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Structural Health Monitoring-Based Methodologies for Managing Uncertainty in Aircraft Structural Life Assessment

机译:基于结构健康监测的飞机结构寿命评估不确定性管理方法

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The uncertainty inherent in most aircraft structural maintenance methodologiesnecessitates inspection intervals, which are established based on either assumed levelsof damage or the results of fatigue tests. Maintenance approaches that rely on onlyscheduled inspections have an intrinsic amount of uncertainty and risk becauseintervals do not reflect the loading and damage history of each specific aircraft. Thisrisk is more pronounced in composite aircraft, because damage is often not visuallyapparent. Human factors in labor-intensive inspections make this damage easy to misswhen performing tedious inspections of the entire aircraft [2].This work presents two case studies of structural health monitoring (SHM)methods that are designed to reduce the risk in aircraft maintenance, as well as the costof frequent, lengthy inspections. The first is an impact identification system which iscapable of locating impacts to a full-scale fuselage using only three sensors. Thisimpact identification method is able to quantify the severity of impacts as well,allowing maintenance personnel to focus inspections on areas that have sustainedfrequent and/or high amplitude impacts. Using this method, over 97% of impacts to aheavy lift helicopter fuselage are located within 9 inches of the true impact location.The second case study details the development of a non-contact wide area inspectionmethod which has the potential to reduce inspection times and uncertainty ascompared to labor-intensive inspection methods such as coin tap testing. Thisinspection method exploits the nonlinear forced vibration characteristics of damagedareas through surface velocity measurements acquired by a scanning laser vibrometer.By comparing the structure’s response to forcing functions of differing magnitudes,the local nonlinear characteristics of damage are identified. This automated inspectionmethod is shown to be effective in locating subsurface damage in composite helicopterpanels, and has the potential to reduce both labor costs and damage detectionuncertainty.
机译:大多数飞机结构维护方法中固有的不确定性 需要检查间隔,该间隔基于任一假定水平确定 损坏或疲劳测试的结果。仅依赖于维护的方法 定期检查具有内在的不确定性和风险,因为 间隔不会反映每架特定飞机的载荷和损坏历史记录。这 复合飞机中的风险更为明显,因为损坏通常不是肉眼可见的 明显的。劳动密集型检查中的人为因素使这种损坏很容易被忽略 对整个飞机进行乏味的检查[2]。 这项工作提出了结构健康监测(SHM)的两个案例研究 旨在降低飞机维护风险以及成本的方法 频繁,冗长的检查。第一个是影响识别系统,它是 仅使用三个传感器就可以将撞击物定位到全尺寸机身上。这 影响识别方法也可以量化影响的严重性, 允许维护人员将检查重点放在持续的区域 频繁和/或高振幅的影响。使用此方法,对某人的影响超过97% 重型直升机的机身位于真正撞击位置的9英寸以内。 第二个案例研究详细介绍了非接触式广域检测的发展 有可能减少检查时间和不确定性的方法 与劳动密集型检查方法(如硬币抽头测试)相比。这 检测方法利用了损伤的非线性强迫振动特性。 通过扫描激光振动计获取的表面速度测量结果来确定区域。 通过比较结构对不同大小的强制功能的响应, 确定损伤的局部非线性特征。这种自动检查 结果表明该方法可有效地定位复合直升机的地下损伤 面板,并有可能减少人工成本和损坏检测 不确定。

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