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Mr. T Rajanna
Ph.D. Scholar
Indian Institute of Technology
Bombay
t.rajanna@gmail.com
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Stiffened laminated panels are structural components consisting of
plates reinforced by a system of ribs to enhance their load carrying
capacities. Plates with an array of stiffeners are commonly found in
fuselage and wings of an aircraft, a ship’s hull and deck, off shore
drilling rigs, pressure vessels, roofing units, launching pedestal
of rocket etc. The diverse applications of such panels are found to
be exposed to in-plane edge loading (compressive/tensile) in many
situations.
For instance, during the take-off of an aircraft, the lifting force
tries to bend the wings upward. Due to this, many upper wing panels
are under the application of
non-uniform
in-plane edge compression. Similarly, lower wing panels are under
non-uniform
in-plane edge tension.
However, the presence of these loadings may significantly alter the
free vibration response of such panels. In fact, a situation may
arise wherein the natural frequency of a component becomes zero,
thereby causing instability of the component at a fairly low-stress
field. Hence, the elastic stability may be considered as a special
case of vibration problem and such problems have been of
considerable importance and interest to researchers for many years.
This work is proposed to
investigate the effect of different ply-angles, boundary conditions,
partial/non-uniform
edge loads,
and different pattern of
stiffeners
and their positions
on the vibration and stability behaviour
of stiffened panels with and without cutouts.
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