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Use of FBG Sensors for SHM in aerospace structures

Photonic Sensors 2012年第3期2卷 203-214页

作者： Gayan C. KAHANDAWA Jayantha EPAARACHCHI Hao WANG K. T. LAU Centre of Excellence in Engineered Fibre Composites University of Southern Queensland Toowoomba 4350Queensland Australia

This paper details some significant findings on the use of the fiber Bragg grating （FBG） sensors for structural health monitoring （SHM） in aerospace fiber reinforced polymer （FRP） structures. A diminutive sensor provides a capability of imbedding inside FRP structures to monitor vital locations of damage. Some practical problems associated with the implementation of FBG based SHM systems in the aerospace FRP structures such as the difficulty of embedding FBG sensors during the manufacturing process and interrelation of distortion to FBG spectra due to internal damage, and other independent effects will be thoroughly studied. An innovative method to interpret FBG signals for identifying damage inside the structures will also be discussed.

关键词： Structural health monitoring aerospace structures fiber Bragg grating sensors

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Structural aerospace Composite/Metallic Samples under Fatigue Loads： Experimental Activity on Three Case Studies

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Journal of Mechanics Engineering and Automation 2014年第4期4卷 318-326页

作者： Giacomo Frulla Giulio Romeo Department of Mechanical and aerospace Engineering Politecnico di Torino Torino 10129 Italy

The use of composite materials in aerospace engineering is ever increasing. Properties such as low weight, high performance, high stiffness and the ability for it to be tailored specifically for different structural uses has increased its importance in recent years. Specific experimental/numerical activities were developed in the last decade at the aerospace department of Polito and are under consideration in recent years regarding the analysis of fatigue behavior of composite/metallic structural samples under cyclic loading condition. A review of the main significant results connected to three case-studies is presented in the paper. The first is related to the definition and analysis of innovative joint for composite high aspect ratio aircraft structures. The modular design oriented to limit component dimensions for transportability requires the presence of a removable joints able to overcome the typical low bearing failure level of composite pin-loaded joint under static and fatigue loading distribution according to airworthiness requirements. The static experiments demonstrate the consistency of the proposed advanced joint configuration that postpones the joint failure to high load level according to the structural requirements. The cyclic loading phase takes as reference point the failure load of the initial configuration and defines a loading cycle with a maximum higher than the failure load of the initial configuration. The fatigue behavior of the advanced joint also demonstrates a substantial consistency with expected duration of 1 e6 cycles as required by the structural design for operating reasons. Specific indication on fatigue limit with respect to critical amplitude is reported. The second is related to the presence of specific damaged situation in thin-walled fiat/stiffened composite plate. Stiffened configurations are frequently used to increase buckling load level. Unexpected events on solid/stiffened composite panels can introduce a certain level of

关键词： aerospace structures composites fatigue corrosion experimental activity.

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