Undergraduate - UnitMAE4408 - Damage tolerance and airworthiness

This unit entry is for students who completed this unit in 2012 only. For students planning to study the unit, please refer to the unit indexes in the the current edition of the Handbook. If you have any queries contact the managing faculty for your course or area of study.

print version

6 points, SCA Band 2, 0.125 EFTSL

Refer to the specific census and withdrawal dates for the semester(s) in which this unit is offered, or view unit timetables.

Level	Undergraduate
Faculty	Faculty of Engineering
Offered	Clayton Second semester 2012 (Day)
Coordinator(s)	Professor Rhys Jones/Mr John Baker

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.

Outcomes

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.