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...
Main Authors: | , , |
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Format: | Article |
Language: | English |
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Faculty of Mechanical Engineering Universiti Teknologi MARA (UiTM),
2015.
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Online Access: | Get fulltext View Fulltext in UiTM IR |
LEADER | 01817 am a22001933u 4500 | ||
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001 | 16144 | ||
042 | |a dc | ||
100 | 1 | 0 | |a Hadi, Bambang K. |e author |
700 | 1 | 0 | |a Ghofur, Muhammad A. |e author |
700 | 1 | 0 | |a Permana, Indra |e author |
245 | 0 | 0 | |a The design of a high aspect ratio HALE aircraft composite wing. part I: static strength analysis / Bambang K. Hadi, Muhammad A. Ghofur and IndraPermana |
260 | |b Faculty of Mechanical Engineering Universiti Teknologi MARA (UiTM), |c 2015. | ||
856 | |z Get fulltext |u https://ir.uitm.edu.my/id/eprint/16144/1/AJ_BAMBANG%20K.%20HADI%20JME%2015%20%281%29.pdf | ||
856 | |z View Fulltext in UiTM IR |u https://ir.uitm.edu.my/id/eprint/16144/ | ||
520 | |a 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. | ||
546 | |a en | ||
650 | 0 | 4 | |a Mechanics applied to machinery. Dynamics |
650 | 0 | 4 | |a Mechanical movements |
655 | 7 | |a Article |