Nonlinear modified bias proportional navigation guidance law against maneuvering targets

Yaning Wang, Hui Wang*, Defu Lin, Wei Wang

*Corresponding author for this work

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Abstract

To realize the terminal acceleration constraint for a bias proportional navigation guidance law without usage of switching logics, this paper proposes a modified bias term and presents a terminal acceleration constrained bias proportional navigation guidance law against maneuvering targets. First, a so-called virtual planar coordinates whose origin is attached to the point mass of the target is built, so that the original maneuvering target is transformed to a virtual stationary target. On this basis, the common structure of bias proportional navigation guidance law is presented. To realize the terminal acceleration constraint, a modified bias term related to the relative distance between target and missile is used to improve the bias proportional navigation guidance law. With the virtual look angle and the line-of-sight angle constrained, the proposed modified bias proportional navigation guidance law can intercept the maneuvering targets in a desired attack angle. Comparisons with the optimal guidance law in the linear system are carried out, and the proposed law is proved to be near-optimal. The numerical simulation results demonstrate the all-aspect interception capability of the proposed law against maneuvering targets.

Original languageEnglish
Pages (from-to)2949-2975
Number of pages27
JournalJournal of the Franklin Institute
Volume359
Issue number7
DOIs
Publication statusPublished - May 2022

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Wang, Y., Wang, H., Lin, D., & Wang, W. (2022). Nonlinear modified bias proportional navigation guidance law against maneuvering targets. Journal of the Franklin Institute, 359(7), 2949-2975. https://doi.org/10.1016/j.jfranklin.2022.02.012