In this thesis, downscaled composite wing box was manufactured, and structural behavior of wing box under bending was investigated by experiment and analysis. The wing box consists of upper and lower parts. The upper part was composed of a skin, two stiffeners, and two spars. The lower part was composed of a skin and two stiffeners. After cocuring these two parts respectively, each part was bonded by adhesive film.
Considering the loading condition and boundary conditions of the wing box, a test machine was manufactured for static tests of the wing box. The results of experiment show some difference locally from those of FEM results in the bucking load and bucking behavior of the skin and spars. But experimental results show good agreement with analytical results for the global structural behavior. Buckling modes of experiment in the upper skin were compared with those of FEM by shadow moire technique.
