Staff View: Optimization of fuzzy controller for minimum time response

Optimization of fuzzy controller for minimum time response

Minimum time control is desired for non-linear spacecraft-satellite attitude systems to save on-board thruster fuel. The regulatory time depends on the initial attitude of the satellite. Bang-bang control of satellite attitude can be accomplished with fuzzy logic controller using largest of Maxima d...

Full description

Saved in:

Bibliographic Details
Main Authors:	Nagi F., Perumal L.
Other Authors:	56272534200
Format:	Article
Published:	Elsevier Ltd 2023
Subjects:	Attitude control Bang-bang Fuzzy controller Largest of maximum Membership function spans Optimization Pneumatic rotary actuator Real-time workshop Self tuning parameters Thruster xPC target Bang bang control systems Fuzzy logic Membership functions Navigation Pneumatic actuators Pneumatics Satellites Fuzzy controllers Real time workshop Controllers
Tags:	Add Tag No Tags, Be the first to tag this record!

id	my.uniten.dspace-30910
record_format	dspace
spelling	my.uniten.dspace-309102023-12-29T15:55:43Z Optimization of fuzzy controller for minimum time response Nagi F. Perumal L. 56272534200 24451029600 Attitude control Bang-bang Fuzzy controller Largest of maximum Membership function spans Optimization Pneumatic rotary actuator Real-time workshop Self tuning parameters Thruster xPC target Attitude control Bang bang control systems Fuzzy logic Membership functions Navigation Optimization Pneumatic actuators Pneumatics Satellites Bang-bang Fuzzy controllers Largest of maximum Pneumatic rotary actuator Real time workshop Self tuning parameters Thruster xPC target Controllers Minimum time control is desired for non-linear spacecraft-satellite attitude systems to save on-board thruster fuel. The regulatory time depends on the initial attitude of the satellite. Bang-bang control of satellite attitude can be accomplished with fuzzy logic controller using largest of Maxima defuzzification technique. In case of fuzzy controller, earlier studies show that minimum response time depends on the span of the fuzzy controller membership functions. This paper shows how the non-linear relation between the initial attitude of satellite and spans of the fuzzy controller membership functions are optimized to achieve minimum response time by using Nelder-Mead simplex search method. A practical demonstration of fuzzy bang-bang control is demonstrated here by controlling angular position of a single axis attitude application. The pneumatic rotary actuator is controlled in real-time using Matlab-Simulink xPC target environment. � 2008 Elsevier Ltd. All rights reserved. Final 2023-12-29T07:55:43Z 2023-12-29T07:55:43Z 2009 Article 10.1016/j.mechatronics.2008.11.005 2-s2.0-62249191341 https://www.scopus.com/inward/record.uri?eid=2-s2.0-62249191341&doi=10.1016%2fj.mechatronics.2008.11.005&partnerID=40&md5=336712d2d8fc40bb99ab8b997aa4f0ed https://irepository.uniten.edu.my/handle/123456789/30910 19 3 325 333 Elsevier Ltd Scopus
institution	Universiti Tenaga Nasional
building	UNITEN Library
collection	Institutional Repository
continent	Asia
country	Malaysia
content_provider	Universiti Tenaga Nasional
content_source	UNITEN Institutional Repository
url_provider	http://dspace.uniten.edu.my/
topic	Attitude control Bang-bang Fuzzy controller Largest of maximum Membership function spans Optimization Pneumatic rotary actuator Real-time workshop Self tuning parameters Thruster xPC target Attitude control Bang bang control systems Fuzzy logic Membership functions Navigation Optimization Pneumatic actuators Pneumatics Satellites Bang-bang Fuzzy controllers Largest of maximum Pneumatic rotary actuator Real time workshop Self tuning parameters Thruster xPC target Controllers
spellingShingle	Attitude control Bang-bang Fuzzy controller Largest of maximum Membership function spans Optimization Pneumatic rotary actuator Real-time workshop Self tuning parameters Thruster xPC target Attitude control Bang bang control systems Fuzzy logic Membership functions Navigation Optimization Pneumatic actuators Pneumatics Satellites Bang-bang Fuzzy controllers Largest of maximum Pneumatic rotary actuator Real time workshop Self tuning parameters Thruster xPC target Controllers Nagi F. Perumal L. Optimization of fuzzy controller for minimum time response
description	Minimum time control is desired for non-linear spacecraft-satellite attitude systems to save on-board thruster fuel. The regulatory time depends on the initial attitude of the satellite. Bang-bang control of satellite attitude can be accomplished with fuzzy logic controller using largest of Maxima defuzzification technique. In case of fuzzy controller, earlier studies show that minimum response time depends on the span of the fuzzy controller membership functions. This paper shows how the non-linear relation between the initial attitude of satellite and spans of the fuzzy controller membership functions are optimized to achieve minimum response time by using Nelder-Mead simplex search method. A practical demonstration of fuzzy bang-bang control is demonstrated here by controlling angular position of a single axis attitude application. The pneumatic rotary actuator is controlled in real-time using Matlab-Simulink xPC target environment. � 2008 Elsevier Ltd. All rights reserved.
author2	56272534200
author_facet	56272534200 Nagi F. Perumal L.
format	Article
author	Nagi F. Perumal L.
author_sort	Nagi F.
title	Optimization of fuzzy controller for minimum time response
title_short	Optimization of fuzzy controller for minimum time response
title_full	Optimization of fuzzy controller for minimum time response
title_fullStr	Optimization of fuzzy controller for minimum time response
title_full_unstemmed	Optimization of fuzzy controller for minimum time response
title_sort	optimization of fuzzy controller for minimum time response
publisher	Elsevier Ltd
publishDate	2023
_version_	1806428104235679744
score	13.222552

Optimization of fuzzy controller for minimum time response

Similar Items