Multi-fidelity wing aerostructural optimization using a trust region filter-SQP algorithm

Journal article (2016)

Authors

A. Elham Flight Performance and Propulsion - Aerospace Engineering
M.J.L. van Tooren University of South Carolina, Flight Performance and Propulsion - Aerospace Engineering
Research Group
Flight Performance and Propulsion (Aerospace Engineering) (TU Delft)
Copyright: © 2016 A. Elham, M.J.L. van Tooren
DOI
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https://doi.org/10.1007/s00158-016-1613-0
Aerostructural optimization Multi-fidelity optimization Trust region filter-SQP algorithm
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Published Date

2016

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Flight Performance and Propulsion

Abstract

A trust region filter-SQP method is used for wing multi-fidelity aerostructural optimization. Filter method eliminates the need for a penalty function, and subsequently a penalty parameter. Besides, it can easily be modified to be used for multi-fidelity optimization. A low fidelity aerostructural analysis tool is presented, that computes the drag, weight and structural deformation of lifting surfaces as well as their sensitivities with respect to the design variables using analytical methods. That tool is used for a mono-fidelity wing aerostructral optimization using a trust region filter-SQP method. In addition to that, a multi-fidelity aerostructural optimization has been performed, using a higher fidelity CFD code to calibrate the results of the lower fidelity model. In that case, the lower fidelity tool is used to compute the objective function, constraints and their derivatives to construct the quadratic programming subproblem. The high fidelity model is used to compute the objective function and the constraints used to generate the filter. The results of the high fidelity analysis are also used to calibrate the results of the lower fidelity tool during the optimization. This method is applied to optimize the wing of an A320 like aircraft for minimum fuel burn. The results showed about 9 % reduction in the aircraft mission fuel burn.

Files

Filter_Method.pdf
(.pdf | 3.24 Mb)