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.


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    Title :

    Optimal sizing of a composite sandwich fuselage component


    Additional title:

    Optimierungsverfahren für Sandwich-Rumpfkomponenten kommerzieller Transportflugzeuge


    Contributors:
    Ley, R. (author) / Peltier, A. (author)

    Published in:

    Publication date :

    2001


    Size :

    26 Seiten, 21 Bilder, 8 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Optimal sizing of a composite sandwich fuselage component

    Ley,R. / Peltier,A. / Northrop Grumman,US | Automotive engineering | 2001


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