Multi-level Integrated Structural Sizing
Of A Composite Sandwich Wing
Author(s)
F. Romano, G. Gatta & M. Pecora
Abstract
In this work a procedure for the structural sizing of a composite sandwich wing
is described. The procedure is named MLISS (Multi-Level Integrated Structural
Sizing); it foresees three growing levels of detailed design and integrates the
features of different analysis tools: in-house codes written in Matlab and Fortran
languages, a commercial structural sizing software and a finite element software.
The wing skin is devised in composite honeycomb-core sandwich panels
while the spar webs and the caps in solid laminate; MLISS sizes the structure
using the external loads determined by an in-house code developed for the
aeroelastic analyses (AEDC).
In the first level, the wing is considered as concentrated elements: the skin is
sized by bending and torsion; the spar webs and the caps by torsion and bending
respectively. The skin carries only the in-plane and bending loads; no transverse
shear effect is considered (the core thickness is zero): the skin panels are
simulated in solid laminate of thickness two times the thickness of a single
sandwich face. Elementary theories are applied to determine the internal loads
acting on the different structural wing components. In the second level, the
internal loads are used to update the wing sizing. The contribution of the
honeycomb core for the skin panels is now considered and its optimal thickness
is evaluated. In the third level the finite element model is built; the internal FEA
loads are evaluated to size definitively the structure by an iterative approach.
Applied to a high aspect ratio wing, MLISS has produced satisfying results;
moreover the structural weight obtained in the first level is not far from that one
obtained in the third level: so for a fast preliminary weight estimation of a
composite sandwich wing, only the first sizing level can be applied.
Keywords: wing, structural sizing, honeycomb-core sandwich panels,
multi-level, integrated, composite material.
Keywords
wing, structural sizing, honeycomb-core sandwich panels,
multi-level, integrated, composite material.
Related Book
Other papers in this volume
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