In-flight and wireless damage detection in a UAV composite wing using fiber optic sensors and strain field pattern recognition

Joham Alvarez-Montoya, Alejandro Carvajal-Castrillón, Julián Sierra-Pérez

    Research output: Contribution to journalArticlepeer-review

    35 Scopus citations

    Abstract

    Aiming to provide more efficient, lightweight structures, composite materials are being extensively used in aerospace vehicles. As the failure mechanisms of these materials are complex, damage detection becomes challenging, requiring advanced techniques for assessing structural integrity and maintaining aircraft safety. In this context, Structural Health Monitoring (SHM) seeks for integrating sensors into the structures in a way that Nondestructive Testing (NDT) is implemented continuously. One promising approach is to use Fiber Optic Sensors (FOS) to acquire strain signals, taking advantages of their capabilities over conventional sensors. Despite several works have developed Health and Usage Monitoring Systems (HUMS) using FOS for performing in-flight SHM in aircraft structures, automatic damage detection using the acquired signals has not been achieved in a robust way against environmental and operational variability, in all flight stages or considering different types of damages. In this work, a HUMS was developed and implemented in an Unmanned Aerial Vehicle (UAV) based on 20 Fiber Bragg Gratings (FBGs) embedded into the composite front spar of the aircraft's wing, a miniaturized data acquisition subsystem for gathering strain signals and a wireless transmission subsystem for remote sensing. The HUMS was tested in 16 flights, six of them were carried out with the pristine structure and the remaining after inducing different artificial damages. The in-flight data were used to validate a previously developed damage detection methodology based on strain field pattern recognition, or strain mapping, which utilizes machine learning algorithms, specifically a Self-Organizing Map (SOM)-based procedure for clustering operational conditions and Principal Component Analysis (PCA) in conjunction with damage indices for final classification. The performance of the damage detection demonstrated a highest accuracy of 0.981 and a highest F1 score of 0.978. As a main contribution, this work implements in-flight strain monitoring, remote sensing and automatic damage detection in an operating composite aircraft structure.

    Original languageEnglish
    Article number106526
    JournalMechanical Systems and Signal Processing
    Volume136
    DOIs
    StatePublished - Feb 2020

    Bibliographical note

    Funding Information:
    The authors are thankful to the Centro de Investigación para el Desarrollo y la Innovación (CIDI) at Universidad Pontificia Bolivariana for funding this project with internal settlement number 636B-06/16–57. Additionally, special thanks to Ae.Eng. Alex López-Ríos from Aircomposites for his invaluable contributions to the UAV design and manufacturing. The authors sincerely appreciate the support given by MSc. Jorge Iván García-Sepúlveda and Ae.Eng. Juan Pablo Alvarado-Perilla, and the wise advice provided by Dr. Leonardo Betancur-Agudelo in the field of wireless data transmission and Dr. Ferney Amaya-Fernández in the field of photonic sensing.

    Publisher Copyright:
    © 2019

    Keywords

    • Aerospace structures
    • Composite materials
    • Damage detection
    • Machine learning
    • Remote sensing
    • Structural health monitoring

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