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Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.

UiTM is currently developing a blended wing body aircraft known as UiTM’s BWB UAV Baseline-II. There are a few revolutions made since 2009. The one which concealed with directional control is known as UiTM’s BWB UAV Baseline-II E-4. This aircraft is categorized as a tailless aircraft. Hence, it is u...

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Main Author: Mohamad, Firdaus
Format: Thesis
Language:English
Published: 2012
Subjects:
Machine design and drawing
Machine construction (General)
Online Access:https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf
https://ir.uitm.edu.my/id/eprint/39638/
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spelling my.uitm.ir.396382022-07-12T02:58:14Z https://ir.uitm.edu.my/id/eprint/39638/ Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad. Mohamad, Firdaus Machine design and drawing Machine construction (General) UiTM is currently developing a blended wing body aircraft known as UiTM’s BWB UAV Baseline-II. There are a few revolutions made since 2009. The one which concealed with directional control is known as UiTM’s BWB UAV Baseline-II E-4. This aircraft is categorized as a tailless aircraft. Hence, it is unequipped with any vertical tail to perform the directional motion. This report presents the design process of alternative yaw control surfaces. The alternative yaw control surfaces are designed in order to provide the restoring or rectifying effect to the BWB aircraft. Trade-off study is performed in order to select the best yaw control surfaces for UiTM’s BWB aircraft. From the study, split drag flaps are selected as yaw control surfaces. These control surfaces are selected depending upon the criteria such as the aspect ratio and wing sweep angle. Deflection of the split drag flaps on the one side of the wing will produce asymmetric drag force and as a consequence, yawing moment will be generated. The selected yaw control surfaces will be analyzed using the Computational Fluid Dynamics (CFD) software in order to obtain the aerodynamics data such as drag coefficients (CD), side force coefficients (Cy), lift coefficients (CL) and yawing moment coefficients (CH). The simulation is executed at various sideslip angles (β) up to 30° and split drag flaps total deflection (δT) angles up to 60°. From the results, it is noticed that the UiTM‘s BWB aircraft can perform the directional motion using the split drag flaps. However, lower deflection of split drag flaps is still inadequate to provide restoring yawing moment for the aircraft. This can be seen when negative yawing moment are still generated at the certain sideslip angles. Meanwhile, higher split drag flaps deflection (δT>30°) will produce positive yawing moments throughout the sideslip angles. 2012 Thesis NonPeerReviewed text en https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad. (2012) Masters thesis, thesis, Universiti Teknologi MARA.
institution Universiti Teknologi Mara
building Tun Abdul Razak Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Mara
content_source UiTM Institutional Repository
url_provider http://ir.uitm.edu.my/
language English
topic Machine design and drawing
Machine construction (General)
spellingShingle Machine design and drawing
Machine construction (General)
Mohamad, Firdaus
Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
description UiTM is currently developing a blended wing body aircraft known as UiTM’s BWB UAV Baseline-II. There are a few revolutions made since 2009. The one which concealed with directional control is known as UiTM’s BWB UAV Baseline-II E-4. This aircraft is categorized as a tailless aircraft. Hence, it is unequipped with any vertical tail to perform the directional motion. This report presents the design process of alternative yaw control surfaces. The alternative yaw control surfaces are designed in order to provide the restoring or rectifying effect to the BWB aircraft. Trade-off study is performed in order to select the best yaw control surfaces for UiTM’s BWB aircraft. From the study, split drag flaps are selected as yaw control surfaces. These control surfaces are selected depending upon the criteria such as the aspect ratio and wing sweep angle. Deflection of the split drag flaps on the one side of the wing will produce asymmetric drag force and as a consequence, yawing moment will be generated. The selected yaw control surfaces will be analyzed using the Computational Fluid Dynamics (CFD) software in order to obtain the aerodynamics data such as drag coefficients (CD), side force coefficients (Cy), lift coefficients (CL) and yawing moment coefficients (CH). The simulation is executed at various sideslip angles (β) up to 30° and split drag flaps total deflection (δT) angles up to 60°. From the results, it is noticed that the UiTM‘s BWB aircraft can perform the directional motion using the split drag flaps. However, lower deflection of split drag flaps is still inadequate to provide restoring yawing moment for the aircraft. This can be seen when negative yawing moment are still generated at the certain sideslip angles. Meanwhile, higher split drag flaps deflection (δT>30°) will produce positive yawing moments throughout the sideslip angles.
format Thesis
author Mohamad, Firdaus
author_facet Mohamad, Firdaus
author_sort Mohamad, Firdaus
title Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
title_short Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
title_full Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
title_fullStr Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
title_full_unstemmed Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad.
title_sort design and analysis of yaw stability and control surfaces for uitm’s bwb uav baseline-ii e-4 / firdaus mohamad.
publishDate 2012
url https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf
https://ir.uitm.edu.my/id/eprint/39638/
_version_ 1738513887077072896
score 13.211869

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