实验流体力学Issue(4)：75-80,6.DOI:10.11729/syltlx20150005
高超声速风洞颤振试验技术研究
Research on flutter test technique in hypersonic wind tunnel
摘要
Abstract
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.关键词
高超声速/风洞颤振试验/亚临界/颤振边界预测/气动弹性Key words
hypersonic/wind tunnel flutter test/subcritical/flutter boundary prediction/aero-elasticity分类
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季辰,李锋,刘子强..高超声速风洞颤振试验技术研究[J].实验流体力学,2015,(4):75-80,6.基金项目
国家自然科学基金（91216202）；国防基础科研题目 （）
