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Abstract
Structural health monitoring is of great importance for the application of composites in aircrafts. Fiber Bragg grating (FBG) sensors are very suitable for structure strain measurement. However, the strain measured by FBG sensors is different from the original strain in host materials. The relationship between them is defined as strain transfer. As composites are anisotropic, the traditional strain transfer model, which regards the elasticity modulus of host materials as a constant, is inadaptable. In this paper, a new strain transfer model is proposed for FBG sensors bonded to the surface of carbon fiber reinforced polymer (CFRP) laminates. Based on the measurement structure, the model is established and the transfer function is derived. The characteristics influencing the strain transfer are analyzed. The stacking directions, stacking numbers, and stacking sequences of CFRP laminates have a distinct effect on the transfer efficiency, which is different from the isotropy host materials. The accuracy of the proposed model was verified by experiments on a nondestructive tensile system, and the maximum model error is less than 0.5%. Moreover, the model was applied to the strain measurement of CFRP wing skin, which indicates that measurement errors decrease by 11.6% to 19.8% after the compensation according to the model.
Highlights
The composite laminates have extraordinary mechanical properties such as high strength, light weight, strong corrosion resistance and low temperature distortion [1]
Since the thermal expansion coefficients of silica core, transfer ratio by changing since the expansion coefficients of coating, adhesive layer, the andelastic laminatesBesides, are different, thethermal temperature changes can generate silica core, coating, layer, and carbon fiber reinforced polymer (CFRP) laminates arecause different, the temperature can residual stress in adhesive the measurement structure, which will the distortion of Fiber Bragg grating (FBG) changes sensor spectra generate stress the measurement which cause the distortion of FBG sensor
The measurement structure was abstracted into the silica core, coating, adhesive layer, layer, andlaminates, CFRP laminates, and the CFRP laminates were as regarded as an anisotropic multilayered and and the CFRP
Summary
The composite laminates have extraordinary mechanical properties such as high strength, light weight, strong corrosion resistance and low temperature distortion [1]. When axial strain is applied to the optical fiber, the wavelength shift of the FBG sensor, represented by. For the FBG sensor under both temperature and strain changes, the overall shift of Bragg wavelength is given by the summation of the two effects [19] as follows:. The strain of the host material is transferred to the adhesive layer, which leads to the deformation of the FBG sensor wrapped inside. The strain measured by FBG sensors is different fromREVIEW the original strain in the host material [25]. Li Sun [28] conducted a strain transfer analysis of a clamped fiber Bragg grating sensor. The strain model transferismodel is established and the function transfer is function
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