Optimization of an aircraft vertical tail cross-section by genetic algorithm

In this study, structural design, structural analysis and structural optimization by genetic algorithm (GA) method are studied for vertical tail section of a two seated trainer aircraft with single turboprop engine. Weight minimization in aircraft structures is very important for both increasing aircraft performance (for ins. altitude and manoeuvre capabilities) and reducing costs. Therefore, the objective function considered in the optimization problem of study is the total weight of the structure. Finite element model of vertical tail is designed using MSC/PATRAN program and this program is used as pre and postprocessor to observe the results. After separating finite element model to sections, loads which effect to structural members in each section are determined and entered to model. Formulas based on common analysis approaches are entered to Microsoft Excel program and strength of each member are checked for initial and final values. Code written by MATLAB are used for GA optimization. Finite element analysis for initial and final values are implemented by using MSC/NASTRAN program and thus the results are rechecked.