This paper presents an experimental investigation of sensor system for monitoring of ultralight aircraft wing. Fiber Bragg Grating (FBG) sensors were chosen as a suitable strain sensors for integration into the composite structural parts. At first, influence of embedded optical fibers on an adhesive joint performance was evaluated, using the single-lap bonded joint specimens. In the next step, FBG sensors were integrated into the load bearing parts of cantilever wing beam and tested during the ground static strength test of the complete wing.
doi: 10.12783/SHM2015/208