International Journal of Engineering Research and General Science Volume 2, Issue 5, August-September, 2014 ISSN 2091-2730 298 www.ijergs.org AN OVERVIEW OF BUCKLING ANALYSIS OF SINGLE PLY COMPOSITE PLATE WITH CUTOUTS Parth Bhavsar [1] , Prof. Krunal Shah [2] , Prof. Sankalp Bhatia [3] [1] Student, M.E. (CAD/CAM), A. D. Patel Institute of Technology, New V.V.Nagar, Gujarat, India [2], [3] Assistant Professor, A. D. Patel Institute of Technology, New V.V.Nagar, Gujarat, India E-mail Id: parthbhavsar20990@gmail.com , Abstract The use of Composite material in aircraft industries is booming now-a days to grab the advantage of high strength to weight ratio. These materials are used to build main components of aircraft like fuselage, panels, rudder, and skins. It is unavoidable to provide different size, shaped cutouts in such components for different purpose i.e inspection, maintenance. The buckling behavior on composite plate with different shape, size and location of the cutouts have been explore by many researchers in last 2 decades. The presented review article is an attempt to summarize the issue of critically examine the current status, problems and opportunities to use of single ply composite in aircraft industries. Keywords:composite material, aircraft, single ply, cutout size, cutout shape, buckling analysis with FEA and Experimental. INTRODUCTION The buckling behavior of plates has been studied by many researchers in structural mechanics for aircraft and other structural parts over a Century. Steel, Aluminium, Titanium plates are often used as the main components of aircraft structures such as fuselage, panels, elevator, rudder, skins etc. So for making optimum structural components material must have best characteristics then other conventional materials. So composite materials are widely used for this purpose, like carbon fiber reinforced polymer (CFRP), Glass fiber reinforced polymer (GFRP), Aramide fiber reinforced polymer (AFRP), etc. There are various holes, vents, cutouts and passage are provided for different purpose, to provide access for inspection, maintenance, or simply to reduce weight. Due to this cutouts in plate elements leads to change in stress distribution within the member and variations in buckling characteristics of the plate element. The effects of the shape, size, location and types of applied load on the performance and buckling behavior of such perforated plates have been investigated by several researchers over the past two decades. Many researcher explore such results for their research work. REVIEW These papers have been reviewed for this study. Following researches is based on their methodology, principles and their conclusions. Donnie G. Brady, Melody A. Hammond explored manufacturing and usage of single ply composite plates, it is a Patent for Single ply reinforced thermoplastic composite. Multiple ply laminates have been used in the aircraft industry for window shades and other applications. A problem with multiple ply laminates is that they are relatively more expensive than single ply composites. However, earlier single ply laminates have a problem to have brittle, and thus not well adapted for being rolled as is required in a window shade application as well as for layering fuselage, fairing and for other components. The invention of a single ply thermoplastic composite is very useful concept for aircraft manufacturer. Arunkumar R. investigated Buckling Analysis of Woven Glass epoxy Laminated Composite Plate,In this study, the influence of cut- out shape, length/thickness ratio, and ply orientation and aspect ratio on the buckling of woven glass epoxy laminated composite plate