Damage distribution of composite structures of a certain type of aircraft

Aiming at the damage and repair of aircraft composite structures, the applications and damage of composite structures in a certain type of aircraft, including the wing, fuselage and other components, were counted. Solid laminates (integral panels) and sandwich laminates are typical composite structural forms in the aircraft. Structural damage distribution models with time variable were established, and then the damage distributions of the structures were fitted and tested by structural methods. The results show that the quantitative proportions of damage are 75% for skin delamination, 20% for stringer delamination and 4% for stringer debonding. Lognormal distribution, Weibull distribution and Gamma distribution can all be used to fit the geometric parameter distributions of the three types of structural damage, in which the Lognormal distribution model has the best fitting effect. The distribution of structural damage geometric parameters of one aircraft does not vary with time, and the distributions of geometric parameters of the structural damage between the same type aircraft are also highly similar, which can be expressed in a unified function form.