Structural optimization of an aircraft pressure bulkhead

In this study, topological optimization and sizing analysis of an elastic solid aircraft component are performed. Topological optimization maintains optimum mass distribution, targeting design variable maximum or minimum while satisfying constraints on a design domain under predefined boundary conditions and loads. An evolutionary algorithm is developed for topological optimization. After development of algorithm, a program is coded using Visual Basic language. The program is designed to process simultaneously with MSC.PATRAN and MSC.NASTRAN. Developed program is run for an aircraft part, pressure bulkhead, and results are obtained. Besides sizing analysis is performed by using 2D FEM elements for same structural aircraft part. Therefore the two major content of engineering, FEM analysis and structural optimization with evolutionary algorithms are discussed on this study. The ESO method availability is to be utilized in a conceptual design of an aircraft component. The model obtained with structural optimization is to be compared with the existing design constructed by size analysis.According to outcome, for defined boundary conditions and constraints, the topological optimized pressure bulkhead model reveal more homogenized load distribution and weight reduction up to 25% compared with sizing optimized model.Evaluation of results reveals that topological optimization of an aircraft part by using evolutionary algorithm is applicable but some improvement actions can be done for future studies.Key Words : Topological optimization, structural optimization