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为实现吸气式高超声速飞行器多参数情况下的灵敏度分析及参数分类,降低设计的复杂度,在吸气式高超声速飞行器参数化建模的基础上,首先采用正交试验设计生成样本,再通过计算流体力学(CFD)进行高精度气动力性能计算,最后运用方差分析法进行气动性能的参数灵敏度分析,在运用较少的试验样本点的情况下,即可完成多参数、复杂构型条件下气动性能的参数灵敏度分析。结果表明,该方法可以正确地分析出参数对飞行器气动性能的敏感程度,得到参数对气动性能的影响规律。同时,通过灵敏度分析的计算样本,还可以初步选出气动性能较优的飞行器构型,为地面试验和优化设计提供参考。
In order to realize the sensitivity analysis and parameter classification under the multiple parameters of the aspirated hypersonic vehicle and reduce the complexity of the design, based on the parametric modeling of the aspirated hypersonic vehicle, the samples are generated by using the orthogonal experiment design first, and then Through computational fluid dynamics (CFD) for high-precision aerodynamic performance calculations, and finally the use of analysis of variance aerodynamic parameters of the sensitivity analysis, the use of fewer test sample points, you can complete the multi-parameter, complex configuration conditions Parameter Sensitivity Analysis of Aerodynamic Performance. The results show that this method can correctly analyze the sensitivity of the parameters to the aerodynamic performance of the aircraft and get the law of the influence of the parameters on the aerodynamic performance. At the same time, through the sensitivity analysis of the sample calculation, the aircraft configuration with better aerodynamic performance can also be preliminarily selected, which can provide reference for the ground test and optimization design.