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23707

Guidance Law Design Using Intelligent Non-Linear Controller

Article

Last updated: 04 Jan 2025

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Abstract

A sliding mode control algorithm combined with a fuzzy control scheme is developed for the trajectory control of a command guidance system. The acceleration command input is obtained. The proposed controller is used to compensate for the influence of unmodeled dynamics and to alleviate chattering. Simulation results show that the proposed controller gives good system performance in the face of system parameters variation and external disturbances. Moreover, the simulation results show the effectiveness of the proposed missile guidance law against different engagement scenarios.

DOI

10.21608/asat.2009.23707

Keywords

Sliding Mode Control, Fuzzy Logic, missile guidance

Authors

First Name

Y.

Last Name

Elhalwagy

MiddleName

Z.

Affiliation

Egyptian Armed Forces.

Email

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City

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Orcid

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Volume

13

Article Issue

AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009

Related Issue

4377

Issue Date

2009-05-01

Receive Date

2019-01-06

Publish Date

2009-05-01

Page Start

1

Page End

14

Print ISSN

2090-0678

Online ISSN

2636-364X

Article File

ASAT_Volume 13_Issue AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May….pdf

PDF . 188.8kB

Link

https://asat.journals.ekb.eg/article_23707.html

Detail API

https://asat.journals.ekb.eg/service?article_code=23707

Order

47

Type

Original Article

Type Code

737

Publication Type

Journal

Publication Title

International Conference on Aerospace Sciences and Aviation Technology

Publication Link

https://asat.journals.ekb.eg/

MainTitle

Guidance Law Design Using Intelligent Non-Linear Controller

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Article

Created At

22 Jan 2023