Analysis of Laminated Composite Structures - Engineering Assignment Help

Assignment Task :

Module Learning Outcomes 

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

1. Description Laminated composite panels have been widely used in engineering applications due to their excellent high strength-to-weight ratio, modulus-to-weight ratio, and the controllability of the structural properties with the variation of fibre orientation and the lamina number. However, in such applications, the structures are susceptible to buckling as usually the thickness of composite laminates being significantly smaller than the width and length of the panels. Buckling is a very dangerous phenomenon related to thin-walled structures because it can appear well before the developed stresses in a structural member reach the compressive yield strength of the respective member. A rectangular plate of dimensions ba× (i.e. length × width) under a uniaxial compressive load is shown in Figure 1

In these equations, the coefficients from the [A], [B] and [D] matrices are those appearing in the formulation of the Classical Lamination Theory (CLT). The critical buckling load N xis obtained when mn = 1= . For the needs of the present assignment, consider a simply supported rectangular plate a × b with a = b = 200mm, moduli of elasticity E1 = 172 GPa and E2 = 6.9 GPa, shear modulus G12 = 3.45 GPa, Poisson’s ratio ν12 = ν23 = 0.25, thickness of each lamina equal to 0.5 mm and density ρ = 1750 kg/m3.The lay-up of the laminate are defined later. 

2. Aims The aims of the present assignment are: 

• To be able to calculate the theoretical critical buckling load of a laminated composite plate
• 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

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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This Engineering Assignment has been solved by our Engineering Experts at My Uni Paper. Our Assignment Writing Experts are efficient to provide a fresh solution to this question. We are serving more than 10000+ Students in Australia, UK & US by helping them to score HD in their academics. Our Experts are well trained to follow all marking rubrics & referencing style.

Be it a used or new solution, the quality of the work submitted by our assignment experts remains unhampered. You may continue to expect the same or even better quality with the used and new assignment solution files respectively. There’s one thing to be noticed that you could choose one between the two and acquire an HD either way. You could choose a new assignment solution file to get yourself an exclusive, plagiarism (with free Turnitin file), expert quality assignment or order an old solution file that was considered worthy of the highest distinction.