Finite element analysis of composite rudder for DO 228 Aircraft 13; 13;

Guruprasad, K and Subba Rao, M and Chandra, Ramesh (1988) Finite element analysis of composite rudder for DO 228 Aircraft 13; 13;. In: Composite Materials and Structures, 6-9 Jan 1988, Madras, India.

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Abstract

The design and analysis of a composite rudder for KO 228 aircraft is described. Stress analysis is carried out using finite element general purpose software ASKA. Automatic mesh generation and postprocessing are carried out using FEMGEN and FEMVIEW. Stress analysis of an existing metallic rudder is carried out to determine permissible deformations in the composite rudder. Initial design is based on the preliminary design studies carried out earlier. A choice of elements from the ASKA library is made from certain test examples. Convergence in maximum displacement is established by considering three different grids. Design variables considered are : geometrical parameters (widths and thicknesses of spar-flange and rib-flanges and thicknesses of spar-web and rib-webs) and lamination parameters (fibre orientation and stacking sequence) of spar, ribs and leading edge. Many iterations on these design variables are attempted to match the stiffness of the composite rudder to that of the metallic rudder. 2 ref.--AA

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Aircraft components;Design;Laminates;Materials substitution; Finite element method;Stress concentration;Ply orientation; Deformation;Rudders;Design parameters;Design engineering; Stress analysis;Aircraft;Stacking;Geometry;Computer programs;Stiffness;Fiber orientation;Mesh generation
Subjects: ENGINEERING > Structural Mechanics
Division/Department: Structures Division, Structures Division, Structures Division
Depositing User: M/S ICAST NAL
Date Deposited: 16 Oct 2006
Last Modified: 24 May 2010 09:51
URI: http://nal-ir.nal.res.in/id/eprint/2979

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