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Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints

Zimmer, Markus (2021) Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints. In: AIAA Scitech 2021 Forum. AIAA Scitech 2021 Forum, 11.-15., 19.-21. Jan 2021, Virtuelle Konferenz. doi: 10.2514/6.2021-1964. ISBN 978-162410609-5.

Full text not available from this repository.

Official URL: https://arc.aiaa.org/doi/10.2514/6.2021-1964

Abstract

Due to the increased application of carbon fibre reinforced plastics (CFRP) in the aircraft industry within the past decades, design of primary load carrying structures has vastly evolved. 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. To investigate this matter, a highly flexible long range jet transport, resembling an Airbus A350- 900 or a Boeing 787-10 class aircraft, is taken as a reference. Its simulation model components are set up using an in-house model generator. In doing so, the main load carrying structure of the wing is optimised by the means of an comprehensive loads and optimisation tool chain built around MSC.Nastran. By applying an aeroelastic tailoring approach the flight mechanic stability of the aircraft is guaranteed, while the calculation of the sensitivities in the gradient based optimisation incorporates the change in the dimensioning loads. To obtain a highly flexible structure, a carbon fibre laminate optimisation is set up, using lamination parameters in combination with large strain allowables (up to 8000 µ in tension). The result is a highly flexible wing structure, featuring a vertical displacement of up to 10 % with respect to the semi-wingspan during cruise flight. Besides the impact of varying boundary conditions and optimisation strategies on the flexibility and the primary structural mass of the wing, the development of significant constraints and modal properties is investigated.

Item URL in elib:https://elib.dlr.de/141247/
Document Type:Conference or Workshop Item (Speech)
Title:Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Zimmer, MarkusMarkus.Zimmer (at) dlr.dehttps://orcid.org/0000-0001-6785-7402
Date:4 January 2021
Journal or Publication Title:AIAA Scitech 2021 Forum
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI:10.2514/6.2021-1964
ISBN:978-162410609-5
Status:Published
Keywords:computational aeroelasticity, nonlinear aeroelasticity, large deflections, carbon fibre, laminate theory, loads, structural optimisation, design, long range
Event Title:AIAA Scitech 2021 Forum
Event Location:Virtuelle Konferenz
Event Type:international Conference
Event Dates:11.-15., 19.-21. Jan 2021
Organizer:AIAA - American Institute of Aeronautics and Astronautics
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Efficient Vehicle
DLR - Research area:Aeronautics
DLR - Program:L EV - Efficient Vehicle
DLR - Research theme (Project):L - Digital Technologies
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Loads Analysis and Aeroelastic Design
Deposited By: Zimmer, Markus
Deposited On:26 Aug 2021 15:56
Last Modified:26 Aug 2021 15:56

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