its weighted coefficient. To reduce the computational complexity of weighted coefficients, the formulas for computing the maneuvering direction angle and turn rate corresponding to a measurement are presented. Simulation results show the proposed method reduces the percentage of lost tracks and improves the state estimation accuracy in tracking a Maneuvering target using PDAF in the presence of clutter.

关键词： target tracking Maneuvering target data association weighted coefficient.

Track Initiation Algorithm for Maneuvering target Using Radial Velocity Measurements

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Track Initiation Algorithm for Maneuvering Target Using Radi...

Event-Triggered-Backstepping-Based Parallel Approaching Guidance Method for Maneuvering target Interception

第26届中国控制与决策会议

作者： Yuan Junquan Yin Shuai Jiang Jin Wang Licai Air force Early-warning Academy

ISBN: (纸本)9781479937097

Aiming at the track initiation of Maneuvering target for track-while-scan（TWS） multiple frequency continuous wave（CW） radar, a new method using the radial velocity measurements is discussed. Firstly, the Maneuvering target model and observation model including radial velocity are built. Then the wave gate design and algorithm for track initiation using the radial velocity measurements are analyzed. Finally the performance of target tracking is compared for different wave gate design methods from the view of constant ranging errors and changing errors by Monte Carlo simulation.

关键词： Multiple Frequency CW Radar Maneuvering target Track Initiation Radial Velocity

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Guidance, Navigation and Control 2022年第1期2卷 77-100页

作者： Yaohua Shen Mou Chen Zixuan Zheng Hongzhen Guo College of Automation Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China School of Astronautics National Key Laboratory of Aerospace Flight DynamicsNorthwestern Polytechnical UniversityXian 710072P.R.China

In order to achieve a straight ballistic trajectory of missile and reduce the update frequency of the missile normal acceleration for the interception of Maneuvering target,a backstepping-based parallel approaching guidance method is designed with nonlinear disturbance observer(NDO)technique and event-triggered(ET)mechanism in this paper.In order to suppress the adverse e®ect of target maneuver,the NDO is designed to estimate the target maneuvering acceleration.Then,the NDO-based backstepping method is used to obtain the normal acceleration of missile and realize the parallel approaching guidance.In order to reduce the update frequency of missile normal acceleration,the ET mechanism is employed in the parallel approaching guidance method.If the missile trajectory is relatively straight,the normal acceleration of missile remains unchanged.On the contrary,if the missile trajectory is not straight,the normal acceleration of missile is updated to make the missile trajectory straight.In this way,the ET-based parallel approaching guidance can be obtained.Furthermore,a determined method for the initial missile°ight-path angle is proposed to keep the normal acceleration of missile at zero in the initial stage of interception.Besides,Lyapunov stability analysis method is used to prove that all signals in the closed-loop guidance system are uniformly ultimately bounded.Finally,simulation results show the e®ectiveness of the proposed guidance method.

关键词： Parallel approaching guidance Maneuvering target nonlinear disturbance observer event-triggered mechanism backstepping method

Time-varying formation pursuit based cooperative guidance for multiple missiles to intercept a Maneuvering target

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Time-varying formation pursuit based cooperative guidance fo...