MAE4408 - Damage tolerance and airworthiness
6 points, SCA Band 2, 0.125 EFTSL
Undergraduate Faculty of Engineering
Leader(s): R Jones
Offered
Clayton Second semester 2009 (Day)
Synopsis
This unit will explain why aircraft structures/components fail, how engineers can learn from such failure and design to prevent it. Both fundamental and applied aspects of failure of aircraft structural components will be covered. The unit will detail the damage tolerance design philosophy, and how it fits into airworthiness requirements as described in the relevant Standard (JSSG 2006). The unit focuses on how fracture mechanics principles and modern fatigue crack growth laws are used to meet JSSG2006. To illustrate the effect of cracking on service aircraft we will consider flaw growth in a range of aircraft undergoing both in-service flight loading and full scale fatigue tests.
Objectives
Understand how fracture mechanics principles can be used to ensure the safety of aircraft structural components. Understand modern fatigue crack growth theories and how these can be used to ensure the continued airworthiness of aircraft structural components. Explain the way in which damage tolerant design fits into JSSG 2006. Solve problems associated with the residual strength of cracked aircraft structural members. Solve problems associated with crack growth in aircraft structural members. Design composite repairs to cracked aircraft structural member.
Assessment
Class Test 10%
Mid Semester Examination 20%
Class Project: 20%
Examination (2 hours): 50%
Contact hours
3 hour lectures, 2 hours practical classes or laboratories and 7 hours of private study per week