平尾模型连续变速压颤振试验方法及数值计算研究  

Continuous varying dynamic pressure wind tunnel test method and numerical calculation of flutter characteristics of horizontal tail model

作　　者：刘南 易家宁 王冬[1,2] 侯良学 杨希明[1,2] LIU Nan;YI Jianing;WANG Dong;HOU Liangxue;YANG Ximing(AVIC Aerodynamic Research Institute,Shenyang 110034,China;Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Research,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院气动研究与试验二部,沈阳110034 [2]高速高雷诺数气动力航空科技重点实验室,沈阳110034

出　　处：《振动与冲击》2021年第15期11-17,共7页Journal of Vibration and Shock

摘　　要：为了提升暂冲式风洞跨声速颤振试验效率和安全性,基于自回归滑动平均(auto-regressive moving average,ARMA)系统辨识方法建立了一套高效颤振高效预测方法,基于补偿解耦和专家PID形成FL-60风洞定马赫数连续变速压流场控制技术。将ARMA系统辨识方法通过国际标模AGARD445.6机翼进行验证,颤振速压和频率计算结果与CFD/CSD耦合计算结果差别不超过4%。然后通过风洞流场调试验证FL-60风洞连续变速压流场控制,速压变化线性度高,马赫数控制精度在±0.003。最后通过平尾模型连续变速压颤振试验进行综合验证,阶梯和连续变速压两种试验方式得到的颤振速压差别小于2%,颤振边界计算结果与风洞试验吻合较好,提出的数值方法在试验前可以对车次安排起到良好的指导意义。In order to improve efficiency and safety of transonic flutter tests in a temporary impulse wind tunnel,an efficient flutter prediction method was established based on the auto-regressive moving average(ARMA)system identification method.Based on compensation decoupling and expert PID,a constant Mach number continuous variable pressure flow field control technology was developed for the FL-60 wind tunnel.Firstly,the ARMA system identification method was verified with the international standard model AGARD445.6 wing,and it was shown that the difference between the calculation results for flutter velocity pressure and frequency and those with the CFD/CSD coupled method is not more than 4%.Then,the flow field of the FL-60 wind tunnel was debugged to verify the continuous variable pressure flow field control of the FL-60 wind tunnel,and it was shown that velocity pressure variation has high linearity and the control accuracy of Mach number is±0.003.Finally,flutter tests of the flat tail model with continuous varying velocity pressure were conducted,and the results showed that the difference between flutter velocity pressures obtained by step tests and continuous varying velocity pressure tests is less than 2%;the flutter boundary calculation results agree well with those of wind tunnel tests;the proposed numerical method can provide a good guidance for test arrangement before test.

关 键 词：颤振 风洞试验 系统辨识 连续变速压 

分 类 号：TH212[机械工程—机械制造及自动化] TH213.3