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在实际飞行条件下的风洞测试期间,在飞机机翼中实时检测损坏

Yoav Ofir¹, Uri Ben-Simon¹, Shay Shoham¹

¹IAI Aviation Group, Ben Gurion International Airport, Lod 7010000, Israel.

Sensors (Basel, Switzerland)

|July 30, 2025

概括

飞机复合机翼的新型结构健康监测 (SHM) 系统使用纤维支架格子 (FBG) 传感器和可调节的紧固件来评估损坏. 该系统成功地使用风洞测试中的Q测量方法识别了损害的发起和程度.

科学领域:

航空航天工程航空航天工程
材料科学材料科学材料科学
机械工程机械工程

背景情况:

复合材料飞机机翼易受损坏,影响结构完整性.
实时结构健康监测 (SHM) 对航空安全至关重要.
现有的监测系统可能缺乏适应可变损坏场景的适应性.

研究的目的:

开发和测试可调节损坏的复合飞机机翼实时SHM系统.
评估系统在现实的飞行条件下监测损坏的能力.
评估不同数据分析技术对损坏检测的有效性.

主要方法:

一个基于FBG的传感器阵列被实施用于监测一个复合机翼中的脱节区域.
使用可锁定紧固件来调整损坏严重程度,模拟可调节的损坏.
主要组件分析 (PCA),Hotelling的T平方和Q测量用于实时数据分析.
测试是在工业风洞中在受控条件下进行的.

主要成果:

SHM系统成功识别了损坏的开始和程度.
在检测损害方面,Q测量被证明是有效的,其表现优于T平方测量.
该系统展示了基于预定义的标准将结构性健康状况归类为正常或异常的能力.

结论:

开发的实时SHM系统具有可调节的损坏,有效监控复合机翼.
"Q测量"是检测和量化航空航天结构损坏的有希望的工具.
这种方法提供了一种可控制和可重复的方法,用于在模拟飞行条件下评估SHM系统的性能.

关键词:

这就是SHM SHM.复合机翼的复合机翼.检测损坏检测损坏的检测.纤维光学传感传感器实时处理实时处理.结构健康监测结构健康监测风洞测试风洞测试风洞测试

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