# HW3 - Aerospace Structural Composites I Homework#3 Anirban...

This preview shows pages 1–2. Sign up to view the full content.

Aerospace Structural Composites I Homework#3 Anirban Chaudhuri 1. Write a Matlab routine to calculate the A matrix of a laminate made from a single material with all plies having the same thickness. The input should consist of material properties (E 1 , E 2 , G 12 , and n 12 ), ply thickness (t), the number of plies (n), and ply angles. Test your routine by using Example 6.3.1 in Chapter 6. Solution: A MATLAB code is provided to evaluate the A-matrix. The main code takes in the input arguments of (material properties) E 1 , E 2 , G 12 , 12 , (thickness) t, (number of plies) n and ply angles. It calls a function that evaluates the A-matrix using the equations given below. 0 1 1 2 1 3 1 4 1 cos2 sin 2 cos4 sin 4 A n Ak k k n Akk k n k k n k Vh Vt … (1) where, h (total height) =n*t 12 3 11 3 0 22 43 1 12 53 2 66 3 23 16 4 26 00 0 0 1 0 2 1 0 2 A A A A A UU U A U V A V A V A V A V A        … (2) MATLAB Code:

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

## This note was uploaded on 06/06/2011 for the course EAS 4240 taught by Professor Peterifju during the Spring '08 term at University of Florida.

### Page1 / 4

HW3 - Aerospace Structural Composites I Homework#3 Anirban...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online