Abstract
Buckling of plain and discretely stiffened composite cylindrical panels made of a repeated sublaminate construction is studied using the finite element method. In repeated sublaminate construction, a full laminate is obtained by repeating a basic sublaminate, which has a smaller number of plies. The optimum design for buckling is obtained by determining the layup sequence of the plies in the sublaminate by ranking, so as to achieve maximum buckling load for a specified thickness. For this purpose, a particularized form of a four- noded, 48-dof quadrilateral composite shell element together with a fully compatible two-noded, 16-dof composite stiffener element are used.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
Similar content being viewed by others
References
. Leissa, A. W., Buckling of laminated composite plates and shell panels, AFWAL-TR-85-3069, Air Force Wright Aeronautical Laboratories, Wright- Patterson AFB, OH (1985), pp. 310 - 77.
Burns, A. B. and Almroth, B. O., Structural optimization of axially compressed ring-stringer stiffened cylinders. Journal of Spacecraft, 3 (1) (1966) 19–25.
Singer, J., Barouch, M. and Harari, O., On the stability of eccentrically stiffened cylindrical shells under axial compression. International Journal of Solids and Structures, 3 (1967) 445–70.
Jones, R. M., Buckling of circular cylindrical shells with multiple orthotropic layers and eccentric stiffeners. AIAA Journal (12) (1968) 2301–5.
Hedgepeth, J. M. and Hall, D. B., Stability of stiffened cylinders. AIAA Journal, (12) (1965) 2275–86.
Tsai, S. W., Composites Design, 4th edn. Think Composites, Dayton, Ohio, Section 9.8, 1988, pp. 9–6.
Venkatesh, A. and Rao, K. P., A doubly curved quadrilateral finite element for the analysis of laminated anisotropic thin shell of revolution. Computers and Structures, 12 (1980) 825–32.
Venkatesh, A. and Rao, K. P., A laminated anisotropic curved beam and shell stiffening finite element. Computers and Structures, 15 (2) (1982) 197–201.
Venkatesh, A. and Rao, K. P., Analysis of laminated shells of revolution with laminated stiffeners using a doubly curved quadrilateral finite element. Computers and Structures, C20 (4) (1985) 669–82.
. Venkatesh, A., Finite element analysis of laminated anisotropic shells with laminated anisotropic stiffeners. PhD thesis, Indian Institute of Science, Bangalore, 1982.
Rao, K. P. and Tripathy, B., Composite cylindrical panels—optimum layup for buckling by ranking. Computers and Structures Journal (in press)
Tripathy, B. and Rao, K. P., Curved composite beams—optimum layup for buckling by ranking. Paper sent for publication to Computers and Structures Journal.
Rao, K. P., Kumar, M. and Shashikumar, V., Buckling of composite plates made of repeated sublaminate construction. Proceedings of the Vllth International Conference on Composite Materials, ICCM 7, Beijing, China, 1989.
Tripathy, B. and Rao, K. P., Stiffened composite cylindrical panels—optimum layup for buckling by ranking. Paper sent for publication to Computers and Structures Journal.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1991 Elsevier Science Publishers LTD.
About this chapter
Cite this chapter
Tripathy, B., Rao, K.P. (1991). Optimum Design for Buckling of Plain and Stiffened Composite Cylindrical Panels. In: Marshall, I.H. (eds) Composite Structures. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-3662-4_29
Download citation
DOI: https://doi.org/10.1007/978-94-011-3662-4_29
Publisher Name: Springer, Dordrecht
Print ISBN: 978-1-85166-647-8
Online ISBN: 978-94-011-3662-4
eBook Packages: Springer Book Archive