Optimization of the curing cycle for the large-scale composite stiffened panel based on the response surface methodology and Fgoalattain algorithm

The autoclave curing process of the large-scale composite stiffened panel greatly affects the manufacturing quality of the component, especially the curing quality of stiffeners and the bonding quality between stiffeners and the panel. In this paper, a multi-objective optimization method is developed to optimize the curing cycle for the composite T-stiffened fuselage panel, which aims to minimize the temperature difference within the component to achieve better forming quality. The autoclave curing model considering thermal properties of composites is established and verified by the experiment first. The response surface models are then built up with the Finite Element Method (FEM) and the Box-Behnken Design (BBD). The fgoalattain algorithm is applied to solve the multi-objective optimization problem with nonlinear constraints. Results show that the maximum temperature difference of the two groups of monitoring points decreases by 22.91% and 21.42%, respectively. Besides, the total curing time is also reduced by 11 mins.