hybrid composite laminate

• We will now add GY-70 to our analysis and replace the 0 ° plies with this material.
• Click on the Material Tab and increase the No. of Materials to 2. (Note the program stops running . It now requires input to fill this table.) This is an Select GY-70 from the Materials Database tab. Change the Apply to Mat. ID. option to 2 and hit the Apply to Mat. ID button. The second row is now populated with Material Data for GY-70. (Click on the STOPPED CLICK TO RUN button to run the analysis again. No results are changed as we have not modified the laminate yet).
• Click the Geometry Tab and in the repeat unit layup table change the first mat ID to 2. Hit the Send to Sublam button to populate the laminate with the new layup. Click on the Stresses & Strains tab in the results section. You will see the stresses have changed significantly. You will also see that the stresses are unsymmetric. Simply hit the Symmetric button located top center and your laminate stresses will be symmetric about the laminate midplane.
• Take a look at the effective properties and ABD matrices for this laminate. You can see that the properties and stresses are now more anisotropic with the presence of higher stiffness carbon fibers.