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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.- 21. 01. 2021, Virtuelle Konferenz. doi: 10.2514/6.2021-1964. ISBN 978-162410609-5.

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

Kurzfassung

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.

elib-URL des Eintrags:https://elib.dlr.de/141247/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Zimmer, MarkusMarkus.Zimmer (at) dlr.dehttps://orcid.org/0000-0001-6785-7402NICHT SPEZIFIZIERT
Datum:4 Januar 2021
Erschienen in:AIAA Scitech 2021 Forum
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Nein
DOI:10.2514/6.2021-1964
ISBN:978-162410609-5
Status:veröffentlicht
Stichwörter:computational aeroelasticity, nonlinear aeroelasticity, large deflections, carbon fibre, laminate theory, loads, structural optimisation, design, long range
Veranstaltungstitel:AIAA Scitech 2021 Forum
Veranstaltungsort:Virtuelle Konferenz
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:11.- 21. 01. 2021
Veranstalter :AIAA - American Institute of Aeronautics and Astronautics
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Effizientes Luftfahrzeug
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L EV - Effizientes Luftfahrzeug
DLR - Teilgebiet (Projekt, Vorhaben):L - Digitale Technologien
Standort: Göttingen
Institute & Einrichtungen:Institut für Aeroelastik > Lastanalyse und Entwurf
Hinterlegt von: Zimmer, Markus
Hinterlegt am:26 Aug 2021 15:56
Letzte Änderung:27 Mär 2024 15:07

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