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Optimum design of composite stiffened wing panels — a parametric study

Published online by Cambridge University Press:  04 July 2016

R. Butler
R. Butler*
Affiliation:
School of Mechanical EngineeringUniversity of Bath, Bath, UK
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Abstract

The program VICONOPT is used to find the optimum (least mass) dimensions of a range of stiffened wing panels which are subject to buckling and material strength constraints and are loaded in axial compression with a sinusoidal manufacturing imperfection. Design plots are presented to show the effects that various rib spacings and stiffener types have on optimum design mass. A simplified model of a complete wing box is used to illustrate the design of a full wing panel and plots of optimum values of design variables at various stations along the wing have been obtained. The results were chosen to illustrate the practicality of optimisation with reference to manufacture of a full wing panel and to show the effect of changing the sophistication of modelling and theory used for the range of panels considered. The important aspects of the choice of design variables and design concepts are highlighted and percentage savings in mass, compared with an optimum metal panel design, are given for the various (global) optima found along with some examples of (rejected) local optima.

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 985 , May 1995 , pp. 169 - 177
Copyright
Copyright © Royal Aeronautical Society 1995 

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