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Design and optimisation of a highly flexible wing structure for a generic long-range aircraft

Zimmer, Markus and Bramsiepe, Kjell (2019) Design and optimisation of a highly flexible wing structure for a generic long-range aircraft. DLRK 2019 - Deutscher Luft- und Raumfahrtkongress, 30. Sep. - 02. Okt. 2019, Darmstadt.

Full text not available from this repository.

Official URL: https://dlrk2019.dglr.de/nc/paper_download/index.html

Abstract

Due to the increased application of carbon fibre reinforced plastics (CFRP) in the aircraft industry in the past decades, design of primary load carrying structures has vastly evolved. Particularly, the Airbus A350 and the Boeing 787 are well known for their complete integral structures fabricated entirely out of CFRP. Ultimately, this led to weight saving and a wider design space as the result of reduced material density and the anisotropic nature of the composite. However, the aforementioned design space is currently limited by uncertainties such as material imperfections, open hole tensions or plate boarder stresses. These uncertainties are commonly overcome by applying large safety margins, limiting the benefit of replacing aluminium with carbon fibre. This work analyses the impact of increased strain failure limits on the structural optimisation of an aircraft wing structure. The goal is the design of a highly flexible wing box to form the groundwork for further research on the effects of large, geometrically nonlinear deformations in the field of aeroelasticity. Therefore, a parametric, in-house model generator is used to build a research model which features the attributes of a modern long range jet transport. Throughout this paper, simulation model components and topological decisions are presented, as well as the loads and optimisation tool chain which is applied to dimension the structure. The optimisation of the composite skin is based on a lamination parameter methodology in which the shell elements are restricted by strain and intracell buckling constraints. Initial results obtained from geometrically nonlinear finite element calculations with varying static manoeuvre loads indicate that the optimised structure is suffering from buckling of whole stiffened panels. As a consequence, responses obtained by linear buckling analyses are considered in the optimisation as well. Finally, the results of a parameter variation are presented. The generated structural model features a vertical wing tip displacement of 8.6% with respect to the wing half span during design cruise flight. Furthermore, the usability of the optimisation results for geometrically nonlinear calculations is demonstrated.

Item URL in elib:https://elib.dlr.de/130032/
Document Type:Conference or Workshop Item (Speech)
Title:Design and optimisation of a highly flexible wing structure for a generic long-range aircraft
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Zimmer, MarkusMarkus.Zimmer (at) dlr.deUNSPECIFIED
Bramsiepe, KjellKjell.Bramsiepe (at) dlr.deUNSPECIFIED
Date:30 September 2019
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:design, optimisation, structure, aeroelasticity, nonlinear, buckling
Event Title:DLRK 2019 - Deutscher Luft- und Raumfahrtkongress
Event Location:Darmstadt
Event Type:national Conference
Event Dates:30. Sep. - 02. Okt. 2019
Organizer:DGLR - Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberath e.V.
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Loads Analysis and Aeroelastic Design
Deposited By: Zimmer, Markus
Deposited On:11 Dec 2019 17:43
Last Modified:11 Dec 2019 17:43

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