Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Saleem, Abdul; Lisy, E. R.

doi:10.1109/access.2022.3185606

Cited by 3 publications

(1 citation statement)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Zhang et al (2019) analyzed the ITCG of super-cavitation weapons impact fixed targets by using SMC and Lyapunov stability theorem in. modern strategic targets are equipped with self-defense devices like close-in weapon systems (CIWS), which allow the target to detect and destroy the incoming missiles at close range (Saleem and Lisy, 2022). A single missile based on the traditional guidance law when following a conventional attack trajectory can be easily intercepted or destroyed by the CIWS.…”

Section: Introductionmentioning

confidence: 99%

Impact time guidance law for arbitrary lead angle using sliding mode control

Du,

Yang,

Wang

et al. 2024

AEAT

View full text Add to dashboard Cite

Purpose This paper aims to investigate a novel impact time control guidance (ITCG) law based on the sliding mode control (SMC) for a nonmaneuvering target using the predicted interception point (PIP). Design/methodology/approach To intercept the target with the minimal miss distance and desired impact time, an estimation of time-to-go is introduced. This estimation results in a precise impact time for multimissiles salvo attack the target at the same time. Even for a large lead angle, the desired impact time is achieved by using the sliding mode and Lyapunov stability theory. The singularity issue of the proposed impact time guidance laws is also analyzed to achieve an arbitrary lead angle with the desired impact time. Findings Numerical scenarios with desired impact time are presented to illustrate the performance of the proposed ITCG law. Comparison with the state-of-art impact time guidance laws proves that the guidance law in this paper can enable the missile to intercept the target with minimal miss distance and final impact time error. This method enables multiple missiles to attack the target simultaneously with different distances and arbitrary lead angles. Originality/value An ITCG law based on sliding mode and Lyapunov stability theory is proposed, and the switching surface is designed based on a novel estimation time-to-go for the missile to intercept the target with minimal miss distance. To intercept the target with initial arbitrary lead angles and desired impact time, the authors analysis the singular issue in SMC to ensure that the missile can intercept the target with arbitrary lead angle. The proposed approach for a nonmaneuvering target using the PIP has simple forms, and therefore, they have the superiority of being implemented easily.

show abstract

Section: Introductionmentioning

confidence: 99%

Impact time guidance law for arbitrary lead angle using sliding mode control

Du,

Yang,

Wang

et al. 2024

AEAT

View full text Add to dashboard Cite

show abstract

Performance Analysis of Three Dimensional Impact Time Control Guidance Laws

Saleem

2024

2024 1st International Conference on Trends in Engineering Systems and Technologies (ICTEST)

View full text Add to dashboard Cite

Multiple Constraints-Based Adaptive Three-Dimensional Back-Stepping Sliding Mode Guidance Law against a Maneuvering Target

2022

View full text Add to dashboard Cite

This paper addresses the issue of a complex three-dimension (3-D) terminal guidance process that is used against maneuvering targets while considering both the terminal impact angle (TIA) and field-of-view (FOV) angle constraints. According to the highly coupled and nonlinear 3-D terminal guidance model, an adaptive back-stepping sliding-mode guidance law algorithm is proposed in order to guarantee the stability and robustness of the guidance system. Considering the explicit expression of the line-of-sight (LOS) angle in the kinematics and dynamics of the terminal guidance process, the TIA constraint is transformed into an LOS constraint based on their well-known relationship. In view of the challenges in obtaining the motion information of maneuvering targets, an adaptive law design is introduced in order to estimate and compensate for external disturbances caused by the maneuvering of the target and modeling uncertainty. In addition, because the FOV angle represented by the overall leading angle is not a state variable in the sliding-mode guidance system, it is decoupled into two partial leading angles based on a specific transformation relation, so the 3-D terminal guidance control problem is converted into separate tracking system control issues in the pitch and yaw planes. Then, the Lyapunov stability theory is utilized to substantiate the stability of the guidance system, where the Lyapunov functions in both of the subsystems consist of the LOS and partial FOV state error terms. Finally, a series of simulations of various motion states of maneuvering targets under different terminal cases were carried out. It was proved that the terminal guidance design based on the strategies presented above was able to obtain the desired LOS constraints with satisfying the FOV limitation, and the simulation results verified the effectiveness, universality, and significance for practical applications of the proposed guidance design method.

show abstract

Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Cited by 3 publications

References 24 publications

Impact time guidance law for arbitrary lead angle using sliding mode control

Impact time guidance law for arbitrary lead angle using sliding mode control

Performance Analysis of Three Dimensional Impact Time Control Guidance Laws

Multiple Constraints-Based Adaptive Three-Dimensional Back-Stepping Sliding Mode Guidance Law against a Maneuvering Target

Contact Info

Product

Resources

About