基于降阶模型的不同厚度翼型颤振边界预测  

Flutter Boundary Prediction of Airfoils with Different Thickness Based on Reduce Order Model

作　　者：周萌[1] 高国柱 ZHOU Meng;GAO Guo-zhu(Aerostatic Platform Department, The No. 38 Research Institute of China Electronics Technology Group Corporation, Hefei 230088 , China)

机构地区：[1]中国电子科技集团公司第三十八研究所浮空平台部

出　　处：《西安航空学院学报》2019年第3期7-14,共8页Journal of Xi’an Aeronautical Institute

摘　　要：为了解决CFD/CSD计算效率低的问题,基于CFD技术,构造降阶的非定常气动力模型,并耦合结构运动方程,建立频域/时域气动弹性系统ROM,采用线性自回归滑动平均模型的系统辨识方法,分析了气动弹性系统的标准模型Isogai二维翼型的颤振边界。结果表明,在翼型最大厚度所在位置保持不变时,计算不同翼型厚度下对应的颤振边界得出,随着翼型厚度增加,跨声速凹坑逐渐左移。因此,当翼型最大厚度所在位置保持不变时,为了达到提高颤振速度的目标,通过采用该方法的计算结果来调整机翼翼型厚度,提高机翼对飞行环境的适应能力。To deal with the low calculation efficiency of CFD/CSD, a ROM is established based on CFD technology, and a frequency-domain/time-domain aeroelastic analysis system is constructed by coupling the structure dynamic equation. Through the systematic identification method of the linear autoregressive moving average model, this method is used to analyze the flutter boundary of Isogai, which is a standard two-dimensional airfoil model of the aeroelastic system. The findings indicate that when the maximum thickness position of airfoil steady remains unchanged, the flutter dip shifts to the left gradually as the thickness increases for symmetrical airfoils. Therefore, when the position of the maximum thickness of the airfoil remains unchanged, in order to achieve the goal of increasing the flutter speed, the airfoil thickness of the wing is adjusted by using the numerical simulation of the method to improve the adaptability of the wing to the flight environment.

关 键 词：降阶模型 翼型 颤振边界 边界预测 气动弹性 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]