静气动弹性计算方法研究  

STATIC AEROELASTIC ANALYSIS OF A FLYING-WING USING DIFFERENT MODELS

作　　者：陈大伟[1] 杨国伟[1] 

机构地区：[1]中国科学院力学研究所高温气体动力学重点实验室,北京100190

出　　处：《力学学报》2009年第4期469-479,共11页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金(10672168);国家自然基金创新研究群体项目(10621202)资助项目~~

摘　　要：对基于结构网格的Euler方程及N-S方程求解器和基于非结构网格的Euler方程求解器,采用结构模态分析方法和柔度矩阵方法,对无人机大展弦比机翼在Ma=0.6,α=2°,飞行高度20km的巡航状态下的静气动弹性特性进行了数值模拟.验证了两种求解器对静气动弹性模拟的准确性.同时,对模态分析方法和柔度矩阵方法进行了对比研究,发现柔度矩阵方法更适用于静气动弹性数值模拟.另外,对应用物面法向偏转方法替代网格变形技术模拟静气动弹性进行了研究,计算表明物面法向偏转方法可以大大提高静气动弹性计算效率和克服机翼结构变形过大时动网格技术无法处理的不足.A loosely-coupled procedure for static aeroelastic analysis of a flying wing is presented. Firstly, the flow solvers used are based on an Euler model and a RANS model with structured grid, and an Euler model with unstructured grid. Secondly, the structure modal analysis and flexibility matrix method are all applied. Furthermore, a theoretical case of the flying wing is carried out in cruise condition of Mach number of 0.6 and the angle of attack of 2° at 20 km altitude. The results show that the flexibility matrix method is more suitable for static aeroelastic analysis than the structure modal analysis. Meanwhile, a surface deflection method is validated to be more efficient than the grid deformation method in the computation analysis due to the three-dimensional geometries deformation.

关 键 词：静气动弹性 柔度矩阵法 非结构网格 结构网格 模态法 物面法向偏转方法 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]