The prediction of crack initiation and propagation of damage initiation and propagation in composite structures has gained significant attention due to the increasing use of these materials in the aerospace industry. In this context, estimating progressive damage in composite ply is crucial, as it refers to the gradual failure and deformation of the structure, which can lead to a reduction in the useful life and safety of the structure. By examining these damages, it is possible to identify the causes and factors contributing to their occurrence and to propose suitable solutions for preventing and repairing the damages. In the present study, an effort is made to develop numerical, analytical, and experimental approaches for modeling and estimating progressive damage at mechanical joints in composite aircraft structures, considering quasi-static loading, including tensile loading. The study incorporates an investigation of damage mechanisms such as fiber breakage, matrix cracking, and delamination that commonly occur in composite laminates under mechanical stress. Combining modeling and experimental results allows for a comprehensive understanding of damage evolution, enabling the formulation of strategies aimed at improving the durability and safety of composite structures in aerospace applications. Ultimately, based on the results of modeling and experiments, strategies will be proposed to enhance the lifespan of the structure.