Failure Analysis of a Laminate You are part of the structural analysis team of the “AE535 Company”.

Failure Analysis of a Laminate You are part of the structural analysis team of the “AE535 Company”. The company is studying a variety of configurations (materials, layups) of composite laminates to include in the wing design and manufacturing of the next composite aircraft. You have been given a laminate configuration and are tasked to evaluate if it will sustain three different conditions of load. You need to report your evaluation to the design team to finally discuss together the approval of the design.

Analysis:

Perform the Failure Analysis of the given Laminate, using a code you have developed, capable of calculating the stresses and strains at each ply of the laminate and assessing if failure of any of the plies occurs according to the Failure Criteria (Maximum Stress, Maximum Strain, Hill-Tsai and Tsai-Wu (stop at First Ply Failure, do not implement Ultimate Laminate Failure).

Perform the analysis for the three assigned load cases and, for each one, evaluate:

a) the midplane strains and curvatures

b) the local stresses and strains at each ply (outermost ply coordinate)

c) if failure occurs

d) If failure occurs, identify at which ply and by which mode of failure

Attach your code at the end of the report. The code must be well commented and working. The code will be discussed orally, during the time allocated for the final exam (10min), during which you will run your code and show the output results.

Code Output: 1. A, B, D matrices

2. Effective Laminate Properties (Mechanical and Thermal)

3. Midplane Strains and Curvatures

4. Global and Local Stresses and Strains at each ply (outermost ply coordinate)

5. Figure 1: three subplots of Global Stresses (1 subplot per stress component) across the thickness of the laminate (overlap the load cases in different colors, one color per load case)

6. Figure 2: three subplots of Global Strains (1 subplot per strain component) across the thickness of the laminate (overlap the load cases in different colors, one color per load case)

Report:

Write a max. 4 pages report where you describe in a thorough narrative the performed analysis. In your introduction, illustrate your case study, including the ABD matrices and Table of Effective Laminate Properties. In the analysis section, explain the steps of the solution. Make sure to support your explanations with the formula used. In the results section, report and comment your results: Table of Global and Local Stresses and Strains at each ply (1 Table per Load case), Plots for Global Stresses and Plots for Global Strains. Explain thoroughly your results referring to your knowledge of composite laminate analysis (i.e. composite properties, ply orientation and layup, load conditions, load-deformation relations). Evaluate failure and explain for which criteria and at which ply/plies it occurs and why. In case of failure, evaluate the failure mode and explain it in terms of micromechanics.

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