Simulation of Adhesive Bonding of a Fiber-Optic Rayleigh Sensor with Composite Material as Part of the Design of a Monitoring System

Abstract

Using fiber optic sensors in the aviation industry is a relevant and promising technology that can significantly improve the safety and efficiency of air travel. Fiber-optic sensors make it possible to warn of potential breakdowns, detect defects in the structure on time, reliably respond to their presence and give timely feedback during operation, which leads to real-time clarification of the state of the aircraft and the need for it to undergo convenient maintenance [1]. In aviation technology, polymer composite materials (PCM) are significantly increasing, in which fiber optic sensors are easily integrated [2]. Adhesive bonding plays a significant role in the durability of a sensor attached to or embedded in a PCM structure. Modelling the adhesive bond between a fiber optic sensor and a composite material makes it possible to determine the optimal physical and mechanical characteristics of the adhesive to increase the durability of the fiber optic sensor and thereby improve the quality of designing aircraft structures [3]. This paper presents the influence of various physical and mechanical properties of the adhesive on fatigue life to determine the optimal parameters for connecting an optical fiber to a composite panel. The results of computer simulation on the Simcenter software platform are presented, in which stresses, the number of cycles to failure that occur in an adhesive joint under various loads, and the physical and mechanical properties of the adhesive are calculated.