With the increased use of composite materials in aircraft structures, continuous and thorough monitoring of structural conditions is highly required for the assurance of safety and reliability. In this study, as part of the fiber Bragg grating (FBG) sensor-based aircraft health and usage monitoring system (HUMS) development research, in-flight strain monitoring of an aircraft tail boom structure using the FBG sensor-based aircraft HUMS was investigated. The FBG sensor-based aircraft HUMS was implemented to the tail boom structure of an ultralight propeller composite aircraft. Flight tests of the testbed aircraft were performed, and in-flight strain variations of the tail boom structure were measured using the implemented system. For in-flight strain variation data-based verification through comparative analysis with flight parameters, the in-flight strain variations of the tail boom structure were analyzed with the flight parameters for various flight conditions. As a result, the HUMS operated as expected during the actual flights, and the acquired in-flight strain variations corresponded adequately in relation to the loading conditions during flight, such as bending loads due to the use of control surfaces and ground impacts during landing procedures.

中文翻译：

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使用基于光纤布拉格光栅传感器的健康和使用监测系统对飞机尾梁结构进行飞行中应变监测

随着复合材料在飞机结构中的使用越来越多，为了确保安全性和可靠性，非常需要对结构条件进行持续和彻底的监测。在这项研究中，作为基于光纤布拉格光栅 (FBG) 传感器的飞机健康和使用监测系统 (HUMS) 开发研究的一部分，研究了使用基于光纤布拉格光栅 (FBG) 传感器的飞机 HUMS 对飞机尾梁结构进行飞行应变监测. 基于 FBG 传感器的飞机 HUMS 已应用于超轻型螺旋桨复合材料飞机的尾梁结构。对试验台飞机进行了飞行测试，并使用实施的系统测量了尾梁结构的飞行应变变化。通过与飞行参数的对比分析，进行基于飞行应变变化数据的验证，结合各种飞行条件下的飞行参数，分析了尾梁结构在飞行中的应变变化。结果，HUMS 在实际飞行期间按预期运行，并且获得的飞行中应变变化与飞行期间的载荷条件充分对应，例如由于使用控制面和着陆过程中的地面撞击引起的弯曲载荷.