Performance analysis of realistic true proportional navigation against maneuvering targets using Lyapunov-like approach

Li, Kebo; Su, Wenshan; Chen, Lei

doi:10.1016/j.ast.2017.06.036

Cited by 27 publications

(12 citation statements)

References 12 publications

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“…Therefore, the LOS rate will decrease to zero as r gradually decreases to zero during the guidance process. The above equation can also be obtained in the interception scenario of a missile guided by the true proportional navigation (TPN) 41,45,46 against a nonmaneuvering target.…”

Section: Relative Kinematicsmentioning

confidence: 99%

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Chen

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

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Section: Relative Kinematicsmentioning

confidence: 99%

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Chen

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…True Proportional Navigation (TPN) [2], [3] and Pure Proportional Navigation (PPN) [4]~ [9] are two main PN guidance laws. Commanded acceleration in TPN is normal to LOS, whereas that of PPN is perpendicular to the missile velocity vector.…”

Section: Introductionmentioning

confidence: 99%

Performance of 3-D PPN Against Arbitrarily Maneuvering Target for Homing Phase

Shin

Tsourdos

et al. 2020

IEEE Trans. Aerosp. Electron. Syst.

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The performance analysis of the three-dimensional (3D) pure proportional navigation (PPN) guidance law was traditionally conducted by considering the cross-coupling effect of two independent two-dimensional (2D) PPN laws in the pitch and yaw planes. This could increase the complexity of the analysis and lead to conservative analysis results, especially when the target has maneuverability. To mitigate this issue, this paper theoretically analyses the performance of 3D PPN directly on a rotating engagement plane using a Lyapunov-like approach. Considering practical issues, the analysis includes not only capturability, but also upper-bounds of heading error, line-of-sight (LOS) rate, commanded acceleration, and closing speed. The analysis results obtained are also demonstrated by using numerical simulation examples. Compared to the previous studies providing the least conservative results, the analysis procedure is significantly simplified and the results are proven to be more practical and less conservative.

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“…Proportional navigation (PN) is widely used in the guidance community for its efficiency, robustness, and ease of implementation. [1][2][3] Although PN shows its advantages against nonmaneuvering targets or agile targets with low maneuverability, however, if the maneuverability of the target is close to that of the missile, the performance of PN will be largely degraded.…”

Section: Introductionmentioning

confidence: 99%

Novel adaptive sliding mode guidance law against arbitrarily maneuvering target

Liao

Zhang²,

et al. 2019

Advances in Mechanical Engineering

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A novel adaptive sliding mode guidance law is proposed in this article. The target is assumed to have an arbitrarily but upper bounded maneuvering acceleration which is considered as the system disturbances and uncertainties. The guidance law is consisted of three terms. The first one is a proportional navigation–type term. The second one is a term used for compensating the target maneuvering acceleration. And the last one is a term for controlling the convergence time of the line-of-sight angular rate. In this guidance law, the upper bound of the target acceleration is estimated by an adaptive estimator with a tunable updating law. Hence, the prior knowledge of the upper bound of the target acceleration is not essential for this guidance law. The novel adaptive sliding mode guidance law can guarantee the asymptotical convergence of the line-of-sight rate to zero or its neighborhood, or even the finite time convergence of the line-of-sight rate conditionally. Finally, the new theoretical findings are demonstrated by numerical simulations.

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Performance analysis of realistic true proportional navigation against maneuvering targets using Lyapunov-like approach

Cited by 27 publications

References 12 publications

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Performance of 3-D PPN Against Arbitrarily Maneuvering Target for Homing Phase

Novel adaptive sliding mode guidance law against arbitrarily maneuvering target

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