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To address the challenges in tracking complex maneuvering extended targets, an effective maneuvering extended target tracking method was proposed for irregularly shaped star-convex using a Transformer network. Initially, the alpha-shape algorithm was used to model the variations in the star-convex shape. In addition, a recursive approach was proposed to estimate the irregular shape of an extended target by detailed derivation in the Bayesian filtering framework. This approach accurately estimated the shape of a static star convex extended target. Moreover, through the structural redesign of the target state transition matrix and the real-time estimation of the maneuvering extended target’s state transition matrix using a transformer network, the accurate tracking of complex maneuvering targets was achieved. Furthermore, the real-time tracking of star convex maneuvering extended targets was achieved by fusing the estimated shape contours with motion states. This study focused on constructing certain complex maneuvering extended target tracking scenarios to assess the performance of the proposed method and the comprehensive estimation capabilities of the algorithm considering both shapes and motion states using multiple performance indicators.

In order to intercept a high-speed maneuvering target at a specific attack angle, a three dimensional sliding mode terminal guidance law is designed based on finite-time and small-overshoot prescribed performance control, which is a new method in control field. The linear sliding surface is designed based on the angle of sight deviation and angle of sight rate deviation to ensure that the angle of sight and angle of sight rate converge to the expected value in finite time. On reaching law design, guidance instructions for the yaw plane and pitch plane are designed respectively based on the finite-time and small-overshoot prescribed performance control, ensuring that the tracking error can converge at a preset convergence time and the overshoot is constrained to a small range. At the same time, the nonlinear finite-time observer is introduced to estimate the target acceleration term in the guidance instruction to further improve the guidance accuracy. The simulation results show that the proposed guidance law can intercept targets at specific attack angle under different interception conditions. Compared with the existing fast terminal sliding mode guidance law, the proposed guidance law can guarantee the small-overshoot convergence of sliding mode variables in finite time, and can strike the target form the specific angle. When intercepting maneuvering targets, the miss distance can be controlled below 1 m, improving the steady-state performance and transient performance of the system.

Copyright of Journal of Ordnance Equipment Engineering is the property of Chongqing University of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Systems Engineering & Electronics is the property of Journal of Systems Engineering & Electronics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Systems Engineering & Electronics is the property of Journal of Systems Engineering & Electronics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Aiming at the problem of multi-missile cooperative interception of maneuvering targets, two different cooperative guidance laws are designed based on the time-to-go. For the scenario of multi-missile distributed communication, a distributed cooperative proportional guidance law with time-varying navigation coefficients is designed based on the idea of biased proportional guidance. For the scenario of specified attack time, based on the form of time-to-go under constant lead angle, a sliding mode guidance law with a specified attack time is designed by using sliding mode control and nonlinear disturbance observer. Simulation results show that the two guidance laws proposed in this paper can effectively carry out cooperative attack or sequential attack against maneuvering targets.

In this paper, a filtering algorithm for tracking strong maneuvering targets is proposed to improve the attack ability of air-to-air missiles in air combat. Firstly, by analyzing the filtering algorithm of strong maneuvering targets, a hybrid grid multiple model(HGMM)framework based on interacting multiple model algorithm is constructed. Then, the hybrid grid multiple model algorithm is designed in detail. Finally, numerical simulation shows that the proposed method is feasible and has good tracking effect, the tracking accuracy is improved abaut 20%.

Copyright of Ordnance Industry Automation is the property of Editorial Board for Ordnance Industry Automation and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

During the long coherent integration time in passive radar,the motion parameters (such as high speed,acceleration and jerk motion,etc.) will bring about range migration (RM) and Doppler frequency migration (DFM),further deteriorate the integration performance.To realize the coherent integration of maneuvering targets with jerk motion,a method based on frequency reversing transform (FRT) and modified Lv’s distribution (MLVD) called FRT-MLVD was proposed to achieve the coherent integration and motion parameters estimation.More specifically,the FRT was firstly proposed to remove RM.Then the MLVD was employed to estimate the acceleration and jerk parameters.After compensating the DFM induced by the acceleration and jerk motion,the residual RM was corrected and the velocity and range was achieved via the KT operation.Simulation results demonstrate that the proposed method can effectively compensate the RM and DFM induced by the target motion parameters in passive radar,and for maneuvering targets with jerk motion,the proposed method achieves a better integration and detection performance over existing methods.

In order to make the missile attack ground moving targets such as armored vehicles at a certain impact angle, the variable structure control theory is applied to derive the sliding mode guidance law with impact angle constraint based on the bias proportional guidance, and parameter adaptive power reaching law is designed based on the Lyapunov stability theory. Considering the difficulty of measuring for target speed, the extended states observer (ESO) is introduced to estimate the target speed. Simulation results show that the designed guidance law can accurately hit stationary targets and maneuvering targets with required impact angle, and need less maximum required normal overload and less normal overload near the hit point, and the rear part of trajectory is relatively straight. [ABSTRACT FROM AUTHOR]

Copyright of Journal of Signal Processing is the property of Journal of Signal Processing and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Journal of Guangdong University of Technology is the property of Journal of Guangdong University of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

As the intelligent missile being a major development trend, it is foreseeable that it will become a precise and effective strike weapon in the future battlefields. On the basis of the traditional proportional guidance saw, this paper proposes a guidance algorithm based on reinforcement learning with variable proportional coefficient. Taking the rate as the state, this algorithm designs a discretized action space, as well as a reward function based on the miss distance, to determine the correct guidance command for the missile. The simulation results prove the algorithm possesses better guidance accuracy than the traditional proportional guidance saw and endows the missile with the ability of autonomous decision-making. [ABSTRACT FROM AUTHOR]

In allusion to the coupling relationship among radial velocity variation, range migration, and Doppler spread of a maneuvering target, a Dynamic Programing (DP)-based Weighted Adaptive Coherent Integration (DPWACI) detection method is proposed. The target energy could be efficiently integrated along its trajectory by the proposed method. The main idea of DPWACI is the joint execution of the three operations: the weighted DP procedure that could accurately search the current position and velocity of the target; the improved coherent integration that could calibrate the Doppler shift during the entire process with a large phase spread; and the adaptive step that could make the integration time suitable for each velocity searching bin. The proposed method is applicable to a target with an arbitrary motion without estimating its specific movement parameters. Simulation results and performance comparisons show the exactitude and superiority of the proposed method.

Copyright of Journal on Communication / Tongxin Xuebao is the property of Journal on Communications Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Systems Engineering & Electronics is the property of Journal of Systems Engineering & Electronics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Systems Engineering & Electronics is the property of Journal of Systems Engineering & Electronics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Journal of Harbin Institute of Technology. Social Sciences Edition / Haerbin Gongye Daxue Xuebao. Shehui Kexue Ban is the property of Harbin Institute of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

To solve the problem of multiple missiles attacking a maneuvering target simultaneously from desired directions in plane, a novel cooperative guidance law with line-of-sight angle constraint is proposed. A multiple missiles cooperative guidance model with line-of-sight angle constraint is constructed based on in-plane missiles-target relative motion equations. A distributed finite time cooperative guidance law in the line-of-sight direction is designed based on multi-agent system cooperative control theory and integral sliding mode control theory, which can guarantee the consensus of all missiles' impact times in finite time. In vertical direction of line-of-sight, a nonlinear disturbance observer is adopted to estimate the target's acceleration in finite time, and a guidance law with line-of-sight angle constraint is designed based on finite time sliding mode control theory. The guidance law can guarantee the missile impact the maneuvering target and the missile's line-of-sight angle converge to its desired value in finite time. The cooperative guidance law is demonstrated through simulation results, which makes multiple missiles impact the maneuvering target simultaneously from desired directions. [ABSTRACT FROM AUTHOR]

Copyright of Journal of Ballistics / Dandao Xuebao is the property of Journal of Ballistics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Focused on energy efficiency issues under tracking targets within WSN,a new dynamic power management（DPM） method for tracking distributed targets was proposed combining with the network energy consumption model and wake-up mechanism.With precedent location information of maneuvering target,the algorithm involved both cancelling noise by wavelet filter and predicting target state by autoregressive transformation is introduced to awaken wireless sensor nodes so that their sleep time is prolonged and energy consumption is reduced.According to the current location of maneuvering target,related nodes in an appointed cluster of WSN constitute a distributed dynamic tracking unit,and the cluster head is responsible for collecting the measurement information from the nodes in the tracking unit.A locating algorithm based on the relative posi-tion of two circulars formed on the bases of measurement information is adopted to simplify the process of locatiny and tracking target.Simulation results show that the DPM-based method can reduce the nodes’ energy consumption,meet the locating and tracking accuracy,and can be applied to locate and track the maneuvering targets on the earth surface.

A fuzzy adaptive algorithm is proposed for the imperfections of tracking a maneuvering target using conventional algorithm based on current statistical model. Maneuvering frequency is adjusted in real time by fuzzy reasoning according to the normalized residual and its change rate. Acceleration variance is depicted using residual power function, and the mean value of current acceleration is updated by the de- viation between the estimated and predicted values of acceleration. On this basis, the weight of proposed algorithm is revised by Gauss membership function and strong tracking algorithm. Fuzzy adaptive algorithm is not restricted by maneuvering frequency given manually and extreme value of maximum acceleration, which is suitable for the different ranges and degrees of maneuvering. The performance of the proposed algorithm is tested by tracking three typical maneuvering targets, such as step maneuvering, circular maneuvering, and Jerk maneuvering. Simulated results show the tracking range is expanded using the pro- posed algorithm compared with the conventional tracking algorithm based on current model and the adaptive algorithm based on Jerk model. The proposed algorithm has good steady-state and transient characteristics, and its tracking accuracy and convergence rate are superior to those of the other two algorithms. [ABSTRACT FROM AUTHOR]

Copyright of Journal of Signal Processing is the property of Journal of Signal Processing and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Journal of Signal Processing is the property of Journal of Signal Processing and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

To solve FACSAF algorithm’s problem, this paper proposed a modified algorithm called MFACSAF. It presented a modified fuzzy membership function which used the filtering residual to adjust the adjustment coefficient adaptively. At last, it did a simulation experiment which used MFACSAF algorithm and FACSAF algorithm to predict the track of maneuvering target, and compared their results. The results of simulation experiment show that, MFACSAF algorithm has the same performance as FACSAF algorithm when it predicts general maneuvering targets, and has a better performance than FACSAF algorithm when it predicts strong maneuvering targets. [ABSTRACT FROM AUTHOR]

Abstract: Aimed at the inherent flaws of stable deterministic error in conventional algorithm using Jerk model, a modified algorithm was proposed. Jerk model and current Jerk model were fused in the improved algorithm. Weak Jerk maneuver was described by using Jerk model and its system noise variance was adjusted by using the relations of position estimation error and acceleration change rate variance. The strong Jerk maneuver was described by using the current Jerk model, and the statistical characteristics of acceleration change rate variance was depicted by using modified Rayleigh distribution. The tracking accuracy for weak Jerk maneuver was improved, and the tracking ability for strong Jerk maneuver was enhanced by introducing fuzzy distribution function and strong track filter. The theoretical analysis and simulation results show that the defect of conventional Jerk model algorithm is overcome by using the improved algorithm, Jerk sudden maneuver with various intensity can be approached adaptively. Under different intensity signal-to-noise ratios and gauging noises, its error is relatively stable and it has better tracking accuracy. [ABSTRACT FROM AUTHOR]

In order to improve the performance of interacting multiple model (IMM) algorithm, a multi rate constant-velocity (MRCV) model and a current statistical (CS) model were introduced in IMM algorithm and an adaptive multi-rate interacting multiple model (AMRIMM) algorithm was developed. Monte Carlo simulations show that the AMRIMM algorithm with less computational amount significantly outperforms the standard IMM algorithm using constant-velocity (CV) and constant-acceleration (CA) models. [ABSTRACT FROM AUTHOR]