Design, Durability and Integrity of Composite Aircraft Structures

In the first half of the course comparisons with metallic material properties are drawn illustrating the areas of superiority and the deficits associated with carbon fibre laminates. Properties considered include static strength and stiffness in tension and compression, response to stress concentrations, property degradation due to elevated temperature and humidity, in-plane fatigue, impact damage and delamination growth under fatigue. Properties are considered in terms of coupon properties together with the behaviour of structural elements. Techniques for stress and strength calculation in laminates complete the treatment of composite material performance and design. The later part of the course emphasises application issues with lectures from aircraft designers about current developments in composite civil and military aircraft.  Aircraft regulatory input concludes the course. The special issues relevant to approval of composite aircraft structure as damage tolerant, together with inspection and maintenance issues are covered in detail.