超高声速飞行器的动力学环境频域宽，使用有限元/边界元方法预示其振动响应存在困难。基于统计能量分析(Statistical energy analysis, SEA)理论建立某型高速飞行器声振耦合动力学模型，用理论解析和经验公式的方法确定各子系统的输入参数，以实际噪声试验条件作为飞行器SEA模型的输入激励，对飞行器舱内噪声声压级和子系统振动加速度响应进行预示，并与试验结果进行比较。结果显示，子系统振动加速度功率谱密度(Power spectral density, PSD)在中高频与试验结果基本一致，舱内声压在整个频段内误差小于3 dB，因此建立的动力学模型和采用的计算方法是可靠的，解决了有限元、边界元在中高频声振响应问题计算的局限性。通过传递路径分析寻找出舱内声场的主要来源，提出以损耗因子为设计变量的噪声控制与优化方法，利用遗传算法实现了这一非线性约束问题求解，为研究飞行器结构和复杂动力学环境以及飞行器降噪优化设计提供有效的手段。
Since dynamic environment of the hypersonic aircraft has a wide frequency domain, it is difficult to predict the vibration response with finite element methods. A certain type of high-speed aircraft’s vibro-acoustic dynamics model is established based on statistical energy analysis (SEA) theory. By using theory analytical method and the empirical formula to determine the input parameters of each subsystem, setting the actual noise test conditions as the input incentives of the SEA model, the aircraft cabin’s noise pressure level and the vibration acceleration response of the subsystems are predicted, and compared to the test results. The results show that the acceleration power spectral density (PSD) of subsystem has a good consistency with the results of test in the middle and high frequency and the error of sound pressure level in cabin throughout the spectrum is less than 3 dB, so the dynamic model and calculation method is reliable and it solves the limitation of calculating the response of vibro-acoustic problems in middle and high frequency using the finite element and boundary element methods. The main source of the sound field in the cabin is found out by transfer path analysis. A method of the control and optimization design of noise based on the variable of loss factor is put forward, using the genetic algorithm to solve the optimization of the nonlinear constraint, and provides an effective means for study on aircraft structures and the complex dynamic environments and the optimization design of aircraft noise reduction.
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