0

Full Content is available to subscribers

Subscribe/Learn More  >

A Design Approach of a Fuselage Barrel in Grid Structure

[+] Author Affiliations
Giuseppe Gatta, Fulvio Romano

CIRA – Italian Aerospace Research Centre, Capua, Italy

Paper No. DETC2005-84166, pp. 627-634; 8 pages
doi:10.1115/DETC2005-84166
From:
  • ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference
  • Volume 4c: 18th Reliability, Stress Analysis, and Failure Prevention Conference
  • Long Beach, California, USA, September 24–28, 2005
  • Conference Sponsors: Design Engineering Division and Computers and Information in Engineering Division
  • ISBN: 0-7918-4741-1 | eISBN: 0-7918-3766-1
  • Copyright © 2005 by ASME

abstract

In this paper a design method of a cylindrical fuselage barrel in grid structure to fabricate in composite material is illustrated. The approach can be divided in two phases. In the first step, a lattice structure, that is a grid structure with ribs only and without a skin, is sized thanks to an analytical approach. The independent variables to optimize are five: number of helical ribs, number of circumferential ribs, rib height, circumferential rib thickness, helical rib thickness. Some geometric constraints on the dimensions of the ribs are introduced. The best lattice structure is individuated by an analytical theory due to professor Vasiliev of the Central Research Institute of Special Machine Building (CRISM), the leading Russian Composite Center. The theory is based on the calculation of four safety factors for the helical rib strength, axisymmetric global buckling, non axisymmetric global buckling and the helical rib local buckling. Successively, a finite element analysis is performed in order to verify the analytical results. A software tool developed in Matlab environment prepares the finite element model, runs the finite element solver (MSC/Nastran) and reads the results. In the second step, an outer skin is added and the best lay-up for it is chosen; the maximum failure index for the skin laminate is calculated too. At the end the structure with the minimum weight and all margins of safety positive is individuated. The skin is extremely light so as to minimize overall weight. In the finite element model ribs and skin are simulated with beam and shell elements respectively; for the skin a common high-strength graphite/epoxy composite material is used, for the ribs an isotropic material with properties derived from experimental data. A grid-stiffened structure allows to reduce the structural mass of about 20% respect to a metallic reference baseline. Moreover, it can be quickly constructed by using filament winding technology; the process can be highly automated and the manufacturing costs can be reduced of the 30%.

Copyright © 2005 by ASME

Figures

Tables

Interactive Graphics

Video

Country-Specific Mortality and Growth Failure in Infancy and Yound Children and Association With Material Stature

Use interactive graphics and maps to view and sort country-specific infant and early dhildhood mortality and growth failure data and their association with maternal

NOTE:
Citing articles are presented as examples only. In non-demo SCM6 implementation, integration with CrossRef’s "Cited By" API will populate this tab (http://www.crossref.org/citedby.html).

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In