<p>Composites are widely utilized in the aerospace industry due to their high strength-to-weight ratio and improved fatigue resistance compared to conventional materials. These materials are manufactured by combining fibers, such as carbon, with resin, and their mechanical properties vary depending on the fiber volume fraction of these components, which can lead to deformation. In aerospace applications, where high precision and quality are required, composites are typically processed using autoclave molding. During the curing cycle, heating and cooling conditions are determined by the properties of the resin, and residual stresses develop due to thermal expansion, chemical shrinkage, and curing. These residual stresses significantly affect the dimensional accuracy and mechanical performance of components, often leading to warpage. Such deformations pose challenges in the fabrication of composite parts or structures, ultimately increasing production time and costs. Accurately predicting these phenomena would contribute to improving the manufacturing process of composite components. This study aims to predict deformation induced by residual stresses during the autoclave process using a structural analysis program. This analysis incorporates changes in material properties caused by thermal expansion, chemical shrinkage, and curing, as well as the effects of viscoelasticity and fiber volume fraction, which may vary for each laminate. By integrating these factors into the structural analysis model, this research seeks to enhance the accuracy of deformation predictions. The results of the study showed that greater deformation occurred during the cooling process compared to conventional analysis methods that consider only the coefficient of thermal expansion. It was also found that incorporating these factors plays an important role in improving the accuracy of structural analysis.</p>