Abstract
This paper looks at structural optimisation techniques applied to real aerospace vehicle shell systems, e.g. the fuselage of a commercial transport aircraft. The objective of this study was to determine the effectiveness of a commercially available, gradient-based structural optimisation tool to minimise the weight of an advanced polymer matrix composite (PMC) honeycomb sandwich barrel representing a fuselage section of a future high speed civil transport. The finite element method using MSC/NASTRAN was chosen for the structural analysis. The key contributions of this study are the demonstration of the application of state-of-the-art structural optimisation techniques to the sizing of a complex shell representative of a realistic vehicle fuselage structure and the lessons learned from this demonstration.
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