摘要
对双后掠布局无人机进行了结构设计,确定了翼面结构方案,并利用有限元软件MSC.Nastran进行应力变形分析,结果达到设计要求;同时为了节省计算周期,以布局外形参数设置为驱动参数,使用CAD软件Catia为结构建立了参数化模型,并将其作为结构优化的输入文件,通过Patran完成优化设置,用Nastran完成结构质量优化,这些工作为气动结构一体化设计奠定了基础。
Based on structure design, the wing structure of new configuration UAV is determined. In order to verify the structure reliability, stress and deformation analysis are carried out with the finite element software MSC. Nastran. The calculating results satisfy design requirements. The dimension drived geometry model was established to reduce the calculation cost. A weight optimization analysis is also carried out with Patran/Nastran software. This work is preparation for the integrated aero-structural optimization and design.
出处
《飞机设计》
2008年第2期29-32,共4页
Aircraft Design
关键词
无人机
结构设计
翼面结构
参数化
优化
UAV
structural design
cranked-wing configuration
parameter
optimization
