This paper looks at structural optimization 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 optimization tool to minimize 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 optimization techniques to the sizing of a complex shell representative of a realistic vehicle fuselage structure and the lessons learned from this demonstration.
Optimal sizing of a composite sandwich fuselage component
Optimierungsverfahren für Sandwich-Rumpfkomponenten kommerzieller Transportflugzeuge
International Journal of Vehicle Design ; 25 , 1/2 ; 89-114
2001
26 Seiten, 21 Bilder, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
Optimal sizing of a composite sandwich fuselage component
Online Contents | 2001
|Optimal sizing of a composite sandwich fuselage component
Kraftfahrwesen | 2001
|