实验流体力学
實驗流體力學
실험류체역학
JOURNAL OF EXPERIMENTS IN FLUID MECHANICS
2015年
4期
75-80
,共6页
高超声速%风洞颤振试验%亚临界%颤振边界预测%气动弹性
高超聲速%風洞顫振試驗%亞臨界%顫振邊界預測%氣動彈性
고초성속%풍동전진시험%아림계%전진변계예측%기동탄성
hypersonic%wind tunnel flutter test%subcritical%flutter boundary prediction%aero-elasticity
为实现在高超声速风洞中开展颤振试验研究，设计了高超声速风洞颤振试验装置和模型保护机构。风洞试验表明该试验装置可用于开展高超声速风洞颤振试验研究，支撑方式可避免风洞及其他机构对模型的频率干扰；保护机构在高动压情况下可正常工作，达到模型保护效果。试验验证了高超声速风洞固定马赫数阶梯变动压和连续变动压两种风洞开车方式。为验证高超声速风洞颤振试验技术，对平板翼进行了高超风洞颤振试验，试验马赫数为5．0和6．0。试验采用随机子空间法（SSI）辨识结构模态参数，采用 Zimmerman-Weissenburger 方法预测颤振临界动压，其颤振预测动压比采用活塞理论计算值高12．7％。试验表明目前采用的高超声速风洞颤振试验技术可用于开展高超声速风洞颤振试验研究。
為實現在高超聲速風洞中開展顫振試驗研究，設計瞭高超聲速風洞顫振試驗裝置和模型保護機構。風洞試驗錶明該試驗裝置可用于開展高超聲速風洞顫振試驗研究，支撐方式可避免風洞及其他機構對模型的頻率榦擾；保護機構在高動壓情況下可正常工作，達到模型保護效果。試驗驗證瞭高超聲速風洞固定馬赫數階梯變動壓和連續變動壓兩種風洞開車方式。為驗證高超聲速風洞顫振試驗技術，對平闆翼進行瞭高超風洞顫振試驗，試驗馬赫數為5．0和6．0。試驗採用隨機子空間法（SSI）辨識結構模態參數，採用 Zimmerman-Weissenburger 方法預測顫振臨界動壓，其顫振預測動壓比採用活塞理論計算值高12．7％。試驗錶明目前採用的高超聲速風洞顫振試驗技術可用于開展高超聲速風洞顫振試驗研究。
위실현재고초성속풍동중개전전진시험연구，설계료고초성속풍동전진시험장치화모형보호궤구。풍동시험표명해시험장치가용우개전고초성속풍동전진시험연구，지탱방식가피면풍동급기타궤구대모형적빈솔간우；보호궤구재고동압정황하가정상공작，체도모형보호효과。시험험증료고초성속풍동고정마혁수계제변동압화련속변동압량충풍동개차방식。위험증고초성속풍동전진시험기술，대평판익진행료고초풍동전진시험，시험마혁수위5．0화6．0。시험채용수궤자공간법（SSI）변식결구모태삼수，채용 Zimmerman-Weissenburger 방법예측전진림계동압，기전진예측동압비채용활새이론계산치고12．7％。시험표명목전채용적고초성속풍동전진시험기술가용우개전고초성속풍동전진시험연구。
In order to conduct flutter test research in hypersonic wind tunnels,a hypersonic wind tunnel flutter test apparatus and a model protection device in the form of protective cover were designed.Wind tunnel tests show that the apparatus can be used to carry out the hypersonic wind tunnel flutter test research and to prevent the test model from being interfered by the wind tunnel vibration.The protection device can work in high dynamic pressure situations and protect the model effectively.The results also validate the two ways of driving the wind tunnel with the dynamic pressure changing step by step or continuously at a fixed Mach number.In order to veri-fy the hypersonic wind tunnel flutter testing technique,flat wings flutter tests were conducted on in the hypersonic wind tunnel at Mach 5.0 and 6.0.The stochastic subspace method was used to identify structural model parameters,and the Zimmerman-Weissenburger method was used for predicting the critical flutter dynamic pressure.The results of this prediction were 12.7% larger than the calculated values using the piston theory.
