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Robust optimization of an airplane component taking into account the uncertainty of the design parameters
Author(s) -
Steenackers Gunther,
Guillaume Patrick,
Vanlanduit Steve
Publication year - 2009
Publication title -
quality and reliability engineering international
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.913
H-Index - 62
eISSN - 1099-1638
pISSN - 0748-8017
DOI - 10.1002/qre.966
Subject(s) - displacement (psychology) , finite element method , monte carlo method , range (aeronautics) , airplane , vibration , component (thermodynamics) , function (biology) , track (disk drive) , computer science , structural engineering , engineering , mathematics , statistics , mechanical engineering , aerospace engineering , physics , psychology , quantum mechanics , evolutionary biology , biology , psychotherapist , thermodynamics
A slat track, structural component of an aircraft wing that transfers the aerodynamical loads, excited by operational forces can result in excessive displacement levels if not properly designed. The design parameter values are not always precisely known but can contain a level of uncertainty to some extent due to, for example dimensional variation. During the different optimization approaches, the slat track geometry is optimized in order to limit the maximum vertical displacement, taking into account the variability of the design parameters. Application and comparison of different optimal, robust and generalized optimization approaches is presented and applied on the slat track finite element model, making use of mean and variance response functions to model the uncertainty on the finite element displacement values. Next to validating different objective function statements, a comparison is also made on the level of accuracy and practicability concerning the different response function models, based on regression techniques and Monte Carlo simulations, optimization and transmissibilities and regressive techniques and vibration reduction over a frequency range. Copyright © 2008 John Wiley & Sons, Ltd.