Wing aerostructural optimization with an analytical fuel consumption sensitivity model
Wing aerostructural optimization with an analytical fuel consumption sensitivity model
Based on a quasi-steady mission in a vertical plane, this paper presents an analytical derivation to compute the fuel consumption sensitivity. Within the mission analysis simplifications required by this method, a wing aerostructural design problem that accounts for multiple flight conditions is proposed. Such graequdient-based optimization problem is presented for an Airbus A320 as a test case application. This test case efficiently couples the mission analysis to the aerostructural FEMWET analysis code via an online-generated parabolic drag polar. FEMWET uses a quasi-three-dimensional wing aerodynamic analysis coupled with a finite beam element method. The optimized solution yields a large-span wing in agreement with aerostructural design optimization literature.
719–732
Jacome, Louis Bahamonde
6c8463f7-c536-435b-8346-0adb48aa7e5b
Elham, A.
676043c6-547a-4081-8521-1567885ad41a
1 September 2019
Jacome, Louis Bahamonde
6c8463f7-c536-435b-8346-0adb48aa7e5b
Elham, A.
676043c6-547a-4081-8521-1567885ad41a
Jacome, Louis Bahamonde and Elham, A.
(2019)
Wing aerostructural optimization with an analytical fuel consumption sensitivity model.
CEAS Aeronautical Journal, 10 (3), .
(doi:10.1007/s13272-018-0342-z).
Abstract
Based on a quasi-steady mission in a vertical plane, this paper presents an analytical derivation to compute the fuel consumption sensitivity. Within the mission analysis simplifications required by this method, a wing aerostructural design problem that accounts for multiple flight conditions is proposed. Such graequdient-based optimization problem is presented for an Airbus A320 as a test case application. This test case efficiently couples the mission analysis to the aerostructural FEMWET analysis code via an online-generated parabolic drag polar. FEMWET uses a quasi-three-dimensional wing aerodynamic analysis coupled with a finite beam element method. The optimized solution yields a large-span wing in agreement with aerostructural design optimization literature.
This record has no associated files available for download.
More information
Accepted/In Press date: 8 November 2018
Published date: 1 September 2019
Identifiers
Local EPrints ID: 470786
URI: http://eprints.soton.ac.uk/id/eprint/470786
ISSN: 1869-5582
PURE UUID: daae3788-d144-40a3-8d80-2f346f93dff7
Catalogue record
Date deposited: 20 Oct 2022 16:32
Last modified: 16 Mar 2024 21:27
Export record
Altmetrics
Contributors
Author:
Louis Bahamonde Jacome
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics