Murthy, Ramana PV and Rao, KP (1985) Analysis of laminated bimodulus composite thin shells of revolution using a doubly curved quadrilateral finite element. In: International Journal for Numerical Methods in Engineering, 21 (2). pp. 285-299.Full text not available from this repository. (Request a copy)
This paper presents a finite element analysis of laminated bimodulus composite thin shells of revolution using a 48 d.o.f. doubly curved quadrilateral finite element. All the three displacements of the shell element reference surface are expressed as products of one-dimensional first-order Hermite interpolation polynomials. The constitutive relationship for a bimodulus composite is assumed to depend on the fibre-direction strain experienced by each orthotropic layer. Consequently the true state of strain and the corresponding constitutive relationship in a bimodulus composite structure are to be determined iteratively. The true state of stress/strain is obtained by specifying a maximum error in the locations of the two neutral surfaces (one along each of the orthogonal reference axes) in the shell. The use of the quadrilateral shell finite element is validated by solving the problem of (i) a freely supported single layer $(0^o)$ bimodulus composite square plate and (ii) a freely supported single layer $(0^o)$ cylindrical panel, which are subjected to sinusoidal transverse loading and for which analytical solutions are available. Next, the problems of a single layer $(90^o)$ pinched cylindrical shell and a single layer $(0^o)$ open crown hemispherical shell are solved to show the ability of the present program.
|Item Type:||Journal Article|
|Additional Information:||The copyright belongs to John Wiley & Sons, Ltd.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||27 Jan 2006|
|Last Modified:||27 Aug 2008 11:42|
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