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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التفاصيل البيبلوغرافية
المؤلف الرئيسي:	Mohamad, Firdaus
التنسيق:	أطروحة
اللغة:	English
منشور في:	2012
الموضوعات:	Machine design and drawing Machine construction (General)
الوصول للمادة أونلاين:	https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf
الوسوم:	إضافة وسم لا توجد وسوم, كن أول من يضع وسما على هذه التسجيلة!

id	my-uitm-ir.39638
record_format	uketd_dc
spelling	my-uitm-ir.396382022-07-12T02:58:14Z Design and analysis of yaw stability and control surfaces for UiTM’s BWB UAV baseline-II E-4 / Firdaus Mohamad. 2012 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 https://ir.uitm.edu.my/id/eprint/39638/ https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf text en public masters Universiti Teknologi MARA Faculty of Mechanical Engineering Wisnoe, Wirachman (Professor Dr.)
institution	Universiti Teknologi MARA
collection	UiTM Institutional Repository
language	English
advisor	Wisnoe, Wirachman (Professor Dr.)
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
qualification_level	Master's degree
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.
granting_institution	Universiti Teknologi MARA
granting_department	Faculty of Mechanical Engineering
publishDate	2012
url	https://ir.uitm.edu.my/id/eprint/39638/1/39638.pdf
_version_	1783734524148973568

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

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