Analysis of curing deformation for resin matrix composite T-shaped stiffened panel

Abstract

In this work, a multi-field coupled finite element simulation method involving thermochemistry and mechanics was devised to predict the curing deformation (C-DE) of a T-shaped stiffened panel (T-SSPL), a typical aircraft structural component, during the autoclave forming process. A more comprehensive and detailed analysis of the factors affecting the C-DE of T-SSPL is also carried out. The methodology uses the Fortran language to write different user subroutines and establish corresponding mathematical models to simulate the different mechanical states of components, and ultimately simulate the entire molding process of the product in the autoclave. And investigates the effects of process parameters, including heating rate, cooling rate, curing pressure, and structural parameters, including the number of bars and height of stringer on the C-DE of T-SSPL, and obtains the following conclusions: the heating rate and curing pressure are positively correlated with the C-DE, and the cooling rate has little influence on the C-DE, and C-DE hardly changes with the change of cooling rate; C-DE increases with the ribs count; however, it decreases and then increases with the stringer height, and these conclusions provides a theoretical basis for the manufacturing of T-SSPL.