摘要
本文对无人机复合材料后掠机翼结构进行尺寸优化设计。该机翼采用双闭室矩形梁式布局。采用商用分析软件,优化各分区T800碳纤维编织布预浸料45°与0°铺层的厚度与翼肋宽度。优化模型选取机翼结构的强度与刚度作为约束条件,结构重量最小作为优化目标。选用蔡-吴准则作为复合材料失效判定准则。优化结果符合机翼主要零件的传力特点,满足复合材料机翼的设计要求。
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.
作者
沈浩杰
陈刚
夏杨
SHEN Hao-jie;CHEN Gang;XIA Yang(Nanjing Institute of Simulation Technology,Nanjing 210016,China)
出处
《复合材料科学与工程》
CAS
北大核心
2021年第12期82-88,共7页
Composites Science and Engineering
作者简介
沈浩杰(1988-),男,博士,工程师,主要从事无人机总体结构设计、复合材料结构设计与分析方面的研究,shhaojie@126.com。
