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An extensive test
series on circular cylindrical laminated composite stringer-stiffened panels
subjected to axial compression, shear loading introduced by shear and combined
axial compression and shear was carried out at the Technion, Israel. The
test program was an essential part of an ongoing effort undertaken by the
POSICOSS project (improved postbuckling simulation for design of fibre composite
stiffened fuselage structures) aiming at design of low cost, low weight airborne
structures that was initiated and supported by the Fifth European Initiative
Program.
The first part of this test series, dealing with panels PSC1–PSC9 (blade-stiffened),
has already been summarized and published. The results of the tests with panels
BOX1–BOX4 (blade- and J-stiffened) have also been reported and published.
These tests dealt with two identical stiffened panels, combined together by
two flat nonstiffened aluminum webs, to form a torsion box, thus enabling
application of shear tractions, through introduction of torsion, and combined axial
compression and shear. The present manuscript aims at describing test results and
relevant numerical studies on the buckling and postbuckling behavior of
another set of four panels, AXIAL1–AXIAL4, stiffened by J-type stringers.
Based on the experimental studies carried out within the framework of the
POSICOSS project and reported in the literature and on the present study
design guidelines were formulated and presented. Accompanying supporting
calculations were presented as well; they were performed with a “fast” calculation
tool developed at the Technion, and based on the effective width method
modified to handle laminated circular cylindrical stringer-stiffened composite
panels.
