Affiliation:
1. National Aeronautical Laboratory, Bangalore, India
Abstract
Numerical solutions are obtained for stresses around a circular hole in laminated composite cylindrical shells subjected to uniform internal pressure loading. Matrix method of structural analysis using a high-precision triangular laminated anisotropic cylindrical shell finite element is employed. Results are presented to show significant influence of composite material systems, winding patterns and curvatures on the state of stress around the opening.
Subject
Mechanical Engineering,Mechanics of Materials,Safety, Risk, Reliability and Quality
Cited by
1 articles.
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