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利用回归分析方法,建立声激励下飞机襟翼振动总加速度和总应力对总声压的仿真模型,及总应力对振动总加速度的仿真模型.通过模式识别,得到结构应力响应与加速度线性和非线性关系的界限,以及结构应力响应、结构加速度响应与总声压线性和非线性关系的界限.
Using the regression analysis method, the simulation model of the total acoustic pressure and the total acoustic pressure on the total sound pressure under the acoustic excitation is established, and the simulation model of the total stress and the total vibration of the vibration is established.From the pattern recognition, the relationship between the structural stress response and acceleration linearity and non- The limit of linear relation and the limit of the relationship between structural stress response, structural acceleration response and total sound pressure linearity and nonlinearity.