Materials Modelling - AERO96011
This course provides additional theory needed for modelling failure of materials in modern high performance structures, e.g. aircraft. Part A of the course covers basic theory and computational approaches for fracture mechanics and fatigue, while part B covers the causes of failure of composite laminates and design methods for such materials.
- The definition of stress intensity factors and energy release rates as fracture criteria.
- The basics of linear elastic fracture mechanics in 2-D and 3-D components, including the Westergaard equations and relationships between the components and fracture criteria.
- The effects of geometry on stress intensity factor, and examples of 2-D and 3-D geometries including mixed-mode fracture. The use of finite element methods for calculating fracture criteria.
- A description of fatigue crack growth, Paris’ law, and finite element usage.
- Basic post-yield fracture mechanics, plasticity fundamentals, Irwin’s plastic zone size around crack tips, crack opening displacement, thickness effects, HRR fields, fracture criteria, and use of finite elements.
- A description of viscoelastic models.
- To describe the phenomenon of creep, including the different types of creep curves, constitutive laws, hardening effects.
- Causes and effects of impact damage on composite materials.
- Failure criteria for notched and impacted composite laminates.
- Failure of composite plies and its evaluation in different coordinate systems
- Failure of laminates and design methods to prevent failure.
- Interlaminar stresses and delamination growth in composite laminates.
- Bending and buckling of orthotropic plates and laminates.
Structural Mechanics and Dynamics - AERO95009
An earlier course AERO40008 Structures 1 is extended. This course aims to demonstrate the different ways in which stresses can be introduced into structures. Design against excessive deformation failure is examined through the analysis of a number of simple structural components. The course provides a basis for courses in aircraft structures, structural mechanics and Finite Elements Analysis which are met in the third and later years of the degree course. The concept of presenting structural problems in matrix form is given and the flexibility and stiffness matrices introduced. Free and forced vibration solutions for continuous and discrete systems are presented. Buckling of perfect and imperfect struts is described.