CompositePro 3.0
Introduction
When charts and tables just aren’t enough, and finite element analysis is too much, CompositePro fills the void with function and value. The program is subdivided into six functional modules and equipped with both English and SI units. The 84 page users guide walks you through each screen of the program.
Micromechanics Module
The micromechanics module allows you to select from a library of 3D fibre and matrix properties or input your own. Once the fibre and matrix properties are selected, lamina mechanical properties, physical properties and strengths can be calculated on a “by-volume” or “by-weight” basis. The theory used for micromechanics calculations is based on rule-of-mixtures, cylinder model & Chamis methods.
Laminate Module
This feature allows you to use a library of composite and metallic lamina properties or to input your own. You can create a lay-up of any combination of laminae, at any angle and easily calculate and plot globallaminate material properties. 2D and 3D properties can be generated and the laminate can be loaded with in-plane strains, stresses, resultants, moment resultants and temperature or moisture loads. The applied loads allow you to display and plot stresses and strains on the individual laminae. You may select from three laminate failure theories (maximum strain, maximum stress or quadratic) to predict 2D laminate strengths. The “first-ply” failure survey option allows you to quickly assess and plot laminate strength for tension, compression and shear. The “progressive-ply” failure option predicts ultimate laminate strengths and plots the respective stress-strain curves. The basis of this module is classical laminated plate theory for orthotropic laminae.
Laminated Plate Module
Once you have defined the plate length and width, three different
options
are available. Plate bending allows calculation of moments and
deflections for
simply supported uniform or concentrated loaded plates. The stability
optioncalculates the minimum loads which will make a uniaxial or
biaxial loaded
plate buckle and the natural vibration frequency for a variety of
boundary
conditions can also be determined.
Sandwich Plate Module
In this module you select core materials from a library or input your own. The length, width and core thickness for the sandwich are first defined. You have two options: sandwich buckling (select from five different boundary conditions for calculating the minimum uniaxial compression stress for buckling) and the bending option (determines the maximum deflection due to a uniform distributed load on a simply supported sandwich). Both options calculate face wrinkling and dimpling stresses. MIL-HDBK 23 theory & methods are employed.
Beam/Tube Module
In this module, the cross sections include solid plate, elliptical, circular, rectangular, I, C, U and T sections. Bending deflection, moments, stresses, etc. can be calculated for point, uniform distributed and triangular loadings using combinations of fixed, free and simple supports. Fundamental vibrationfrequencies,cylindrical stability calculations, torsional stresses and deflections can also be determined. The module includes pressure vessel analysis for thin walled pipes and tanks and thick wall vessel analysis for thick walled pipes and tanks. Calculations are based upon beam theory (Roarks Formulas for Stress and Strain) and NASA SP-8007 cylindrical stability.
Utilities Module
This module includes the features of volume fraction converter, filament winding calculator, textile converter, radius of curvature and fabric builder.