Size optimization design of composite wing for UAV

doi:10.19936/j.cnki.2096-8000.20211228.013

Abstract

Abstract: In order to deduce the structure weight and perform the properties of composite in the swept wing structure for UAV, the size optimization was conducted in the wing configuration with a double closed cell rectangular beam in the specific position. The composite wing adopted T800 carbon fiber woven clothes. Through commercial software MSC. Patran and Nastran, 89 variables, the thicknesses of 45° and 0° in different subareas and the widths of ribs were optimized to minimize the structure weight. The constraints of the optimized model included the strength and stiffness of the wing structure. The Tsai-Wu failure criterion was utilized to calculate the damage factors and determine the damage of composite structure. The optimized results satisfied the characteristics of force transmission within the main components of the swept wing, and met the strength, stiffness and weight requirements of the composite wing.

Key words: UAV, composite wing, size optimization, Tsai-Wu failure criterion

CLC Number:

TB332

SHEN Hao-jie, CHEN Gang, XIA Yang. Size optimization design of composite wing for UAV[J]. COMPOSITES SCIENCE AND ENGINEERING, 2021, 0(12): 82-88.

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