Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

Ma, Fei; Wu, Yan; Wang, Siqi; Yang, Xiaofei; Hua, Yueyang

doi:10.1177/01423312211059864

Cited by 7 publications

(4 citation statements)

References 38 publications

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“…Zhang [2] proposed an ITACG with finite time convergence. Yu [1], Chen [3], and Lin [4] proposed fixed-time ITACGs based on the sliding mode theory. Ma [5] designed a disturbance-observer-based ITACG to enable the interception of maneuvering targets.…”

Section: Literature Reviewmentioning

confidence: 99%

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Cubature Kalman Filters Model Predictive Static Programming Guidance Method with Impact Time and Angle Constraints Considering Modeling Errors

Xie

Wei

et al. 2023

Mathematics

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This paper proposes a CKF-MPSP guidance method for hitting stationary targets with impact time and angle constraints for missiles in the presence of modeling errors. This innovative guidance scheme is composed of three parts: First, the model predictive static programming (MPSP) algorithm is used to design a nominal guidance method that simultaneously satisfies impact time and angle constraints. Second, the cubature Kalman filter (CKF) is introduced to estimate values of the influence of the inevitable modeling errors. Finally, a one-step compensation scheme is proposed to eliminate the modeling errors’ influence. The proposed method uses a real missile dynamics model, instead of a simplified one with a constant-velocity assumption, and eliminates the effects of modeling errors with the compensation scheme; thus, it is more practical. Simulations in the presence of modeling errors are conducted, and the results illustrate that the CKF-MPSP guidance method can reach the target with a high accuracy of impact time and angles, which demonstrates the high precision and strong robustness of the method.

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Section: Literature Reviewmentioning

confidence: 99%

“…Because of the design paradigm, the methods presented in Refs. [1][2][3][4][5][6][7] all need a control force both in the LOS and normal LOS direction for time control and angle constraints, respectively. However, most existing missiles are thrust-free and controlled by aerodynamic force in the terminal guidance period.…”

Section: Literature Reviewmentioning

confidence: 99%

Cubature Kalman Filters Model Predictive Static Programming Guidance Method with Impact Time and Angle Constraints Considering Modeling Errors

Xie

Wei

et al. 2023

Mathematics

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“…However, the flight control system is suffering from multiple constraints due to complex flight conditions and inherent physical limitations of the actuator, where actuator input saturation is another important issue for the flight control system. A saturation function [18][19][20] is always introduced to describe the input saturation nonlinearity, where the negative effects of saturation are compensated by building an auxiliary system. Besides, Zhang et al 21 construct an anti-windup compensator to deal with the input saturation.…”

Section: Introductionmentioning

confidence: 99%

Asymmetric integral barrier Lyapunov function-based three-dimensional integrated guidance and control design with field-of-view constraint and input saturation

Feng,

Hou,

Wang

et al. 2024

Advances in Mechanical Engineering

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This paper proposes an adaptive integrated guidance control (IGC) scheme for the flight vehicle intercepting the maneuvering target with asymmetric field-of-view angle constraint, input magnitude and rate saturation, and system uncertainties. A novel nonlinear three-dimensional IGC model is established in the body line-of-sight (LOS) coordinate system by employing the dual-integral control law. Based on this model, the input magnitude and rate saturation for the conventional IGC system can be converted to the limitations of the new augmented states. Asymmetric integral barrier Lyapunov function and dynamic surface control approach are applied to deal with the asymmetric state constraints of the proposed IGC model, and adaptive control laws are designed to compensate for model uncertainties. Furthermore, based on the Lyapunov stability theory, it is proved that all signals in the closed-loop system are bounded while the constrained states are not violated. Finally, the effectiveness and robustness of the proposed IGC scheme are illustrated with numerical simulations.

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“…In recent years, the missile-target engagement has attracted significant attention and a variety of advanced guidance techniques have been developed (Ma et al, 2021(Ma et al, , 2022Wang et al, 2022;Weiss and Shima, 2019). The proportional navigation (PN) guidance and its variants have been widely studied and applied in the field of individual homing guidance situations due to its implementation simplicity and efficiency (Kim and Lee, 2022;Zhou et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

An event-triggered distributed cooperative guidance law for simultaneous attack with autopilot lag consideration

Zhai

Yang

2023

Transactions of the Institute of Measurement and Control

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This article proposes an event-triggered distributed cooperative guidance law for multiple missiles to simultaneously attack a stationary target with consideration of autopilot lag and unknown disturbances. In order to achieve a consensus on each missile’s impact time and save communication costs, the guidance law is designed on the basis of an auxiliary variable consisting of the time-to-go expression and its time derivative. Driven by the properly designed event-triggered mechanism, the information interaction among missiles performs in a need-based scheme and there is no need to continuously monitor the consensus errors between neighbor missiles. By this means, the communication burden is significantly reduced while satisfactory guidance performance is still guaranteed. The proposed guidance law can be extended to a communication failure case where one of the missiles suddenly cannot receive information from its neighbors. An integral sliding mode controller is integrated with the nominal guidance law to eliminate the adverse effects caused by unknown disturbances. Numerical simulations are carried out to illustrate the effectiveness of the proposed guidance design.

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Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

Cited by 7 publications

References 38 publications

Cubature Kalman Filters Model Predictive Static Programming Guidance Method with Impact Time and Angle Constraints Considering Modeling Errors

Cubature Kalman Filters Model Predictive Static Programming Guidance Method with Impact Time and Angle Constraints Considering Modeling Errors

Asymmetric integral barrier Lyapunov function-based three-dimensional integrated guidance and control design with field-of-view constraint and input saturation

An event-triggered distributed cooperative guidance law for simultaneous attack with autopilot lag consideration

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