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Joint fixity effect on structural design of a box wing aircraft

Published online by Cambridge University Press:  27 January 2016

P. O. Jemitola ,
J. Fielding  and
P. Stocking
P. O. Jemitola*
Affiliation:
Department of Aerospace Engineering, Cranfield University, Cranfield, UK
J. Fielding
Affiliation:
Department of Aerospace Engineering, Cranfield University, Cranfield, UK
P. Stocking
Affiliation:
Department of Aerospace Engineering, Cranfield University, Cranfield, UK
*
p.o.jemitola@cranfield.ac.uk
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Abstract

A computational study was performed to compare the stress distributions in finite element torsion box models of a box wing structure that result from employing four different wing/end fin joint fixities. All considered wings were trimmed in pitch. The joint fixities refer to the type of attachment that connects the tip of the fore and aft wings to the end fin. Using loads from a vortex lattice tool, the analysis determined the best wing-joint fixity of a statically loaded idealised box wing configuration by comparing the stress distributions resulting from the different wing joints in addition to other essential aerodynamic requirements. Analysis of the wing joint fixity indicates that the rigid joint is the most suitable.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1178 , April 2012 , pp. 363 - 372
Copyright
Copyright © Royal Aeronautical Society 2012 

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