飞行器表面测压试验设计及分区重构方法

Design of experiment and regional reconstruction of Wind Tunnel Pressure Test

  • 摘要: 针对飞行器多工况风洞测压试验的试验设计及重构问题,提出了一种融合先验信息的测压试验设计及重构方法框架。发展了先验信息的提取方法、基于聚类方法的试验设计和基于面元均匀性的优化方法,建立了先验信息与试验设计的定量关联,形成融合先验信息的测压试验设计方法。针对表面压力各部分分布特性的显著差异,基于POD方法发展了匹配先验信息基模态与测点数量的分区化重构方法,对典型高速飞机构型的测试显示重构均值误差小于0.2%、均方根误差小于4%、最大误差小于30%,且各工况重构性能基本一致。多工况重构特性一致对升力线斜率等关键参数的意义较大。采用融合先验信息的试验设计可进一步提高重构精度,不同工况下的最大误差可降低0~10%。融合先验信息的测压试验设计及重构方法框架输入仅包含数值结果及少量经验超参数,依赖人工经验的程度较低,降低了测压试验设计和重构难度,适用于复杂构型飞行器。

     

    Abstract: A priori-embedded design of experiment and reconstruction frame is proposed for the pressure measurement of flight vehicle in the wind tunnel pressure test. An design of experiment method integrating prior information is put forward to quantitatively transfer the prior to pressure design sites. It contains feature extraction method of prior pressure distribution, clustering process of multiple cases, and the optimization of triangular panel uniformity of the initial design. In order to model the difference among the local pressure distributions, a reconstruction method based on POD, which balances the number of base modal and design sites, is proposed. Test on a typical high-speed plane shows that the mean reconstruction error is less than 0.2% and the root mean square error is less than 4%, while the maximum error is less than 30%. Reconstruction performance under multiple cases behave similar, which is meaningful for the lift curve slope. With priori-embedded design, the maximum error could be further imporved with a decrease of 0-10%. Input of this frame contains numerical results and few empirical parameters, which is suitable for pressure measurement tests of flight vehicles with complex configuration.

     

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