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Conceptual design method for the wing weight estimation of strut-braced wing aircraft

Pinho Chiozzotto, Gabriel (2015) Conceptual design method for the wing weight estimation of strut-braced wing aircraft. 5th CEAS Air & Space Conference, 07.-11. Sept. 2015, Delft, The Netherlands.

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Abstract

This paper presents a method for the wing weight estimation of strut-braced wing aircraft in conceptual design. The method is simple to implement and captures important effects for the design of high aspect ratio braced wings. Conventional aluminum design or composites can be considered. Aeroelastic divergence, aileron reversal and elastic effects on the wing lift distribution are accounted for with simple strip theory and beam stiffness matrices. The stiffness matrices are extended to include the strut reaction. A direct method is used for the strut and wing internal loads calculation. Comparison with Nastran results shows good accuracy in the prediction of aeroelastic effects and strut reaction. Design studies show potential to reduce the wing mass between 11% and 14% or increase the aspect ratio from 10 to 12 in comparison to a conventional wing.

Item URL in elib:https://elib.dlr.de/98248/
Document Type:Conference or Workshop Item (Speech)
Title:Conceptual design method for the wing weight estimation of strut-braced wing aircraft
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Pinho Chiozzotto, Gabrielgabriel.pinhochiozzotto (at) dlr.deUNSPECIFIED
Date:September 2015
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Aeroelasticity. Loads. Mass estimation. Conceptual design.
Event Title:5th CEAS Air & Space Conference
Event Location:Delft, The Netherlands
Event Type:international Conference
Event Dates:07.-11. Sept. 2015
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 - Flexible Aircraft (old)
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Loads Analysis and Aeroelastic Design
Deposited By: Chiozzotto, Gabriel
Deposited On:13 Oct 2015 10:38
Last Modified:13 Oct 2015 10:38

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