In-Flight Strain Monitoring of Aircraft Tail Boom Structure Using a Fiber Bragg Grating Sensor Based Health and Usage Mo
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ORIGINAL PAPER
In-Flight Strain Monitoring of Aircraft Tail Boom Structure Using a Fiber Bragg Grating Sensor Based Health and Usage Monitoring System Hyunseok Kwon1 · Yurim Park1 · Changkyo Shin1 · Jin-Hyuk Kim2 · Chun-Gon Kim1 Received: 18 May 2020 / Revised: 27 August 2020 / Accepted: 14 September 2020 © The Korean Society for Aeronautical & Space Sciences 2020
Abstract 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. Keywords Health and usage monitoring system · In-flight strain measurement · Fiber Bragg grating sensor · Flight demonstration · Tail boom structure
1 Introduction With increasing demand for air transportation, which is fast and convenient, demand for high performance aircrafts with large capacities and high fuel efficiency is also increasing. Since composite materials, which have high specific stiffness and high specific strength, provide advantages for light weight design, the percentage of composite materials in aircraft design is rapidly increasing. However, since composite materials have unique damage and failure characteristics compared to conventional metallic materials, continuous and thorough monitoring of composite aircraft during operation is necessary [1]. Research on heath and usage monitoring systems (HUMS) enables pilots and maintenance engineers to maintain the air-
B
Chun-Gon Kim [email protected]
1
Department of Aerospace Engineering, KAIST, 291, Daehak-ro, Yuseong-gu, Daejeon, Republic of Korea
2
Korea Aerospace Research Institute, 169-84, Gwahak-ro, Yuseong-gu, Daejeon, Republic of Korea
craft based on the condition of the aircraft by measuring and analyzing structural events that occur during its operation [2]. Therefore, to assure the reliability and safety of the aircraft, development of HUMS for aircrafts is being actively conducted using various sensors. In-flight
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