Study of flutter on a composite UAV wing

A study of flutter of the VAV composite wing has been done by considering the aeroelasticity phenomenon which involves the dynamic instability of a structure which able to lead a catastrophic failure. To prevent any failure, various design effects and materials parameters of the wing structure for a...

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Main Author:	Zaki, Nurul Zubaidah
Format:	Thesis
Language:	English
Published:	2017
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/78962/1/NurulZubaidahZakiMFKM2017.pdf
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id	my-utm-ep.78962
record_format	uketd_dc
spelling	my-utm-ep.789622018-09-19T05:13:12Z Study of flutter on a composite UAV wing 2017-01 Zaki, Nurul Zubaidah TJ Mechanical engineering and machinery A study of flutter of the VAV composite wing has been done by considering the aeroelasticity phenomenon which involves the dynamic instability of a structure which able to lead a catastrophic failure. To prevent any failure, various design effects and materials parameters of the wing structure for a composite VAV wing are being considered in the study as it able to give a significant effect towards the flutter. The flutter velocity can be obtained by deriving the equation from the binary wing model which governs by mathematical equation related to the effect of aerodynamic damping and stiffness as well as structural damping and stiffness. The most important parameters in this study is the heaving stiffness, Ku and pitching stiffness, Ke which is resulted from the derivation of the full aeroelastic equation of motion. The stiffness can be obtained by simulating or analysis of the wing structures in the finite element software, Abaqus/CAE 6.13-EFI where the natural frequencies of the bending and torsional can be obtained. The equation of full aeroelastic motion can be solved by finding its eigenvalue from the MATLAB software by writing the script file. The flutter speed can be obtained from the intersection point of heaving and pitching frequency across the speed as well as at the point where the damping ratio is zero along the air speed. From the study, a sets of spar and ribs at certain location across the wing has been proves to produce a higher flutter velocity which is 162.31 m/s. 2017-01 Thesis http://eprints.utm.my/id/eprint/78962/ http://eprints.utm.my/id/eprint/78962/1/NurulZubaidahZakiMFKM2017.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:108174 masters Universiti Teknologi Malaysia, Faculty of Mechanical Engineering Faculty of Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Zaki, Nurul Zubaidah Study of flutter on a composite UAV wing
description	A study of flutter of the VAV composite wing has been done by considering the aeroelasticity phenomenon which involves the dynamic instability of a structure which able to lead a catastrophic failure. To prevent any failure, various design effects and materials parameters of the wing structure for a composite VAV wing are being considered in the study as it able to give a significant effect towards the flutter. The flutter velocity can be obtained by deriving the equation from the binary wing model which governs by mathematical equation related to the effect of aerodynamic damping and stiffness as well as structural damping and stiffness. The most important parameters in this study is the heaving stiffness, Ku and pitching stiffness, Ke which is resulted from the derivation of the full aeroelastic equation of motion. The stiffness can be obtained by simulating or analysis of the wing structures in the finite element software, Abaqus/CAE 6.13-EFI where the natural frequencies of the bending and torsional can be obtained. The equation of full aeroelastic motion can be solved by finding its eigenvalue from the MATLAB software by writing the script file. The flutter speed can be obtained from the intersection point of heaving and pitching frequency across the speed as well as at the point where the damping ratio is zero along the air speed. From the study, a sets of spar and ribs at certain location across the wing has been proves to produce a higher flutter velocity which is 162.31 m/s.
format	Thesis
qualification_level	Master's degree
author	Zaki, Nurul Zubaidah
author_facet	Zaki, Nurul Zubaidah
author_sort	Zaki, Nurul Zubaidah
title	Study of flutter on a composite UAV wing
title_short	Study of flutter on a composite UAV wing
title_full	Study of flutter on a composite UAV wing
title_fullStr	Study of flutter on a composite UAV wing
title_full_unstemmed	Study of flutter on a composite UAV wing
title_sort	study of flutter on a composite uav wing
granting_institution	Universiti Teknologi Malaysia, Faculty of Mechanical Engineering
granting_department	Faculty of Mechanical Engineering
publishDate	2017
url	http://eprints.utm.my/id/eprint/78962/1/NurulZubaidahZakiMFKM2017.pdf
_version_	1747818114178875392

Study of flutter on a composite UAV wing

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