基于共模型技术的大展弦比飞机气动/结构耦合性设计  

Coupled Aerodynamic Structural Design of High-aspect Ratio Aircraft Based on the Shared Model Technology

作　　者：谭林林[1] 瞿进[1] 

机构地区：[1]上海飞机设计研究院总体气动设计研究部,上海200235

出　　处：《民用飞机设计与研究》2011年第1期7-12,共6页Civil Aircraft Design & Research

摘　　要：在考虑弹性变形情况下,以大展弦比飞翼飞机为例,对气动/结构耦合设计方法进行研究提出了几何/结构/气动的共模型技术。首先是基于共模型技术生成表面气动网格和空间气动网格以及结构有限元网格,并实现气动载荷在结构模型和气动模型间的数据传递,最后进行气动/结构耦合计算分析,在进行气动/结构耦合计算分析时要进行多次迭代,直到结构变形达到收敛标准。在迭代的过程中要根据结构弹性变形,重建气动模型。整个设计思想是基于共模型技术将飞机的非线性气动力和结构变形同时考虑到飞机的飞行载荷计算中,更好地研究了大展弦比飞机静气动弹性问题。Considering the situation of elastic deformation, the coupled aerodynamic-structural design was performed. In the study, the shared model technology of three-dimensional shape,the aerodynamic model and the finite element model was developed. Firstly,aerodynamic surface mesh, space air grid, as well as the finite element mesh must be generated based on the shared model technology. Secondly,It must be achieve that aerodynamic load transferred between the structure of model and aerodynamic model. Finally, the coupled aerodynamic-structural analyses is perform .It was iterative until reaching to the request of the convergence. During the procedure ,the aerodynamic model must be reconstructed according with the deformation of the model. The whole design ideal was that the nonlinear aerodynamics and the structure deformation was taken account to the flight load design ,which was better to research the aero elasticity of high-aspect ratio aircraft.

关 键 词：气动/结构耦合设计 共模型技术 气动模型 有限元模型 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]