Condition for the Growth of Adhesive Destruction during Cyclic Deformation of Carbon-Fiber Panels

Some aspects of the problem of adhesive fracture of aircraft panels made of composite materials under fatigue loading are considered. Algorithms of computer modeling of the delamination development process are described. Various methods of nondestructive testing for identifying the size and location of adhesive failure are analyzed. The cause of adhesion failure between anisotropic layers even under uniaxial tension is explained. The growth of delamination area under cyclic tension is described by an equation in the form of a power-law dependence on the range of the elastic energy release rate. For aircraft panels made of laminated carbon-fiber-reinforced plastics, the independence of the delamination growth rate from its current area is experimentally confirmed.