飞行器表面测压试验设计及分区重构方法

魏巍; 薛亦菲; 林键; 程思野; 张江; 陈星

doi:10.7638/kqdlxxb-2023.0222

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飞行器表面测压试验设计及分区重构方法

研究论文 | 更新时间：2026-07-27

- 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
- 空气动力学学报 2024年42卷第11期页码：63-74
- 作者机构：
  
  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
- 作者简介：
  
  魏巍*（1989—），男，博士，河南人，高级工程师，研究方向：空气动力学. E-mail：weiweicaaa@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0222
  中图分类号： V211.74
- 纸质出版：2024
- 稿件说明：
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魏巍, 薛亦菲, 林键, 等. 飞行器表面测压试验设计及分区重构方法[J]. 空气动力学学报, 2024, 42(11): 63−74.

WEI Wei, XUE Yifei, LIN Jian, et al. Experimental design and regional reconstruction method for wind tunnel pressure measurements on flight vehicles[J]. 2024, 42(11): 63-74.
魏巍, 薛亦菲, 林键, 等. 飞行器表面测压试验设计及分区重构方法[J]. 空气动力学学报, 2024, 42(11): 63−74. DOI： 10.7638/kqdlxxb-2023.0222

WEI Wei, XUE Yifei, LIN Jian, et al. Experimental design and regional reconstruction method for wind tunnel pressure measurements on flight vehicles[J]. 2024, 42(11): 63-74. DOI： 10.7638/kqdlxxb-2023.0222.

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。

Abstract

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.

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references

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