This module builds the basic mechanics and solids and aerospace structure principals by providing students with further skills in the analysis of stress, strain and deformation of advanced aircraft and spacecraft structures

Stress analysis of aerospace components: Tapered wing spars and box beams; beams having variable stringer areas. cut-outs; fuselage frames and wing ribs. principles of stiffener/web construction. Fatigue of aerospace structures: Safe life and fail-safe structures; designing against fatigue; fatigue strength of components; prediction of aerospace structure fatigue life; crack propagation. Aeroelasticity: Load distribution and divergence, control effectiveness and reversal, introduction to flutter. First Design of Spacecraft Structures. Stress analysis of cones, thin-walled tubes and rings in space structures. Structural and loading discontinuities: shear stress distribution in beams; shear lag. Structural Stability: Unstable behaviour; beam columns; slender column buckling; column imperfections and load misalignment; inelastic buckling; Approximate methods; thin plate buckling; crippling stresses. Crashworthiness: Bird strike and space impact events, hard debris/hail impact, certification. Composite Structures: Bolted composite joints; stresses in open hole and filled hole coupons, single/double lap joints, multi-bolt joints, load distribution, bearing/bypass stresses, joint failure; bonded lap shear joints; thin walled composite beams. Damage Evaluation Techniques; A-, B- and C-scan, X-ray, microscopy. Sandwich construction and honeycomb mechanical properties, stresses in face sheets. Design, safety and transportation load factors for standard structural elements of spacecraft structures

1. Understand the concept of aeroelasticity (including flutter) and how it can be used to avoid problems in structural design (homework for credit). 2. Understand the Aircraft and Spacecraft Certification process and how it shapes the design and testing of aircraft structures (impact on leading edge and plate structures). 3. Use advanced stress analysis techniques to solve complex problems in aerospace structural design. (homework for credit) 4. Evaluate bolted/bonded joint designs and apply engineering skills to identify efficient designs. (coursework for credit) 5. Solve problems related to fatigue of aerospace structures (homework for credit) 6. Design a stringer to withstand buckling loads using theoretical and finite element approaches (homework for credit) 7. Carry out a stress analysis of a tapered wing spar (cracked spar versus un-cracked spar), design a bolted/riveted repair. (coursework for credit) 8. Understand the basic concepts of spacecraft structure design: load limits and factors, selection of materials and manufacturing methods.

8. Co-operate with other members of small groups (coursework). 9. Appreciate societal issues of safe design of aerospace structures and the role of the engineer in society with respect to safety critical structures (case studies).

10. Manufacture a bolted/riveted repair for a cracked plate and test this repair, both statically and dynamically (i.e. fatigue test) on a universal straining frame. DIC systems, X-ray and C-scan systems. (lab work for credit).

The module will be delivered by 2 lecture hours and one 3-hour slot per week. The student will learn how to carry out a stress analysis of aerospace structures using the latest experimental, numerical and theoretical stress analysis techniques. Research findings are incorporated into the lab aspects of the course. Also, case studies are used to disseminate the latest research findings, primarily in the areas of composite aircraft and spacecraft design, manufacturing and characterisation.