Design of multiple-ply laminated composite tapered beams

Technical Report · Tue Jun 01 04:00:00 EDT 1993

OSTI ID:5937359

Rodriguez, P

A study of a special case of symmetric laminated composite cantilever beams is presented. The approach models beams that are tapered both in depth and width and investigates the effect of the ply layup angle and the ply taper on bending and interlaminar shearing stresses. For the determination of stresses and deflections, the beam stiffness matrices are expressed as linear functions of the beam length. Using classical lamination theory (CLT) the stiffness matrices are determined and assembled at strategic locations along the length of the beam. They are then inverted and necessary stiffness parameters are obtained numerically and extracted for determination of design information at each location chosen. Several ply layup configurations are investigated, and design considerations are preSDsented based on the findings. Finally, recommendations for the design of these beams are presented, and a means for anticipating the location of highest stresses is offered.

• Research Organization: National Aeronautics and Space Administration, Huntsville, AL (United States). George C. Marshall Space Flight Center
• OSTI ID: 5937359
• Report Number(s): N-93-31650; NASA-TM--108411; NAS--1.15:108411
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360601* -- Other Materials-- Preparation & Manufacture
360603 -- Materials-- Properties
BEAMS
BENDING
COMPOSITE MATERIALS
DEFORMATION
DESIGN
FATIGUE
FIBERS
FLEXURAL STRENGTH
MATERIALS
MECHANICAL PROPERTIES
SHEAR
SHEAR PROPERTIES
STRESS ANALYSIS
STRESSES