Buckling and postbuckling behavior of laminated composite stringer stiffened curved panels under axial compression: Experiments and design guidelines

Abstract

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.

Numerical and experimental investigations of compressed stiffened composite panel with local impact damage

“…Numerical modeling again is one of the most effective tools for studying and predicting a correct solution of the problem. Previous work related to numerical and experimental investigation of impact damage formation, delamination fail- ure and damage tolerance of aircraft composite structures has been reported in different papers [16][17][18][19][20]. This study is a successor of the previous work published in [21].…”

Analysis of the openings of aircraft composite laminated wing beam web under shear load

“…(3) When the load is mainly in the 0 0 direction, the 90 0 -direction layer group should be used as little as possible, and it can be separated by layers in the 0 0 direction or ±45 0 direction to reduce the shear stress and normal stress; in addition, in the layer The outer layer of the pressure plate uses ±45 0 direction paving, which can effectively improve the impact resistance of the structure [12].…”

Buckling and Post-buckling Characteristics of Stiffened Panels Under Compression-Shear Load

“…The stiffened panel structures are widely used in aircraft structures such as wings, fuselage skins, beam webs, and tail fins. The most common form of failure of the stiffened wall panel structures is loss of stability [1][2][3][4][5][6][7][8][9][10][11][12][13]. The stiffened panel still has strong load capacity after local instability; how to accurately capture the buckling of the stiffened panel and the displacement field outside the postbuckling plane is one of the focuses of attention in the stability test.…”