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The design of a high aspect ratio HALE aircraft composite wing. Part I: Static strength analysis
Hadi B.K.a, Ghofur M.A.a, Permana I.a
a Lightweight Structures Research Group, Faculty of Mechanical and Aerospace Engineering, Institute of Technology Bandung, Bandung, 40132, Indonesia
[vc_row][vc_column][vc_row_inner][vc_column_inner][vc_separator css=”.vc_custom_1624529070653{padding-top: 30px !important;padding-bottom: 30px !important;}”][/vc_column_inner][/vc_row_inner][vc_row_inner layout=”boxed”][vc_column_inner width=”3/4″ css=”.vc_custom_1624695412187{border-right-width: 1px !important;border-right-color: #dddddd !important;border-right-style: solid !important;border-radius: 1px !important;}”][vc_empty_space][megatron_heading title=”Abstract” size=”size-sm” text_align=”text-left”][vc_column_text]© 2015 by the Faculty of Mechanical Engineering (FKM).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°/+45°/-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°/+45°/-45°)s was 30% lighter than the one with quasi-isotropic configuration, and was 60% lighter than the aluminum wing.[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Author keywords” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Indexed keywords” size=”size-sm” text_align=”text-left”][vc_column_text]Composite wing,HALE UAV,High aspect ratio,Static strength analysis,Tsai-Wu failure criteria[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Funding details” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”DOI” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][/vc_column_inner][vc_column_inner width=”1/4″][vc_column_text]Widget Plumx[/vc_column_text][/vc_column_inner][/vc_row_inner][/vc_column][/vc_row][vc_row][vc_column][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][/vc_column][/vc_row]