Abstract
The increasing utilization of carbon fiber reinforced plastic (CFRP) in the aeronautical industry calls for a structural health monitoring (SHM) system for adhesively bonded CFRP joints. Optical glass fiber with inscribed fiber Bragg gratings (FBGs) is a promising technology for a SHM system. This paper investigates the intrusive effect of embedding optical glass fibers carrying FBGs on adhesive bond strength and adhesive layer thickness and quality. Embedding the optical glass fibers directly in the adhesive bond has the advantage of directly monitoring the targeted structure but poses the risk of significantly reducing the bond strength. Optical glass fibers with different cladding diameters (50, 80, 125 µm) and coating types (polyimide, with a thickness of 3−8 µm, and acrylate, with a thickness of ~35 µm) are embedded in structural and repair film adhesives here. Without embedded optical glass fibers, the film adhesives have an adhesive layer thickness of ~90 µm (structural) and ~100 µm (repair) after curing. The intrusive effect of the fiber embedding on the adhesive bond strength is investigated here with quasi static and fatigue single lap joint (SLJ) tensile shear tests. Also, the influence of hydrothermal aging procedures on the quasi static tensile shear strength is investigated. It is found that optical glass fibers with a total diameter (glass fiber cladding + coating) of ~145 µm significantly reduce the quasi static tensile shear strength and increase the adhesive layer thickness and number of air inclusions (or pores) in the structural film adhesive joints. In the repair adhesive joints, no significant reduction of quasi static tensile shear strength is caused by the embedding of any of the tested fiber types and diameters. However, an increase in the adhesive layer thickness is detected. In both adhesive films, no effect on the quasi-static tensile shear strength is detected when embedding optical glass fibers with total diameters <100 µm. The applied aging regime only affects the repair film adhesive joints, and the structural film adhesive joints show no significant reduction. A polyimide-coated 80 µm optical glass fiber is selected for fatigue SLJ tensile shear tests in combination with the more sensitive structural film adhesive. No significant differences between the S-N curves and tensile shear fatigue strength of the reference samples without embedded optical fibers and the samples carrying the polyimide-coated 80 µm optical glass fibers are detected. Thus, it is concluded that the influences of embedding optical glass fibers with total diameters <100 µm on the fatigue limit of the tested film adhesive joints is negligible.
Highlights
The utilization of carbon fiber reinforced plastic (CFRP) in the aircraft construction industry hasThe utilization of carbon fiber reinforced plastic (CFRP) in the aircraft construction industry continuously increased in the past decade [1]
For FM® 300K adhesive bonds, the results indicate that embedding optical glass fibers with total diameters of ~145 μm causes a significant reduction in quasi-static tensile shear strength in comparison to the reference sample
Key Aspects for Selecting an Appropriate Optical Glass Fiber for structural health monitoring (SHM) Applications in FM® 300-2K and the results indicate that the tested FM® 300-2K repair film adhesive is more tolerant towards embedding different fiber diameters and coating types than the tested FM® 300K adhesive film, the same recommendations apply for both
Summary
The utilization of carbon fiber reinforced plastic (CFRP) in the aircraft construction industry has. The utilization of carbon fiber reinforced plastic (CFRP) in the aircraft construction industry continuously increased in the past decade [1]. Adhesive bonding is better suited for joining CFRP has continuously increased in the past decade [1]. Adhesive bonding is better suited for joining materials than conventional techniques like riveting or bolting [2,3]. Without a method for identifying the condition of an adhesive bond, industry sets high security standards. Without a method for identifying the condition of an adhesive airworthiness authorities will not approve adhesive bonding for primary aircraft structures [3]. A bond, airworthiness authorities will not approve adhesive bonding for primary aircraft structures [3]
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