Terminal Impact Angle Control Guidance Law Considering Target Observability

Bin Li; Pan Tang; Haotian Xu; Duo Zheng

doi:10.3390/aerospace9040193

Terminal Impact Angle Control Guidance Law Considering Target Observability

Bin Li, Pan Tang, Haotian Xu, Duo Zheng^*

^*Corresponding author for this work

School of Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

8 Citations (Scopus)

Abstract

The problem of the terminal impact angle control guidance law, considering the target observability for passive guidance with bearing-only measurement, is investigated in this paper. Modified line-of-sight (LOS) angle error dynamics and their closed-loop analytical solution are developed to enhance the target observability, and then their characteristics are studied, which makes the LOS angular rate oscillate in the early stage. The terminal impact angle control guidance law with the global sliding mode is designed to eliminate the approaching stage of sliding mode control, which makes the system robust throughout the entire process of control. Finally, numerical simulations are presented to demonstrate the performance of the proposed guidance law under various conditions, which achieves the desired results.

Original language	English
Article number	193
Journal	Aerospace
Volume	9
Issue number	4
DOIs	https://doi.org/10.3390/aerospace9040193
Publication status	Published - Apr 2022

Keywords

global sliding mode
line-of-sight angle error dynamics
target observability
terminal impact angle control

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10.3390/aerospace9040193

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title = "Terminal Impact Angle Control Guidance Law Considering Target Observability",

abstract = "The problem of the terminal impact angle control guidance law, considering the target observability for passive guidance with bearing-only measurement, is investigated in this paper. Modified line-of-sight (LOS) angle error dynamics and their closed-loop analytical solution are developed to enhance the target observability, and then their characteristics are studied, which makes the LOS angular rate oscillate in the early stage. The terminal impact angle control guidance law with the global sliding mode is designed to eliminate the approaching stage of sliding mode control, which makes the system robust throughout the entire process of control. Finally, numerical simulations are presented to demonstrate the performance of the proposed guidance law under various conditions, which achieves the desired results.",

keywords = "global sliding mode, line-of-sight angle error dynamics, target observability, terminal impact angle control",

author = "Bin Li and Pan Tang and Haotian Xu and Duo Zheng",

note = "Publisher Copyright: {\textcopyright} 2022 by the authors. Licensee MDPI, Basel, Switzerland.",

year = "2022",

month = apr,

doi = "10.3390/aerospace9040193",

language = "English",

volume = "9",

journal = "Aerospace",

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TY - JOUR

T1 - Terminal Impact Angle Control Guidance Law Considering Target Observability

AU - Li, Bin

AU - Tang, Pan

AU - Xu, Haotian

AU - Zheng, Duo

PY - 2022/4

Y1 - 2022/4

N2 - The problem of the terminal impact angle control guidance law, considering the target observability for passive guidance with bearing-only measurement, is investigated in this paper. Modified line-of-sight (LOS) angle error dynamics and their closed-loop analytical solution are developed to enhance the target observability, and then their characteristics are studied, which makes the LOS angular rate oscillate in the early stage. The terminal impact angle control guidance law with the global sliding mode is designed to eliminate the approaching stage of sliding mode control, which makes the system robust throughout the entire process of control. Finally, numerical simulations are presented to demonstrate the performance of the proposed guidance law under various conditions, which achieves the desired results.

AB - The problem of the terminal impact angle control guidance law, considering the target observability for passive guidance with bearing-only measurement, is investigated in this paper. Modified line-of-sight (LOS) angle error dynamics and their closed-loop analytical solution are developed to enhance the target observability, and then their characteristics are studied, which makes the LOS angular rate oscillate in the early stage. The terminal impact angle control guidance law with the global sliding mode is designed to eliminate the approaching stage of sliding mode control, which makes the system robust throughout the entire process of control. Finally, numerical simulations are presented to demonstrate the performance of the proposed guidance law under various conditions, which achieves the desired results.

KW - global sliding mode

KW - line-of-sight angle error dynamics

KW - target observability

KW - terminal impact angle control

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U2 - 10.3390/aerospace9040193

DO - 10.3390/aerospace9040193

M3 - Article

AN - SCOPUS:85128616004

SN - 2226-4310

VL - 9

JO - Aerospace

JF - Aerospace

IS - 4

M1 - 193

ER -

Terminal Impact Angle Control Guidance Law Considering Target Observability

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Keywords

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