Abstract
This paper presents the concept of application of fibre Bragg grating (FBG) sensors forstructural health monitoring (SHM) of an adaptive wing. In this concept, theshape of the wing is controlled and altered due to the wing design and the use ofintegrated shape memory alloy (SMA) actuators. FBG sensors are great toolsfor controlling the condition of composite structures due to their immunity toelectromagnetic fields as well as their small size and weight. They can be mounted ontothe surface or embedded into the wing skin without any significant influence onthe wing strength. In the first part of the paper a determination of the twistingmoments produced by activation of the SMA actuators is presented. As a firststep, a numerical analysis using a finite element method (FEM) commercial codeABAQUS® is presented. Then a comparison between strain values measured by FBG sensors anddetermined numerically is used for determination of the real value of the activationmoment of every SMA actuator. Two types of damage scenarios are analysed anddiscussed in the paper. The first scenario is reduction of the twisting moment valuesproduced by one of the SMA actuators. The second scenario is outer skin damage.In both damage scenarios, a neural network is used for damage detection andlocalization.
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