Author:
Niyogi Samiksha B,Wankhade Rajan L,Gajbhiye Param D
Abstract
Abstract
In this work, the simplified forms of governing differential equations are employed to analyse the laminated composite plates subjected to buckling. Effect of orthotropic material via variation in the E1/E2 ratio on the buckling parameters is verified and corresponding results are provided. With the developments in the modern technology, composites have found a significant role in applications in aerospace industry. Under the compressive in-plane loads, the composites undergo buckling. Hence, it is crucial to observe and study the buckling characteristics of laminated composites with effect of material properties. We have obtained the results of the buckling loads of a laminated composite having a cross-ply lamination scheme of plates with simply supported and clamped boundary conditions. Effect of the orthotropic material on these parameters is studied via the present study.
Subject
General Physics and Astronomy
Reference18 articles.
1. Stability and natural vibration analysis of laminated plates by using a mixed element based on a refined plate theory;Putcha;J. Sound Vib,1986
2. Geometric nonlinear analysis of skew plates using finite element method;Wankhade;International Journal of Advanced Engineering Technology,2011
3. Free vibration of simply supported piezolaminated composite plates using finite element method;Bajoria;Advanced Materials Research,2012
4. Stability of simply supported smart piezolaminated composite plates using finite element method;Wankhade;Proc. Int. Conf. Adv. Aeronautical Mech. Eng. AME,2012
5. Analysis of thick beams using first order shear deformation theory;Deshpande,2013
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