Abstract
Because of the advantages of lightweight and high-strength integrated molding of composite materials at low cost, thus, large-scale carbon fiber composite structures are widely used in aerospace applications. However, the curing deformation of large-scale composite structures will produce a certain shape deviation, which cannot meet the needs of the installation. If forced assembly will form large installation stress, which will seriously jeopardize the mechanical properties and lifetime of the composite parts. Therefore, it is being studied to control the curing deformation of largescale composite structures, which is important to ensure the quality of the structure, reduce the cost and improve the service life of the structure. The traditional composite parts development model requires large-scale sample testing, uncontrollable manufacturing quality, low efficiency, and other problems. In particular, the curing and molding process involves the intersection of several disciplines such as thermal, chemical and mechanics, so it is increasingly important to study the curing deformation of large-scale composite structures to improve R&D efficiency, control quality, and reduce cost.
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