基于降阶模型的翼型颤振主动抑制研究  

On Active Flutter Suppression of Airfoils Basedon Reduced-order Model

作　　者：高国柱 周萌[1] GAO Guo-zhu;ZHOU Meng(Aerostatic Platform Department,No.38 Research Institute of China Electronics TechnologyGroup 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,合肥230088

出　　处：《西安航空学院学报》2020年第1期28-31,75,共5页Journal of Xi’an Aeronautical Institute

摘　　要：为了解决CFD/CSD计算效率低下的问题,基于气动力降阶模型建立开环气动弹性分析系统,耦合操纵面模态对应的气动状态空间方程,发展了一套伺服气动弹性分析系统,设计主动控制律从而进行二维翼型颤振抑制。结果表明,基于ROM计算的无量纲颤振速度准确性及精度高;使用开、闭环气弹系统时基于ROM和CFD分别仿真时域仿真结果吻合较好;基于ROM闭环气弹系统的NACA0012翼型气弹颤振边界比开环气弹系统提高了约20%。研究结果为有效抑制翼型颤振提供一种快速计算和设计方法。In order to solve the problem of low efficiency of the CFD/CSD aeroelastic analysis method,the open-loop aeroelastic analysis system based on aerodynamic reduced-order model and the aerodynamic state space equation are used to develop a servo aeroelastic analysis system to perform flutter suppression.The results of the closed-loop simulation show that the accuracy and precision of dimensionless flutter speed based on ROM calculations are high;the time-domain simulation results based on ROM and CFD when using open and closed-loop aeroelastic systems are highly consistent;the flutter boundary of NACA0012 airfoil based on ROM closed-loop aeroelastic system is about 20%higher than that of the open-loop aeroelastic system.The research results provide a rapid evaluation and design method for the effective suppression of airfoil flutter.

关 键 词：降阶模型 翼型颤振 主动抑制 CFD/CSD 主动控制律 二维翼型 颤振边界 

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]