Superaugmentation and stability augmentation control system for unmanned aerial vehicle

It is always a challenge to compromise between stability and controllability in the design of an aircraft. The challenge is becoming bigger in designing a flight control system of a small, light weight and low speed unmanned aerial vehicle (UAV). This type of UAV is facing a higher degree of difficu...

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Main Author:	Nogoud, Yasser Abdullah Mahjoub
Format:	Thesis
Language:	English
Published:	2017
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/81628/1/YasserAbdullahMahjoubPFKM2017.pdf
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id	my-utm-ep.81628
record_format	uketd_dc
spelling	my-utm-ep.816282019-09-10T01:50:11Z Superaugmentation and stability augmentation control system for unmanned aerial vehicle 2017 Nogoud, Yasser Abdullah Mahjoub TJ Mechanical engineering and machinery It is always a challenge to compromise between stability and controllability in the design of an aircraft. The challenge is becoming bigger in designing a flight control system of a small, light weight and low speed unmanned aerial vehicle (UAV). This type of UAV is facing a higher degree of difficulty because of its constraints in stability margin due to the limitation of the centre of gravity locations and experiencing more problems in control system when flying in air turbulence (severe wind gust or crosswind). This research work is focused on analysis, design and simulation of a robust flight control system (FCS) for a small UAV to make it capable of flying in severe gusty conditions. A combination of the variable stability technique along with advanced flying and handling qualities (FHQ) requirements are used to reduce the gust effect on the aircraft. A low-speed UTM-UAV is used as a testbed for this research. A mathematical model for the aircraft including gust velocity components was formulated based on a combination of experimental wind tunnel with theoretical and empirical methods to estimate the aerodynamics coefficient, thus stability and control derivatives. A linearized longitudinal and lateral-directional equations of motion of the aircraft in the state-space form were developed and validated against a non-linear model. Matlab/Simulink simulation algorithm was developed to analyse and evaluate the dynamic behaviour of the UAV at different speeds and CG locations. The simulation results show that the selection of particular stability and control derivatives has a significant influence on the FHQ level of the aircraft gust response for a small UAV. The superaugmentation FCS that consisted of stability augmentation system (SAS) and command stability augmentation system (CSAS) was developed to improve the dynamic characteristics of the longitudinal aircraft. A simulation result shows that the superaugmented aircraft is capable of operating in severe gust environments than augmented aircraft, and puts less strain on the elevator activity in both extreme and calm weather conditions. A comparison of superaugmented aircraft to augmented aircraft shows a significant reduction (70-80%) in undesirable pitch motion caused by a vertical gust in which, that level 1 flight phase Cat.C can be achieved. 2017 Thesis http://eprints.utm.my/id/eprint/81628/ http://eprints.utm.my/id/eprint/81628/1/YasserAbdullahMahjoubPFKM2017.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:126136 phd doctoral Universiti Teknologi Malaysia Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Nogoud, Yasser Abdullah Mahjoub Superaugmentation and stability augmentation control system for unmanned aerial vehicle
description	It is always a challenge to compromise between stability and controllability in the design of an aircraft. The challenge is becoming bigger in designing a flight control system of a small, light weight and low speed unmanned aerial vehicle (UAV). This type of UAV is facing a higher degree of difficulty because of its constraints in stability margin due to the limitation of the centre of gravity locations and experiencing more problems in control system when flying in air turbulence (severe wind gust or crosswind). This research work is focused on analysis, design and simulation of a robust flight control system (FCS) for a small UAV to make it capable of flying in severe gusty conditions. A combination of the variable stability technique along with advanced flying and handling qualities (FHQ) requirements are used to reduce the gust effect on the aircraft. A low-speed UTM-UAV is used as a testbed for this research. A mathematical model for the aircraft including gust velocity components was formulated based on a combination of experimental wind tunnel with theoretical and empirical methods to estimate the aerodynamics coefficient, thus stability and control derivatives. A linearized longitudinal and lateral-directional equations of motion of the aircraft in the state-space form were developed and validated against a non-linear model. Matlab/Simulink simulation algorithm was developed to analyse and evaluate the dynamic behaviour of the UAV at different speeds and CG locations. The simulation results show that the selection of particular stability and control derivatives has a significant influence on the FHQ level of the aircraft gust response for a small UAV. The superaugmentation FCS that consisted of stability augmentation system (SAS) and command stability augmentation system (CSAS) was developed to improve the dynamic characteristics of the longitudinal aircraft. A simulation result shows that the superaugmented aircraft is capable of operating in severe gust environments than augmented aircraft, and puts less strain on the elevator activity in both extreme and calm weather conditions. A comparison of superaugmented aircraft to augmented aircraft shows a significant reduction (70-80%) in undesirable pitch motion caused by a vertical gust in which, that level 1 flight phase Cat.C can be achieved.
format	Thesis
qualification_name	Doctor of Philosophy (PhD.)
qualification_level	Doctorate
author	Nogoud, Yasser Abdullah Mahjoub
author_facet	Nogoud, Yasser Abdullah Mahjoub
author_sort	Nogoud, Yasser Abdullah Mahjoub
title	Superaugmentation and stability augmentation control system for unmanned aerial vehicle
title_short	Superaugmentation and stability augmentation control system for unmanned aerial vehicle
title_full	Superaugmentation and stability augmentation control system for unmanned aerial vehicle
title_fullStr	Superaugmentation and stability augmentation control system for unmanned aerial vehicle
title_full_unstemmed	Superaugmentation and stability augmentation control system for unmanned aerial vehicle
title_sort	superaugmentation and stability augmentation control system for unmanned aerial vehicle
granting_institution	Universiti Teknologi Malaysia
granting_department	Mechanical Engineering
publishDate	2017
url	http://eprints.utm.my/id/eprint/81628/1/YasserAbdullahMahjoubPFKM2017.pdf
_version_	1747818374970212352

Superaugmentation and stability augmentation control system for unmanned aerial vehicle

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