高超声速风洞颤振试验技术研究

摘要

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。%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.