Finite element vibration analysis of laminated composite folded plate structures

Article type: Research Article

Authors: Guha Niyogi, A. | Laha, M.K. | Sinha, P.K.^;

Affiliations: Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur – 721 302, India

Note: [] Corresponding author. Tel.: +91 3222 77997; Fax: +91 3222 55303/55239; E‐mail: pksinha@aero.iitkgp.ernet.in

Abstract: A nine‐noded Lagrangian plate bending finite element that incorporates first‐order transverse shear deformation and rotary inertia is used to predict the free and forced vibration response of laminated composite folded plate structures. A 6\times 6 transformation matrix is derived to transform the system element matrices before assembly. The usual five degrees‐of‐freedom per node is appended with an additional drilling degree of freedom in order to fit the transformation. The present finite element results show good agreement with the available semi‐analytical solutions and finite element results. Parametric studies are conducted for free and forced vibration analysis for laminated folded plates, with reference to crank angle, fibre angle and stacking sequence. The natural frequencies and mode shapes, and forced vibration responses furnished here may serve as a benchmark for future investigations.

Keywords: Composite, finite element method, stacking sequence, transverse shear, folded plates, crank angle, transformation

Journal: Shock and Vibration, vol. 6, no. 5-6, pp. 273-283, 1999