CompositePro Modules

Laminate Module. This module is packed with features. A library of composite and metallic lamina properties can be used or input your own. A layup of any combination of laminae, at any angle can be created. Global laminate material properties are easily calculated and plotted. The laminate can then be loaded with in-plane strains, stresses, resultants, moment resultants and temperature or moisture loads.

Stresses and strains on the individual laminae, due to the applied loads, can be displayed and plotted. You may select from three laminate failure theories (maximum strain, maximum stress or quadratic) to predict 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" option predicts ultimate laminate strengths and plots the respective stress-strain curves. Classical in-plane laminated plate theory is the basis of this module.

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 option calculates the minimum loads which will make a uniaxial or biaxial loaded plate buckle.
• Finally, the natural vibration frequency for a variety of boundary conditions can be determined.

Classical "Navier" plate solutions are utilized.

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 may now choose from two options. Sandwich buckling lets you select from five different boundary conditions for calculating the minimum uniaxial compression stress for buckling. 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 and methods are employed.

Beam/Tube Module

• Crossections include elliptical, circular, rectangular, I, C, U and T sections.
• Bending deflection, moments, stresses, etc. are calculated for point, uniform distributed and triangular loadings using combinations of fixed, free and simple supports.
• Torsional stresses and deflections can be determined.
• Fundamental vibration frequencies of bending and twisting are determined for a variety of end conditions and end masses.
• Cylindrical stability for external pressure, bending, torsion and axial compression is available as well as column stability calculations.
• For closed crossections ply placement through the laminate is taken into account.
• The calculations are based upon basic beam theory and NASA SP-8007 cylindrical stability formulations.

Utilities Module

• Volume Fraction Converter: converts between fiber volume and weight fractions.
• Filament Winding Calculator: calculates the layer and lay-up thickness for a filament wound lay-up.
• Textile Converter: converts between fiber yield, denier, end area, tex, and lineal density.
• Radius of Curvature: calculates the bending radius for un-symmetric laminates.
• Fabric Builder: aids in creating a lay-up which is composed of woven, stitched or random fabrics or broadgoods.