The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana

High Altitude Long Endurance (HALE) UAV is a type of aircraft that is able to fly in high operational altitude (±65,000 ft) and longer duration (±36 hours). This aircraft uses a high aspect ratio wing, up to 25. In this paper, the design of a high aspect ratio wing will be performed. The Global Hawk...

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Main Authors:	Hadi, Bambang K., Ghofur, Muhammad A., Permana, Indra
Format:	Article
Language:	English
Published:	Faculty of Mechanical Engineering (FKM) and UiTMPress, 2015
Subjects:	Mechanics applied to machinery. Dynamics Mechanical movements
Online Access:	http://ir.uitm.edu.my/id/eprint/16144/ http://ir.uitm.edu.my/id/eprint/16144/1/AJ_BAMBANG%20K.%20HADI%20JME%2015%20%281%29.pdf

id	uitm-16144
recordtype	eprints
spelling	uitm-161442017-02-20T03:18:44Z http://ir.uitm.edu.my/id/eprint/16144/ The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana Hadi, Bambang K. Ghofur, Muhammad A. Permana, Indra Mechanics applied to machinery. Dynamics Mechanical movements High Altitude Long Endurance (HALE) UAV is a type of aircraft that is able to fly in high operational altitude (±65,000 ft) and longer duration (±36 hours). This aircraft uses a high aspect ratio wing, up to 25. In this paper, the design of a high aspect ratio wing will be performed. The Global Hawk RQ-4A was used as a test case. Static strength analysis with Tsai-Wu failure criteria will be used. The carbon/epoxy T300/5208 is selected and the results will be compared with the use of aluminum 2024-T3. Two laminate configurations were used in this study. They were (0°/0°/+450°/-45°)s and a quasi-isotropic (0°/+45°/-45°/90°)s. The aim of the study was to find a minimum weight while fulfilling the strength criteria. Finite Element Method was used extensively during the study, using NASTRAN software. The results showed that the wing with laminate configuration of (0°/0°/+450°/-45°)s was 30% lighter than the one with quasi-isotropic configuration, and was 60% lighter than the aluminum wing. Faculty of Mechanical Engineering (FKM) and UiTMPress, 2015 Article PeerReviewed text en http://ir.uitm.edu.my/id/eprint/16144/1/AJ_BAMBANG%20K.%20HADI%20JME%2015%20%281%29.pdf Hadi, Bambang K. and Ghofur, Muhammad A. and Permana, Indra (2015) The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana. Journal of Mechanical Engineering, 12 (2). pp. 2-11. ISSN 1823-5514
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Teknologi MARA
building	UiTM Institutional Repository
collection	Online Access
language	English
topic	Mechanics applied to machinery. Dynamics Mechanical movements
spellingShingle	Mechanics applied to machinery. Dynamics Mechanical movements Hadi, Bambang K. Ghofur, Muhammad A. Permana, Indra The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
description	High Altitude Long Endurance (HALE) UAV is a type of aircraft that is able to fly in high operational altitude (±65,000 ft) and longer duration (±36 hours). This aircraft uses a high aspect ratio wing, up to 25. In this paper, the design of a high aspect ratio wing will be performed. The Global Hawk RQ-4A was used as a test case. Static strength analysis with Tsai-Wu failure criteria will be used. The carbon/epoxy T300/5208 is selected and the results will be compared with the use of aluminum 2024-T3. Two laminate configurations were used in this study. They were (0°/0°/+450°/-45°)s and a quasi-isotropic (0°/+45°/-45°/90°)s. The aim of the study was to find a minimum weight while fulfilling the strength criteria. Finite Element Method was used extensively during the study, using NASTRAN software. The results showed that the wing with laminate configuration of (0°/0°/+450°/-45°)s was 30% lighter than the one with quasi-isotropic configuration, and was 60% lighter than the aluminum wing.
format	Article
author	Hadi, Bambang K. Ghofur, Muhammad A. Permana, Indra
author_facet	Hadi, Bambang K. Ghofur, Muhammad A. Permana, Indra
author_sort	Hadi, Bambang K.
title	The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
title_short	The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
title_full	The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
title_fullStr	The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
title_full_unstemmed	The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana
title_sort	design of a high aspect ratio hale aircraft composite wing. part i: static strength analysis / bambang k. hadi, muhammad a. ghofur and indrapermana
publisher	Faculty of Mechanical Engineering (FKM) and UiTMPress,
publishDate	2015
url	http://ir.uitm.edu.my/id/eprint/16144/ http://ir.uitm.edu.my/id/eprint/16144/1/AJ_BAMBANG%20K.%20HADI%20JME%2015%20%281%29.pdf
first_indexed	2023-09-18T22:55:25Z
last_indexed	2023-09-18T22:55:25Z
_version_	1777417820944990208

The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana

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