Browse Prior Art Database

Unidirectional Fibrous Composite-Material Strength Analysis

IP.com Disclosure Number: IPCOM000036830D
Original Publication Date: 1989-Nov-01
Included in the Prior Art Database: 2005-Jan-29
Document File: 2 page(s) / 79K

Publishing Venue

IBM

Related People

Baradari, F: AUTHOR [+2]

Abstract

Disclosed is a program for engineering analysis of unidirectional fibrous composite materials. The main application of this code is design optimization, which yields to minimum usage of raw materials and saves manufacturing process time.

This text was extracted from a PDF file.
At least one non-text object (such as an image or picture) has been suppressed.
This is the abbreviated version, containing approximately 63% of the total text.

Page 1 of 2

Unidirectional Fibrous Composite-Material Strength Analysis

Disclosed is a program for engineering analysis of unidirectional fibrous composite materials. The main application of this code is design optimization, which yields to minimum usage of raw materials and saves manufacturing process time.

The word "composite" in composite material signifies that two or more materials are combined on a macroscopic scale to form a useful material. The key is the macroscopic examination of material. Use of this concept allows the tailoring of a composite-material capability. Tailoring of a composite material yields only the stiffness and strength required in a given direction. This computer code has been developed according to classical lamination theory, to analyze lamination strength and load-deformation behavior.

In this code, the load on laminate is taken to mean both forces and moments; similarly, deformations are meant to include both strain and curvature. The analysis is composed of two different approaches that depend on whether any lamina have failed. If no lamina have hailed, the load must be determined at which the first lamina fails, that is, violates the Tsi-Wu failure criterion. If one or more lamina have already failed, new laminate stiffness matrix is calculated. Lamina stresses are recalculated to determine their distribution after a lamina has failed. Then it will be verified that remaining laminas, at their increased stress level, did not fail at the same...