飞行器表面测压试验设计及分区重构方法  

Experimental design and regional reconstruction method for wind tunnel pressure measurements on flight vehicles

作　　者：魏巍[1] 薛亦菲 林键[1] 程思野 张江[1] 陈星[1] WEI Wei;XUE Yifei;LIN Jian;CHENG Siye;ZHANG Jiang;CHEN Xing(China Academy of Aerospace Aerodynamics,Beijing 100074,China;Chinese Aeronautical Establishment,Beijing 100029,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]中国航空研究院,北京100029

出　　处：《空气动力学学报》2024年第11期63-74,I0002,共13页Acta Aerodynamica Sinica

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。首先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。其次,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结果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具有重要意义。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%。本文提出的方法和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。This paper introduces an a priori-embedded framework for the design of experiments and regional reconstruction in wind tunnel pressure testing for flight vehicles.We propose an experimental design methodology that integrates prior information,enabling a quantitative translation of prior knowledge to pressure design sites.This approach encompasses the extraction of features from prior pressure distributions,a clustering process for multiple scenarios,and an optimization strategy for the uniformity of triangular facets in the initial design.To capture variations in local pressure distributions,we introduce a proper orthogonal decomposition(POD)-based reconstruction technique that aligns the number of base modal shapes with the number of design sites.Evaluations on a typical high-speed aircraft demonstrate a mean reconstruction error of less than 0.2%,a root mean square error below 4%,and a maximum error not exceeding 30%.The consistent reconstruction performance across various cases is significant for the accurate determination of the lift curve slope.The incorporation of a priori-embedded design further refines the maximum error reduction by 0~10%.The framework requires only numerical outcomes and minimal empirical parameters,rendering it well-suited for complex configuration flight vehicles in pressure measurement testing.

关 键 词：试验设计 数据重构 测压 风洞试验 融合先验信息 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]