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Optimum design of composite stiffened wingpanels — 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 (leastmass) dimensions of a range of stiffened wing panelswhich are subject to buckling and material strengthconstraints and are loaded in axial compression witha sinusoidal manufacturing imperfection. Designplots are presented to show the effects that variousrib spacings and stiffener types have on optimumdesign mass. A simplified model of a complete wingbox is used to illustrate the design of a full wingpanel and plots of optimum values of designvariables at various stations along the wing havebeen obtained. The results were chosen to illustratethe practicality of optimisation with reference tomanufacture of a full wing panel and to show theeffect of changing the sophistication of modellingand theory used for the range of panels considered.The important aspects of the choice of designvariables and design concepts are highlighted andpercentage savings in mass, compared with an optimummetal panel design, are given for the various(global) optima found along with some examples of(rejected) local optima.

Information

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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