Due to their nature, the design and optimization of fiber reinforced laminated composite material models can be a time consuming task. In this paper, by employing BETA CAE Systems’ ANSA / μETA pre and post processing suite, the optimum weight, and the angle of attack of a F1 front wing was determined in a two-step optimization approach.
First, using ANSA and NASTRAN’s SOL 200 Topometry Optimization, areas requiring reinforcement by increased thickness, were identified. Then, using the results from thickness distribution, the model was divided to areas on which composite material layers (plies) were distributed. A new optimization problem was set up using as design variables the ply orientation, the thickness and the size of each layer. The last design variable is important since the material orientation variation of each layer may alternate the former optimum solution. CFD analysis was performed in the optimization loop to achieve the minimum possible Drag coefficient while complying with the optimization constraints. Morphing action took place compensating for the deformations while special design variable constraints prevent non manufacturable solutions.