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设计了舵面颤振试验装置,在亚跨超风洞中对展弦比2.0的NACA0012矩形舵面开展了颤振试验研究。试验马赫数范围为0.3~0.75。试验采用直接观测法获得舵面在不同质量特性条件下的亚声速和接近跨声速的颤振特性。同时还采用亚临界数据分析方法对试验的扭转应变信号进行了离线分析,即通过采用ARMA方法识别扭转应变信号的阻尼和频率,并通过阻尼外插得到颤振临界动压值。研究结果表明:该试验装置可以用于在现有亚跨超风洞中开展舵面颤振问题研究。当采集的亚临界信号为典型指数衰减信号时,以ARMA方法为基础的亚临界颤振试验技术可以稳定地识别出信号阻尼和频率,并较为准确地获得舵面的颤振临界动压、颤振频率等颤振参数。
The rudder flutter test device was designed and the flutter test was conducted on the NACA0012 rectangular rudder with an aspect ratio of 2.0 in the subsonic wind tunnel. Test Mach range of 0.3 ~ 0.75. The direct observation method is used to obtain the subsonic and near-flutter flutter characteristics of the rudder surface under different mass characteristics. At the same time, the sub-critical data analysis method was used to analyze the torsional strain signal of the experiment. The damping and frequency of the torsional strain signal were identified by ARMA method and the critical dynamic flutter pressure was obtained by damping extrapolation. The results show that the device can be used to study the flutter of the control surface in the existing subsurface supercavity. When the acquired subcritical signal is a typical exponential decay signal, the subcritical flutter test technique based on the ARMA method can stably identify the signal damping and the frequency, and obtain the critical flutter dynamic pressure of the rudder surface more accurately Vibration frequency and other chatter parameters.