2.4 m连续式跨声速风洞大飞机精细化测力试验技术

张刃; 徐志福; 李小刚; 刘昱; 张颖; 杜文天

doi:10.7638/kqdlxxb-2023.0167

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2.4 m连续式跨声速风洞大飞机精细化测力试验技术

研究专栏——大飞机精细化与综合化风洞试验技术 | 更新时间：2026-05-28

- 2.4 m连续式跨声速风洞大飞机精细化测力试验技术
- Precision force measurement techniques for large aircraft models in 2.4 m continuous transonic wind tunnel
- 空气动力学学报 2023年41卷第12期页码：118-132
- 作者机构：
  
  1. 中国航空工业空气动力研究院,沈阳,110034
  2. 高速高雷诺数气动力航空科技重点实验室,沈阳,110034
- 作者简介：
  
  张刃（1985—），男，辽宁大连人，高级工程师，研究方向：试验空气动力学. E-mail： zr8526@163.com
  徐志福*（1988—），男，高级工程师，研究方向：试验空气动力学. E-mail： xuzhifu880423@163.com
- 基金信息：
  
  民机科研项目
- DOI：10.7638/kqdlxxb-2023.0167
  中图分类号： V211.74+1
- 纸质出版：2023
- 稿件说明：
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张刃, 徐志福, 李小刚, 等. 2.4 m连续式跨声速风洞大飞机精细化测力试验技术[J]. 空气动力学学报, 2023, 41(12): 118−132.

ZHANG Ren, XU Zhifu, LI Xiaogang, et al. Precision force measurement techniques for large aircraft models in 2.4 m continuous transonic wind tunnel[J]. 2023, 41(12): 118-132.
张刃, 徐志福, 李小刚, 等. 2.4 m连续式跨声速风洞大飞机精细化测力试验技术[J]. 空气动力学学报, 2023, 41(12): 118−132. DOI： 10.7638/kqdlxxb-2023.0167

ZHANG Ren, XU Zhifu, LI Xiaogang, et al. Precision force measurement techniques for large aircraft models in 2.4 m continuous transonic wind tunnel[J]. 2023, 41(12): 118-132. DOI： 10.7638/kqdlxxb-2023.0167.

摘要

为满足大飞机研制对风洞测力试验数据精准度的需求，并适应2.4 m连续式跨声速风洞运行特点，中国航空工业空气动力研究院成功研发了多项精细化的测力试验技术。这些技术中，低热膨胀系数高强度天平和天平温度效应补偿与修正技术有效地减小了温度变化对天平数据的影响；角度传感器和视频相结合的直接测量方法与改进后的角度叠加测量方法，均提高了模型姿态角的测量精度；基于线性回归的天平初始载荷计算方法可以一次性获得各种试验状态下的天平初始载荷，并提高气动载荷计算的准确性；基于前后置减振器的主动振动抑制技术能降低模型振动对测量数据的干扰并拓宽迎角范围；弹性变形视频测量与CFD修正技术可以有效分离高雷诺数试验结果中的弹性变形对气动力的影响量。本文对这些试验技术的原理进行了详细介绍，并给出案例证明这些试验技术能够有效提高测力试验的精准度；与ETW 风洞的对比试验显示，大展弦比民机模型的升力系数偏差约0.002，阻力系数偏差约0.0002。

Abstract

To meet the stringent demand for the precision and accuracy in wind tunnel force testing of large aircraft models

Aerodynamics Research Institute of AVIC (Aviation Industry Corporation of China) has innovated several cutting-edge force measurement techniques tailored for the 2.4 m continuous transonic wind tunnel. These techniques include a high-strength and low-thermal-expansion-coefficient balance with the temperature compensation and correction

an attitude angle measurement method using angle sensors and video and a modified method for measuring the attitude angle superposition

a fast calculation method of the initial balance loads under various test conditions based on the linear regression

an active anti-vibration technique based on front and rear damping systems that broadens the range of attack angle

video measurement and CFD (Computational Fluid Dynamics) simulation integrated elastic deformation correction method that effectively isolates the effects of elastic deformation on the aerodynamic forces in high-Reynolds-number tests. This paper delves into the principles underlying these innovative testing techniques and demonstrates their efficacy through case studies. Compared to the European Transonic Windtunnel

our techniques have achieved remarkable improvements in accuracy

with deviations of lift and drag coefficients for a large aspect ratio civil aircraft model being only 0.002 and 0.0002

respectively. These advancements represent a significant step forward in ensuring the reliability and accuracy of wind tunnel testing for large aircraft models.

关键词

Keywords

references

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