AE7723: Advanced Stress Analysis & Materials - Engineering Assignment Help

Assignment Task:

Module Learning Outcomes
The following module learning outcomes and professional body learning outcomes are tested in this assessment:

1. Evaluate stresses and deflections in engineering structures under various complex loading conditions.
2. Use finite element software for analysis of complex structures.

2. Aims
The aims of the present assignment are:

1. To be able to calculate the theoretical critical buckling load of a laminated composite plate
2. To become familiar with the analysis of a laminated composite plate using ANSYS finite element software.

3. Objectives
The objectives of the present assignment are the following:
i. To understand basic theories and terminology related to the laminated composite materials and how to model them with finite element analysis.
ii. To calculate the critical buckling load of a laminated composite plate using analytical
iii. To use FEA for buckling analysis of laminated fibre reinforced polymer (FRP) composite materials
iv. To use FEA for the buckling analysis of an aircraft fuselage section made from FRP materials.

4. Deliverables
Part 1: Theoretical questions (10% - all questions carry equal marks)
a) What is buckling and why is it important in engineering?
b) What is a ‘Degree of Freedom’?
c) What is a “mesh independent result”?
d) How can the critical buckling load of a plate be computed using a “FEA -eigenvalue analysis”?
e) How can the critical buckling load of a plate be computed using a “FEA - nonlinear analysis”?
f) What is a laminated composite plate?
g) What are the main assumptions for the Classical Laminated Plate Theory (CLPT)?
h) What are the main assumptions for the first-order shear deformation theory (FSDT)?
i) How can the results from the FE analysis of a laminated composite plate be validated?

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