For predicting the forming behaviour of Al-Mg-compounds and changes in the interface strength during further processing it is essential to accurate determine the occurring state of stress on the interface. For this purpose precise material properties of the compound are needed. Tensile tests with hydrostatic extruded AZ31 and AlSi1MgMn revealed flow curves with strong dependencies on temperature, strain rate and thermal treatment. During dwell times the true stress relaxes significant under high temperatures.

Turbogenerator coil retaining rings (CRRs) are shrunk fitted onto the rotor over the coils, in order to restrain them against the centrifugal force. They are typically subjected to low cycle fatigue (LCF), with a cycle being completed at every machine switch-on and switch-off. The object of this paper is to show a computationally efficient methodology, based on the AMV, to determine the failure probability of a CRR. Its estimation is based on the experimental evaluation of material static, cyclic and fatigue properties and on the knowledge of the entity of cyclic loads. The determined value, in the order of 10^-11 at the last stage of the machine life, is compatible with reference values for structures under fatigue in the aeronautical field.

The presented paper is divided into experimental, numerical, and analytical studies and gives an overview of the current computation of knurled interference fits. Experimental joining/push out studies were done to estimate the strength of the connection, to define the forming or cutting joining process, and to validate the numerical model. With the help of the static torque studies we explain the mechanical breakdown of these shaft-hub connections. To save experimental time and improve the connection we validated a numerical model. With the help of the current analytical equations we can compute a forming knurled interference fit up to a geometric interference of 0.55 t.

Carbon fibre in polyphenylene sulfide composites became popular material in aircraft industry but its fragility to impact loading limits the application of these composites in aircraft primary structures. The article deals with experimental investigation of the response of damaged composite. Material degradation of intact and damaged specimens during fatigue tests was investigated. As damage parameters the changes in natural frequencies, ultrasound wave propagation and bending stiffness were chosen. In the article the entire fatigue life of intact and damaged specimens was studied by all the presented methods and the accuracy and reliability of assessment of damage parameters were compared.

This paper deals with development of the volume model of irregular specimens using optical projections. A sequence of 360 projections of the specimen was acquired and processed using a custom set of procedures developed in MatLab environment. The projections were segmented, filtered and smoothed. A semiautomatic procedure was used to calibrate scale of the projections and to remove eccentricity of axis of rotation of the specimen. The volume model was obtained using inverse Radon transform. Additional procedures were developed to obtain crosssection characteristics required for evaluation of corresponding micromechanical test. For verification of the developed procedure volume models of known shaped objects were estimated and compared.