飞行器跨声速气动弹性数值分析  

NUMERICAL ANALYSES OF TRANSONIC FLUTTER ON AN AIRCRAFT

作　　者：杨国伟[1] 钱卫[2] 

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,北京100080 [2]中国航空总公司第一集团沈阳飞机设计研究所,沈阳110000

出　　处：《力学学报》2005年第6期769-776,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(10372106).~~

摘　　要：将流体和结构运动方程分别构造为含子迭代的计算格式,发展了一种紧耦合气动弹性分析方法.其中流体计算的空间离散采用改进的HLLEW(Harten—Lax-van Leer-Einfeldt-Wada)格式. TFI(transfinite inter- polation)方法用于生成随结构变形的自适应多块动网格.利用所发展的方法,对-翼-身-尾气动外形,数值预测了马赫数在0.3-1.3范围内的气动颤振边界.并详细研究了时间步长、子迭代步数、初始流场、耦合方法、疏密网格对颤振计算结果的影响.In the paper, a fully-coupled numerical method has been developed by the subiteration discretizitions of fluid and structure governing equations for transonic flutter analyses. The modified HLLEW （Harten-Lax-van Leer-Einfeldt-Wada）scheme is used for the solution of fluid equations. TFI （transfinite interpolation） technique is applied for the adaptive grid deformation. For a wing-body-stabilizer aerodynamic configuration, flutter boundaries were predicted by the developed solver in the range of Mach number from 0.3 to 1.3. Effects of various factors for the prediction of flutter boundaries, such as time-step size, subiteration number, initial flowfield, coupling algorithm, grid dependence were emphatically investigated.

关 键 词：气动弹性 颤振边界 耦合算法 计算流体力学 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]