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Engineering Students' MATLAB Task

This document provides instructions for Assignment 1 of the course AE682A: Analysis of Composite Structures. Students are asked to: 1) Write a MATLAB code to calculate the A, B, D matrices given laminate stacking sequence and lamina properties. The code should also determine lamina strains, stresses, and first-ply failure load using Tsai-Hill criterion for given loads. 2) Use the code to: a) Compare engineering constants of two laminates and comment on effect of 90-degree plies. b) Determine margin of safety for laminates under biaxial loads using Tsai-Hill criterion and comment. c) Comment on effect of interchanging load directions. 3

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Vishnu A R
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99 views1 page

Engineering Students' MATLAB Task

This document provides instructions for Assignment 1 of the course AE682A: Analysis of Composite Structures. Students are asked to: 1) Write a MATLAB code to calculate the A, B, D matrices given laminate stacking sequence and lamina properties. The code should also determine lamina strains, stresses, and first-ply failure load using Tsai-Hill criterion for given loads. 2) Use the code to: a) Compare engineering constants of two laminates and comment on effect of 90-degree plies. b) Determine margin of safety for laminates under biaxial loads using Tsai-Hill criterion and comment. c) Comment on effect of interchanging load directions. 3

Uploaded by

Vishnu A R
Copyright
© © All Rights Reserved
We take content rights seriously. If you suspect this is your content, claim it here.
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Download as PDF, TXT or read online on Scribd
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AE682A: Analysis of Composite Structures

Assignment 1 Start date: 11 Aug 2017 Due on: 21 Aug 2017

a) Write a MATLAB code for the following:


Given the laminate stacking sequence and the lamina properties, i.e., elastic
constants EL, ET, GLT, LT write a MATLAB code to find A, B, D matrices.
Further, given the requisite strength parameters for Tsai-Hill Failure criterion,
and the applied loads (N, M), extend the programme to determine individual
lamina strains and stresses and from those to determine the first-ply failure
load using Tsai-Hill criterion.

b) Use the code to determine the following:


i. The elastic properties of unidirectional carbon fiber–epoxy are EL=181.3 GPa,
ET=10.27 GPa, GLT=7.17 GPa, and LT=0.28. Compare the engineering elastic
constants of the [±45/0]s and [±45/0/90]s laminates manufactured from this
carbon fiber–epoxy material. Comment on the effect of additional 90-deg plies
in the second laminate.
ii. Consider the laminates in Prob 2. For this material, the ply thickness is 0.150
mm, the unidirectional longitudinal strength is 1100 MPa, transverse strength
50 MPa and the lamina in-plane shear strength is 120 MPa. The expected load
on the laminates is a biaxial load with Ny/Nx = 0.2. Use Tsai-Hill failure criteria
to find the margin of safety (MoS) for each of the above laminate if the applied
Nx=300 N/mm. [MoS= (Failure Load-Applied Load)/Failure Load]. Comment
on the usefulness of the 90-deg plies from the strength point of view.
iii. If the loads in x-y directions were interchanged, what effect would be seen on
the behaviour of laminates and the on margins? Give your comments.

Assignment due date : Mon 21 Aug.

You need to submit (soft copy)


(i) MATLAB source code (The code should be general and not just for the
laminate given. Use the solved examples in the class to verify portions of your
programme.)
(ii) Relevant matrix output and parameters for the numerical problem.
(iii) Your comments on the results obtained as asked in the problem statement

You need to submit in soft copy form through email.


You may be asked to make a presentation, if required.

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