dc.contributor.advisor |
Zhang, Xiang |
|
dc.contributor.author |
Sodzi, P. |
|
dc.date.accessioned |
2012-01-18T16:13:00Z |
|
dc.date.available |
2012-01-18T16:13:00Z |
|
dc.date.issued |
2009-12 |
|
dc.identifier.uri |
http://dspace.lib.cranfield.ac.uk/handle/1826/6863 |
|
dc.description.abstract |
Wing joint design is one of the most critical areas in aircraft structures. Efficient and
damage tolerant wing-fuselage integration structure, applicable to the next generation of
transport aircraft, will facilitate the realisation of the benefits offered by new aircraft
concepts. The Blended Wing Body (BWB) aircraft concept represents a potential
revolution in subsonic transport efficiency for large airplanes. Studies have shown the
BWB to be superior to conventional airframes in all key measures. Apart from the
aerodynamic advantages, the BWB aircraft also provides a platform for wing-fuselage
design changes.
The main objective of this research is to design a damage tolerant wing-fuselage joint
with a novel bird’s mouth termination for a BWB aircraft that has a similar payload
range to the B767 aircraft. The damage tolerance analysis of the proposed BWB
wing/fuselage integration structure includes assessments of fatigue crack growth life,
residual strength and inspection capability.
The proposed structure includes a bird’s mouth termination of the spars that facilitates
smooth transfer of loading from the spar web into the root rib and the upper and lower
skins and is novel in its application to the blended wing body configuration. A finite
element analysis was required to determine local stresses for the prediction of fatigue
crack growth life, residual strength and inspection capability and to identify weak spots
in the proposed structure. The project aircraft wing comprises of three spars (front,
centre and rear) and a false rear spar thus defining a four cell wing box. Wing root
shear, bending moment and torque loads were derived and applied to a thin-walled three
box idealisation of the proposed structure. The challenges experienced in replicating the
loads obtained from the three box idealisation were addressed by modification of the
boundary conditions. Checks for compression and shear buckling were also undertaken
that confirmed that the applied loads were below the limits of the proposed structure.
The finite element analysis showed very clearly that the stresses in the novel bird’s
mouth spar termination were significantly lower than in the skin and that the skin
remained the more critical damage tolerant component at the wing root when the
structure was subjected to ultimate design stresses. The spar web at the bird’s mouth
termination was shown to have a larger crack growth life compared to the skin. The
thickness of the skin requires further investigation as a significant amount of local
bending was experienced due to the applied pressure. The skin will sustain a two-bay
crack at the design limit load thus proving the proposed wing fuselage integration
structure to be damage tolerant.
In conclusion, the main objective of the thesis has been achieved. An integrated wingfuselage
joint with novel bird’s mouth spar termination and surrounding structure have
been designed and substantiated (evaluated) by damage tolerance requirements. |
en_UK |
dc.language.iso |
en |
en_UK |
dc.publisher |
Cranfield University |
en_UK |
dc.rights |
© Cranfield University 2009. All rights reserved. No part of this publication may be
reproduced without the written permission of the copyright holder. |
en_UK |
dc.title |
Damage tolerant wing-fuselage integration structural design applicable to future BWB transport aircraft |
en_UK |
dc.type |
Thesis or dissertation |
en_UK |
dc.type.qualificationlevel |
Doctoral |
en_UK |
dc.type.qualificationname |
PhD |
en_UK |