FREE VIBRATION AND BUCKLING CHARACTERISTICS OF COMPOSITE PANELS HAVING ANISOTROPIC DAMAGE IN A SINGLE LAYER
The present study deals with the effects of single layer damage on the free vibration and the buckling characteristics of doubly curved composite panels. First order shear deformation theory is used to model the panels, considering the effects of rotary inertia and shear deformation according to Sanders first approximation for doubly curved shells. An element based anisotropic damage formulation is used to model damaged composite panels using Finite Element Method. The orthogonality of the damaged model is established and subsequently, suitable damage parameters are chosen for the present study. Cross-ply and angle- ply cylindrical, spherical and hyper-paraboloid curved laminates as well as flat plates have been studied. The results obtained have been compared with equivalent undamaged panels as well as with panels having damage throughout the thickness. It has been observed that the damage model shows a strong orthogonality and damage in the fiber direction affects free-vibration and buckling characteristics more than damage in any other orthogonal direction. Curvature greatly affects the free vibration and buckling characteristics of damaged panels. A damage located on a layer stressed due to curvature greatly influences free vibration and buckling characteristics than damage located in an unstressed or less stressed layer. It has also been observed that the fundamental natural frequency and buckling load of a single layer damaged panel always lie between the corresponding undamaged case and a case where damage exists throughout the thickness.
Anisotropic damage composite structure curved panels vibration buckling curvature effects
P.K.Datta S.Biswas
Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur, India-721302
国际会议
The IJSSD Symposium 2012 on Progress in Structural Stability and Dynamics(2012国际结构稳定与动力学进展会议)
南京
英文
87-93
2012-04-14（万方平台首次上网日期，不代表论文的发表时间）