Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application

Flapping-wing micro air vehicles are small, hand-held flying vehicles that can maneuver in a constrained space because of its lightweight, low aspect ratio, and ability to fly in low Reynolds number environment. Flying mammals such as bats, and flying squirrels share a unique feature that allows the...

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Main Author:	Yusoff, Hamid
Format:	Thesis
Language:	English
Published:	2013
Subjects:	TJ1-1570 Mechanical engineering and machinery
Online Access:	http://eprints.usm.my/41111/1/HAMID_YUSOFF_24_Pages.pdf
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id	my-usm-ep.41111
record_format	uketd_dc
spelling	my-usm-ep.411112018-07-19T08:20:22Z Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application 2013 Yusoff, Hamid TJ1-1570 Mechanical engineering and machinery Flapping-wing micro air vehicles are small, hand-held flying vehicles that can maneuver in a constrained space because of its lightweight, low aspect ratio, and ability to fly in low Reynolds number environment. Flying mammals such as bats, and flying squirrels share a unique feature that allows them to fly with amazing agility and maneuverability unmatched by other flying animals of the same size. The unique feature that allows these animals to have such fight capabilities is their thin and flexible membrane wings. In this work, the unique characteristic features of flexible membrane wings associated with flying mammals such as bats are investigated for their highly efficient aerodynamic abilities. The primary goal of this study is to incorporate the mechanism involved in these flying mammals for improved aerodynamic performance of MAV’s. An Electronic Control System (ECS) was introduced to control a proper flapper wing mechanism to emulate the wing flapping of bats for the ongoing micro air vehicle (MAV) research. Besides, aerodynamic tests were carried out in an open-air wind chamber to investigate the aerodynamic characteristics, particularly the wing skin flexibility and camber effect. Furthermore, the optimization using response surface methodology (RSM) was carried out to investigate the interactive relationship of each factor and optimize the aerodynamic performance. In addition to this, three-dimensional numerical simulation was also accomplished on flat and camber wing using FLUENT software. UDFs were written to mimic the harmonic motion of the flapping wing and the dynamic mesh model was utilized. The aerodynamic performance based on lift and drag coefficient were investigated as functions of AoA, frequency, and velocity. Advance ratio parameter was adopted to study the effects of unsteady flow for flexible and camber wing. The proposed ECS demonstrates efficient control and accurate measurement. Moreover, the tedious procedure involved in the repeated calibrations for the manual system was totally eliminated by ECS. It was found that the most flexible wing skin was best suited for unsteady state with low advance ratio, whereas the least flexible wing was preferred for higher ranges. Furthermore, the experimental results showed that the cambered wings have significantly higher lift and drag when compared to that observed in case of flat wings. Moreover, the optimum result for the aerodynamic performance of the flapping wing characterized based on optimum camber, velocity, and frequency was found to be 15%, 4.29 m/s, and 9 Hz respectively. The numerical results were in good agreement with the experimental findings. The numerical results confirmed the enhancement of aerodynamic performance and camber wing was able to increase by as much as 1.12 times when compared to the flat wing. Investigation on the formation of vortices as well as its strength revealed that a higher camber wing was able to generate a higher LEV strength, provided the shape of the vorticity pattern was more compact, more attached, and more concentrated. 2013 Thesis http://eprints.usm.my/41111/ http://eprints.usm.my/41111/1/HAMID_YUSOFF_24_Pages.pdf application/pdf en public phd doctoral Universiti Sains Malaysia Pusat Pengajian Kejuruteraan Mekanik
institution	Universiti Sains Malaysia
collection	USM Institutional Repository
language	English
topic	TJ1-1570 Mechanical engineering and machinery
spellingShingle	TJ1-1570 Mechanical engineering and machinery Yusoff, Hamid Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
description	Flapping-wing micro air vehicles are small, hand-held flying vehicles that can maneuver in a constrained space because of its lightweight, low aspect ratio, and ability to fly in low Reynolds number environment. Flying mammals such as bats, and flying squirrels share a unique feature that allows them to fly with amazing agility and maneuverability unmatched by other flying animals of the same size. The unique feature that allows these animals to have such fight capabilities is their thin and flexible membrane wings. In this work, the unique characteristic features of flexible membrane wings associated with flying mammals such as bats are investigated for their highly efficient aerodynamic abilities. The primary goal of this study is to incorporate the mechanism involved in these flying mammals for improved aerodynamic performance of MAV’s. An Electronic Control System (ECS) was introduced to control a proper flapper wing mechanism to emulate the wing flapping of bats for the ongoing micro air vehicle (MAV) research. Besides, aerodynamic tests were carried out in an open-air wind chamber to investigate the aerodynamic characteristics, particularly the wing skin flexibility and camber effect. Furthermore, the optimization using response surface methodology (RSM) was carried out to investigate the interactive relationship of each factor and optimize the aerodynamic performance. In addition to this, three-dimensional numerical simulation was also accomplished on flat and camber wing using FLUENT software. UDFs were written to mimic the harmonic motion of the flapping wing and the dynamic mesh model was utilized. The aerodynamic performance based on lift and drag coefficient were investigated as functions of AoA, frequency, and velocity. Advance ratio parameter was adopted to study the effects of unsteady flow for flexible and camber wing. The proposed ECS demonstrates efficient control and accurate measurement. Moreover, the tedious procedure involved in the repeated calibrations for the manual system was totally eliminated by ECS. It was found that the most flexible wing skin was best suited for unsteady state with low advance ratio, whereas the least flexible wing was preferred for higher ranges. Furthermore, the experimental results showed that the cambered wings have significantly higher lift and drag when compared to that observed in case of flat wings. Moreover, the optimum result for the aerodynamic performance of the flapping wing characterized based on optimum camber, velocity, and frequency was found to be 15%, 4.29 m/s, and 9 Hz respectively. The numerical results were in good agreement with the experimental findings. The numerical results confirmed the enhancement of aerodynamic performance and camber wing was able to increase by as much as 1.12 times when compared to the flat wing. Investigation on the formation of vortices as well as its strength revealed that a higher camber wing was able to generate a higher LEV strength, provided the shape of the vorticity pattern was more compact, more attached, and more concentrated.
format	Thesis
qualification_name	Doctor of Philosophy (PhD.)
qualification_level	Doctorate
author	Yusoff, Hamid
author_facet	Yusoff, Hamid
author_sort	Yusoff, Hamid
title	Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
title_short	Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
title_full	Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
title_fullStr	Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
title_full_unstemmed	Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application
title_sort	experimental and numerical investigations on the performance of flexible skin flapping wing for micro aerial vehicle application
granting_institution	Universiti Sains Malaysia
granting_department	Pusat Pengajian Kejuruteraan Mekanik
publishDate	2013
url	http://eprints.usm.my/41111/1/HAMID_YUSOFF_24_Pages.pdf
_version_	1747820876801245184

Experimental And Numerical Investigations On The Performance Of Flexible Skin Flapping Wing For Micro Aerial Vehicle Application

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